Experimental Investigation of Temperature and Velocity Distribution About a Rocket Jet Citation Whitmore, Quentin Robert (1947) Experimental Investigation of Temperature and Velocity Distribution About a Rocket Jet. Master's thesis, California Institute of Technology. doi:10.7907/SN1E-KS25. https://resolver.caltech.edu/CaltechETD:etd-12092008-140117 Abstract The purpose of the investigation was to determine the temperature distribution and velocity profile surrounding the wake of a 1500 pound thrust liquid rocket motor. The temperature measurements were restricted to those 500°F and below. The velocities measured were in the region in which the temperature measurements were made. The region in which the temperatures exceeded 500°F was found to be included within a solid angle of ten degrees. The high temperature region was found to be larger than the high velocity region. The investigation was carried out during the academic year 1946-1947 at GALCIT Jet Propulsion Laboratory under the supervision of Dr. Robert H. Boden. Item Type: Thesis (Master's thesis) Subject Keywords: Aeronautical Engineering ; Electrical Engineering Degree Grantor: California Institute of Technology Division: Engineering and Applied Science Major Option: Aeronautics Electrical Engineering Thesis Availability: Public (worldwide access) Research Advisor(s): Unknown, Unknown Group: GALCIT Thesis Committee: Unknown, Unknown Defense Date: 1947 Record Number: CaltechETD:etd-12092008-140117 Persistent URL: https://resolver.caltech.edu/CaltechETD:etd-12092008-140117 DOI: 10.7907/SN1E-KS25 Default Usage Policy: No commercial reproduction, distribution, display or performance rights in this work are provided. ID Code: 4913 Collection: CaltechTHESIS Deposited By: Imported from ETD-db Deposited On: 07 Jan 2009 Last Modified: 16 Mar 2023 22:57 Thesis Files Preview PDF (Whitmore_qr_1947.pdf) - Final Version See Usage Policy. 22MB Repository Staff Only: item control page

BAPER = RIMMED NTAL INVESTIGATION OF TEMPERATURE ND VELOCITY DISTRIBUTION ABOUT A ROCKET JET ~ by Lt. @. R. Whitmore, U,S.N, In Partial Fulfillment of the Requirements for the Professional Degree in Aeronautical Engineering California Institute of Technology Pasadena, California Ca eo i ae) rt Load G nD Be PES Pea) & a Bay te od co a be ACKNOVWLE DGEMENT In presenting this thesis, the author wishes to express his appreciation and gratitude to Dr. R, H, Boden of the Jet Propulsion Laboratory, California Institute of Technology, for his personal supervision, helpful suggestions and expeditious coordination of supply and test vit facilities, The author is indebted to Mr, Stanley S$. Corrsin for his helpful suggestions concerning equipment which could be used for the investi~ The author wishes to express his appreciation for the cooperation fe OW and suggestions of Mr. anthony Briglio and the members of the pit "PF" test crew. SUMMARY The purpose of the investigation was to determine the temperature distribution and velocity profile surrounding the wake of a 1500 pound thrust liquid rocket motor, The temperatures measurements were re- stricted to those 500°F and below. ‘The velocities measured were in the region in which the temperature measurements were made, The region in which the temperatures exceeded SOO0°F was found to be included within a solid angle of ten degrees. The high tempera- ture region was found to be larger than the high velocity region, The investigation was carried out during the academic year 1946- 1947 at GALCIT Jet Propulsion Laboratory under the supervision of Dr. Robert H. Boden, INTRODUCTION The jet of gases from a de Laval nozzle has been extensively studied by a number of investigators, These studies were primarily limited to the shock wave characteristics in the supersonic flow, Optical methods have been developed to show the variation of density in the jet. However, little experimental work has been done to deter= mine the velocity, pressure, and temperature in the jet and in ths regions surrounding the high velocity gases. The object of this investigation was to measure the velocity and temperature distribution in the region surrounding the high velocity luminous gases, The measurements were carried out at GALCIT in the Jet Propulsion Laboratory during the academic year 1946-47 under the supervision of Dr, Robert Boden. 2e EQUIPMENT The liquid rockets which were run for performance date with various fuel specifications were of the regeneratively cooled type developing a 1500 pound thrust, The rocket motors were ail mounted on the same thrust carriage and the structure of the pit surrounding the rockets rem@ined essentially the same for all of the rus. The rocket motors were mounted horizontelly as shown in Fig. I. l and 2 show the irregular nature of the area into which the rocket was fired, The radiation thermocouples which were used to make the tempera- ture survey were of the iron-constantan type. Instructions and a schematic drawing of the type used may be found in Fig. 3, The thermocouples were used in connection with a Brown Potentiometer which had 15 outlets. The potentiometer could record the 15 different ten- peratures at a rate of one 4 second if the temperature at each thermo-~ couples were constant. Fig. 5 is a photograph of this Brow Potentio= meter, A rack made of pipe and angle iron was built to hold the ther- mocouples in vosition as shown in Fig. 5. To redues the effect of radiation, a shield was built to protect a thermocouple from the flame of hot gases, Fig. 6 is a schematic representation of the shield used to produce this effect. A Leeds and Northrop portable optical Pyrometer, No, 8622, was used to determine the flame temperature of the luminous flame, The cireult of this pyrometer appears in Fig. 7. 3e A stagnation temperature probe which doubled as a shislded ther- mocouple was mounted on the rack as show in Fig. 5. Pig. 3 is a photostatic copy of the production drawing for the stegnation probe. The Prandtl Pitot tube was selected as best suited for the velocity survey because of its yaw characteristics as showm in Fig. 9, Fig. 10a and Fig. 10b are copies of the production drawings for the Prandt tube, Because of the high temperatures to which the tubes were to be subjected, the joints were all silver soldered, The Pitot tubes were mounted upon the thermocouple rack six inches apart, (Fig. 5), One- quarter inch copper tubing was used to commect the Pitot tubes with the tubes of the multiple manometer board, The multiple manometer board (Fig. 11) consisted of 12 "U" tubes half filled with alcohol. The alcohol was dyed red to improve its photographic characteristics. The board was mounted upon a frame of angle iron which could be bolted in three tilting positions (90°, 30°, and 14.5°). To record the manometer tube displacements, & 35 mm, movie cameras was mounted on the manometer frame. Two reflector type photo flood lamps, mounted as shown in Fig. 11, provided the illumin- ation. To measure the velocities close to the motor within the firing pit, a remote control variable position Prandtl tube was built (Fig. 12). A small synchro was placed inside of a metal box with a sheft protruding through the top to which the Prandtl tube was mounted (Fig. 13). The control synehro end power source for the variable. position Pitot tube can be seen in Fig. 14. This control station wes inside the observation room of the pit. Fig. 15 is the electrical circuit for the control of the variable position Pitot. The pressures 4, from this remote controlled Pitot tube were measured with the small inclined manometer, Fig. 16. The luminous vertion of the jet was vhotographed with an Eastman high speed 16 mm. movie camera, The camera was capable of taking 3,000 frames a second and was run at top speed for these photogravhs. Two portions of the flame were studied; (1) the region just aft of the nozzle; (2) the region in which the luminous flame ends, 5e PROCEDURE wr The rocket motors were run primarily for performance information. The temperature and velocity survey of this report was added after the performance series had been started. (1) An initial survey to determine the sultebility of an iron- constantan thermocouple was made during test runs Nos, 18, 19, 20, 2l, 22, @4, 25, 26, 27 and 29, The lag in temperature response was measured during these runs, (2) An attenpt was made to protect the thermocouple from the direct radiation of the flame and to determine the effectiveness of a shield during run Nos, 28, 29, 30, 51, 32, 33, 34, and 35, (3) A Prandtl Pitot-statie tube was placed in the field to determine the possibility of using that tube for the velocity survey during runs Nos. 37 and 38. The initial runs demonstrated that the instruments selected could be used to obtain the objectives, A rack was made upon which 11 thermo- couples and 12 Pitot tubes were mounted, The Brown Potentiometer was available in the pit and the inclined manometer board was built so that velocities over a wide range could be determined, The rack was placed perpendicular to the longitudinal axis of the motor at five stations behind the motor, The five stations were 26.5, 24,5, 22, 19 and 16 feet aft of the motor nozzle, The rack was so oriented for runs 73 to 93 inclusive. Por runs 95 to 98 the rack was placed at a 37° angle so that the direction of the velocity could be determined. The temperature survey within six feet of the motor 6. was completed by placing the rack parallel with the longitudinal axis of the motor during runs 99 and 100, The stagnation temperature was determined by placing the stagna- tion probe on the rack for runs 95 to 98 inclusive. The remote control Pitot tube was placed inside the pit close to the motor to measure the velocity profile there during runs 34 to 98 inclusive. The investigation was extended to the flame characteristics with the use of the Leeds and Northrop Optical “yrameter and an Eastman high speed movie camera, The optical pyrometer was held 10 feet aft of the motor and 10 feet from the axis of the flame. From this position the pyrometer was sighted upon the flame six feet aft of the nozzle, The high speed camera was set up to take kodachrome pictures of the exit of the motor during run No, 84, Black and white pictures of the end of the flame were taken during run No, 85, The camera was 10 feet from the flame during run No.84 and 45 feet from the lame during run No, 85, 7. RESULTS AND DISCUSSION (1) A blackened thermocouple when exposed to a high temperature requires time to reach that temperature, Fig, 18 is the response of the thermocouples which were used in this investigation. The data for this curve was obtained from runs Nos, 18 to 28 as shown in Table I(a) to I1(3). It was realized that the response of the thermocouple was faster when the change in temperature was small compared with the ambient air temperature. (2) The shield about the thermocouple reduced the temperature rise and also produced a mich slower temperature rise as is indicated in Fig. 18, (3) The temperature surveys taken 26.5, 24.5, 22, 19 and 16 feet aft of the motor are plotted, Figs. 19a to 23a and 24a and b, as temperature rise versus radial distance from the center line of the axis of the flame. The rise in temperature was in each case corrected for time lag by the use of the thermocouple Response Curve, Fig. 17. The data is quite consistant considering the variations caused by winds and that the mixture ratio was seldom repeated. However, the temperatures measured by the thermocouples are not necessarily the air temperatures, since the air is relatively transparent to radiation. The thermocouples reached equilibrium after sixty seconds which indicates that they were losing as much energy via conduction along the leads, convection to the air, and the radiation losses as they were receiving via radiatim, Some of the temperatures were teken in the mixing region of the jet gases and ambient air. The location of this mixing region was not determined in this investigation. 8. (4) The flame temperatures six feet aft of the nozzle as measured by the optical pyrometer, were 3390°F, 3260°F, and 3300°F, These temperatures are approximately 600° above the theoretical exit temperatures, This may be explained by the after burning of the exhaust gases, The emissivity of the flame was taken to be unity because it consists mainly of flowing carbon particles, The pyrometer was hand held at a distance of ten feet aft of the motor and ten feet from the center line of the exhaust flame. A slight burning sensation was felt by the observer on the face and arms which were exposed to the flame. (5) The velocity measurements were made with the assumption that the flow was parallel with the ground at the level of the motor. This assumption was not checked and may have been erroneous, The velocity versus distence from the center line of the exhaust jet may be Pound in Figs. 19b to 23b,. A plot of the velecity profile showing direction velocity and streamlines may be seen in Pigs, 25 and 27, (6) The characteristic of the first shock wave aft of the motor in the jet was recorded on a Kodachrome film by the Eastman high speed camera during run No, 84, It was not possible to measure the velocity of the exhaust gases from this film. A higher speed camera with a larger field is necessary, The average velocity of the end of the luminous gases which was measured from the black and white film taken during run No, 85, was determined to be 2300 ft/sec. Since the flow was subsonic at this distenee from the motor, this would require an exhaust temperature of 2110°F at least, if the of the gases was 1.2, The velocity was therefore considered to be a reasonable one. 9. CONCLUSIONS AND RECOMMENDATIONS é (1) The temperatures surrounding the jet of a 1500 pound thrust liquid rocket, as measured by a blackened thermocouple, are surprising- ly low. The high temperature region gradually expands as the distance aft of the motor is increased, At 26.5 feet aft of the motor, the temperature can be expected to be 500°F higher than ambient at a dis- tance of 25 inches from the center line of the motor. At a distance of four feet aft of the nozzle, the temperature rise can be expected to be 500° when only 12 inches from the center line of the flame. However, @ considerable amount of heat is conducted away by the the rmo- couple leads. Therefore, before placing equipment as closely as these temperatures indicate as safe, it would be necessary to determine the heat losses of the equipment to be expected from conduction, radiation, and convection. (2) The velocity survey was rather sketchy, but does show that the induced velocities are quite small and of the order of 50 ft/sec The velocities were appreciable (ever 100 ft/sec. ) in the region in which mixing was expected, Jt was found that the high temperature regions were larger than the high velocity region, as was found by other investigators dealing with small hot jets. The induced velocities might be successfully measured with the use of small smoke sources placed throughout the region of interest and the paths of the smoke recorded by a movie camera, A rack of Pitot tubes could be made so thet each tube could be pivoted during the run, This could be accomplished very nicely by electrical or mechanical linkages. 10, The survey should be extended to include the luminous region of the exhaust gases, A spectogram of the flame would be desirable, The optical pyrometer could be successfully employed to determine the flame temperatures if the emissivity of the flame were determined. The ultra-high speed camera may be the best method to determine the velocities of the hot exhaust gases, Run #18 Fuel frvoll Oxidizer WFNA TABLE Ta TEMPERATURE SURVEY Duration of Run 45.8 sec. Mixture Ratio 1.45 M-272 Thermocouple #2 Thermocouple #43 Dist. Aft of Motor Le" Dist. from ¢ of Motor 67" Dist. Aft of Motor = 8" Dist. from g of Motor 21" Time Temperature Time Temperature Sec. oF Sec. Op ) 52 9) 52 6 86 7 132 37 106 38 152 53 82 5h, 122 70 7h 71 109 TABLE Ib TEMPERATURE SURVEY Run #19 Duration of Run 59.6 sec. Motor M-272 Fuel FUOH Oxidizer WPNA Mixture Ratio 1.26 Thermocouple #2 Thermocouple # 3 Dist. aft of Motor 8" Dist. aft of Motor 4g" Dist. from f of Motor 67" | Dist. fromg of Motor 15" Time Temperature Time Temperature Sec. ‘OF Sec. OF 0 53 0 53 1h, 7h 15 1h2 35 82 a7 166 58 85 59 169 Run #20 Fuel FUOH Oxidizer WENA TABLE Ic TEMPERATURE SURVEY Duration of Run 5 sec, Mixture Ratio 1.96 M~272 Thermocouple #2 Thermocouple #4 Dist. aft of Motor Le" Dist. from ¢ of Motor 67" Dist. aft of Motor he" Dist. from ¢ of Motor 12" Time Temperature Time Temperature Sec. Op Sec. OF 8 56 0) 56 30 69 6 386 44 L2G TABLE Id TEMPERATURE SURVEY Run #21 Duration of Run Wh.9 sec. Motor M-272 Fuel FUOH Oxidizer WFNA Mixture Ratio 1.91 Thermocouple #2 Thermocouple #3 Dist. aft of Motor 48" | Dist. Art of Motor = 8" Dist. from¢of Motor 67" Dist. fromg¢g of Motor 12" Time Temperature Time Temperature Sec. OF Sec. OF 0 D7 0 a7 18 70 30 holy TABLE I(f) TEMPERATURE SURVEY Run #23 Duration of Run l5 sec. Motor M-272 Fuel FUOH Oxidizer WFNA Mixture Ratio 2.40 Thermocouple #2 Thermocouple #3 Dist. Aft of Motor 48" | Dist. Aft of Motor he" Dist. from¢@ of Motor 67" Dist. from g of Motor 12" Time Tempera ture Time Temperature Sec. OF Sec, OF 0 55 0 56 15 87 16 226 ho 93 2 2h0 TABLE I(g) TEMPERATURE SURVEY Run #2) Duration of Run 15.1 sec. Motor M-272 Fuel FUOH Oxidizer WFNA Mixture Ratio 2.30 Thermocouple #2 ite Thermocouple #4 Dist. Aft of Motor hs" Dist. from € of Motor 67” Dist. Art of Motor 120" Dist. from¢g of Motor 30" Time Temperature Time Temperature Sec. OF Sec. oF 0 73 0 Tu 12 91 wh 151 47 102 39 173 TABLE I(h) TEMPERATURE SURVEY Run #25 Duration of Run 5.1 sec. Motor M-272 Fuel FUOH Oxidizer WFNA Mixture Ratio 2.26 Thermocouple #2 Thermocouple #3 Dist. Aft of Motor Lg" Dist, Aft of Motor 120" Dist. from g of Motor 67" Dist. fromg of Motor 30" Time Temperature Time Temperature Sec, OF Sec. OP 0 64, 0 88 1 65 2 130 31 99 32. 1)8 Run #26 Duration of Run 21 sec. Fuel FUOH TEMPERATURE SURVEY TABLE r(4) Oxidizer WFNA Mixture Ratio 2.39 Motor M272 Thermocouple #2 Thermocouple #4 Dist. Aft of Motor Lg ft Dist. from ¢ of Motor 67" Dist, aft of Motor 120" Dist. from ¢ of Motor 18" Time Temperatures Time Temperature Sec, OF Sec, OF 0 7h 0 79 11 90 15 89 TABLE I(4) TEMPERATURE SURVEY Run #27 Duration of Run 5.1 sec. Motor M-272 Fuel FUOH Oxidizer WFNA Mixture Ratio 2.20 Thermocouple #2 Thermocouple #3 Dist. Aft of Motor Le" Dist. Aft of Motor 120" Dist. from ¢ of Motor 67" Dist. from @ of Motor 19" Time Temperature Time Temperature Sec. OF Sec, Op ) 67 ) 67 30 90 35 500 TABLE II(a) TEMPERATURE SURVEY Run #28 Duration of Run 15. sec. Fuel FUOH Oxidizer WFNA ‘iixture Ratio 2.56 M-272 Thermocouple #2 Thermocouple #3 Dist. Aft of Motor use" Dist. from¢g of Motor 67" Dist. Aft of Motor 6" Dist. fromg of Motor 2)," Time Temperature Time Temp erature Sec. OF Sec. On 0 67 0 67 12 79 13 70 lo 89 Wa 130 65 79 66 126 82 120 Run #29 Fuel FUOH Oxidizer TABLE II(b) TEMPERATURE SURVEY Duration of Run 15 sec. Mixture Ratio 2.53 M-272 Thermocouple #2 Thermocouple #3 Dist. Aft of Motor Le" Dist. from ¢ of Motor 67" Dist. Aft of Motor se" Dist. from g of Motor 2h" Time Temperature Time Temperature Sec. OF Sec. OF 0 66 0 66 22 82 8% 102 Lis 86 16 122 210 119 TABLE II(c) TEMPERATURE SURVEY Run #30 Duration of Run 15.2 sec. Fuel FUOH Oxidizer WFNA Mixture Ratio 4,03 M-272 Thermocouple #2 Thermorouple # Dist. Aft of Motor hs" Dist. from ¢ of Motor 67" Dist. Aft of Motor 4g" Dist. from G of Motor 22" Time Temperature Time Temp erature Sec. OF Sec, OF 0 62 0 62 15 71 16 82 Lo Thy ha 105 65 10), 82 102 TABLE II(d) TEMPERATURE SURVEY Run #41 Duration of Run Fuel FUOH 5.2 sec. Oxidizér WFNA Mixture Ratio 3.11 Motor M-272 Thermocouple #2 Thermocouple #3 Dist. Aft of Motor 48" | Dist. art of Motor 15" Dist. fromg of Motor 300" | Dist. fromgof Motor 36" Time Temperature Time Temperature Sec. OF Sec. OP ) 57 0 59 26 63 27 90 of 97 7h 96 Run #32 Fuel FUOH Oxidizer TABLE TI(e) TEMPERATURE SURVEY Duration of Run 5.6 sec. Mixture Ratio 43.10 Motor M-272 Thermocouple #2 Thermocouple #3 Dist. Aft of Motor Le" Dist. from g of Motor 67" Dist. Aft of Motor he" Dist. from ¢ of Motor 22" Time Temperature Time Temperature Sec. OF Sec. OF ) 64, 0 6h, 23 75 el, 86 20 73 56 105 73 70 an 102 TABLE II(f) TEMPERATURE SURVEY Run #33 Duration of Run 15 sec. Motor M-272 Fuel FUOH Oxidizer 95% WFNA & 5% Hod Mixture Ratio 4.10 Thermocouple #2 Thermocouple #3 Dist. Aft of Motor 46" | Dist. Aft of Motor 4g" Dist. from @ of Motor 67" Dist. from g of Motor 22" Time Temperature Time Temperature Sec. oP Sec. (OF 0 66 0 68 13 90 1h 76 38 Lol, 39 96 62 BE 63 105 Run #3), Fuel FUOH Oxidizer 95% WFNA & 5% Hoo TABLE II(g) TEMPERATURE SURVEY Duration of Run 5 sec. Mixture Ratio Motor M-272 1.73 Thermocouple #2 Thermocouple #3 Dist. Aft of Motor Ls" Dist. from ¢ of Motor 67" Dist. Aft of Motor Le" Dist. from ¢ of Motor 22" Time Temperature Time Temperature Sec, OF Sec, OF 0 68 fe) 68 10 89 11 75 30 106 31 92 107 8h 108 120 156 80 137 12h, TABLE YI(h) TEMPERATURE SURVEY Run #45 Duration of Run Lhe sec. Motor M-272 Fuel FUOH Oxidizer 95% WFNA & 5% Hoo Mixture Ratio 2.15 Thermocouple #2 Thermocouple #3 Dist. Art of Motor Lge Dist. Aft of Motor 120" Dist. from ¢ of Motor 67" Dist. from¢ of Motor 13" Time Temperature | Time Temperature Sec, oF Sec. OF F 66 6) 7h 29 96 1 266 40 500 TABLE II(4) TEMPERATURE SURVEY Run #36 Duration of Run |h.8 sec. Motor M-272 Fuel FUOH Oxidiger 95% WFNA & 5% Ho0 Mixture Ratio 2.05 Thermocouple #2 Thermocouple #3 Dist. Aft of Motor L8" | Dist. Aft of Motor 120" Dist. from g@ of Motor 67" | Dist. fromg of Motor 22" Time Temperature ‘Time . Temperature Sec. OF Sec. OP 0 66 0 72 11 8h, iy 166 an 98 35 182 TABLE II(j) TEMPERATURE SURVEY Run #38 Duration of Run 59 sec. Motor M-272 Fuel FUOH Oxidizer 95% WFNA & 5% HoO Mixture Ratio 2.20 Thermocouple #2 Thermocouple #3 Dist. Aft of Motor 18" | Dist. Aft of Motor Le" Dist. from ¢ of Motor 67" | Dist. from Z of Motor 15" Time Temperature Time Temperature Sec, OF Sec. Op ) 61 0 62 9 76 10 126 De 86 33 11 oy) 92 29 158 TABLE II(k) TEMPERATURE SURVEY Run #39 Duration of Run l5 sec. Motor M272 Fuel FUOH Oxidizer 95% WFNA 5% H,0 Mixture Ratio .2,32 Thermocouple #2 Thermocouple #4 Dist. Aft of Motor hg" Dist. Aft of Motor 15" Dist. from ¢ of Motor 300" Dist. from g of Motor 36" Time Temperature Time Temperature ‘Sec. OF Sec, Op 0 56 0 6h, za 58 10 1h5 38 169 TABLE Da TEMPERATURE SURVEY Run #73 Duration of Run 15.1 sec. Motor M272 Fuel 60% Aniline 2 0% FUOH Oxidiz er 6 1/2% RFNA Mixture Ratio 2.03 Distance Aft of Nozzle 2 6.5 ft. | Distance Thermo~- | Time of Temp. of emp. Rise from couple Reading Thermo- Corrected Numb er after Temp. couple Temp. for of Motor Sta rt before Rise Thermo. — of Run Run | Response ( inches) (Sec.) (°F) ( °F) AT ATs 13 5 10 500 56 hhh 710 19 6 11 500 | 57 ha 681 25 7 13 L275 57 18 590 31 9 25 318 a7 291 351 37 10 28 276 57 219 ehh LZ 11 29 210 57 153 168 hg 13 35 15k 58 96 102 55 1h 37 Lil 58 53 56 61 15 Re 100 58 he hy Run #74, Fuel 80% Aniline Oxidizer 6 1/2% RFNA TABLE III b TEMPERATURE SURVEY Duration of Run l5 sec. 20% FUOH Motor M-272 Mixture Ratio 1.69 Distance Aft of Nozzle 26.5 ft. |Distance Thermo- Time of Temp. of remp. Rise from couple Reading Thermo-= Lrorrected Numb er after Temp. couple Temp. for of Motor Start before Rise Thermo, of Run Run Response ( inches) ( Sec.) °F F AT AT; 13 5 22 500 48 52 532 19 6 23 500 9 4521 525 25 7 2h, L.60 52 os 470 31 9 39 318 17 e71 282 37 10 lio 282... 7 235 ahh L.3 11 50 150 Lé 10h, 105 9 13 53 Lol, 52 52 53 55 1h 5u 80 54 26 26 TABLE Ile TEMPERATURE SURVEY Run # 75 Duration of Run 15,0 sec. Motor 4.272 Fuel 80% Aniline 20% FUOH Oxidizer 6 1/2% RFNA Mixture Ratio 1.70 Distance Aft of Nozzle 26.5 ft. ‘Distance Thermo- | Time of Temp. of Temp. Risa from couple | Reading Thermo- Gorrected ¢ Number after Temp. couple Temp. for — of Motor Start before Rise Thermo. of Run Run Response inches Sec. oF or AT Ak 29 6 LO 315 72 23 389 35 7 “Ly 218 72 146 200 1 18 177 71 106 132 7 10 25 136 7é 6h, 73 53 11 26 10h, 72 52 36 99 13 30 9h 72 22 ah 65 Ly 31 85 7e 1) 14 71 15 42 83 72 11 12 TABLE td TEMPERATURE SURVEY Run #77 Duration of Run l.8 sec. Motor M-272 Fuel 80% Aniline 20% FUOH Oxidizer 6 1/2% RFNA Mixture Ratio 1.10 Distance Aft of Nozzle 26.5 ft. Distance | Thermo- .| Time of Temp. of Temp. Rise from couple Reading Thermo- Corrected Number after Temp. couple Temp. for — of Motor Start before Rise Thermo, of Run . Run Response inches Sec. OF oF / AT ATe 59 11 1 91 68 23 - 67 14 6 89 68 21 h7 71 1h 7 8h 68 16 32 77 15 8 80 68 le 22 29 6 29 26 68 358 39h, TABLE IL e TEMPERATURE SURVEY Run #78 Duration of Run 15 sec. Motor M-272 Fuel 80% Aniline 20% FUOH Oxidizer 6 1/2% RFNA Mixture Ratio 1.38 Distance Aft of Nozzle 26.5 ft. Distance| Thermo- Time of Temp. of Temp. Risa from couple Reading | Thermo- Corrected Number after Temp. couple Temp. for of Motor Start before Rise Thermo. of Run Run Response inches See. oF OF AT ATe 29 6 21 28 76 352 21 35 7 22 382 80 302 356 Ta 9 39 28h, 76 208 216 Li7 10 Lo 158 76 82 85.5 53 11 h6 115 78 37 37 8 59 14 51 100 75 25 25.2 65 1h 52 92 76 16 16 71 15 53 90 79 11 11 TABLE JIL f TEMPERATURE SURVEY Dura tion of Run 5.2 sec. Run #80 Motor M-272 Fuel 80% Aniline 20% FUOH Oxidizer 6 1/2% RFNA 26.5 ft. Mixture Ration 2.36 Distance Aft of Nozz le Distance! Thermo~ |Time of Temp. of Temp. Rise from couple |Reading Thermo-~ Corrected Number after Temp. couple Temp. for — of Motor Start before Rise Thermo. of Run Run Response Incnes Sec F °F AT ATe L7 10 1 127 85 he - 59 13 9 110 82 28 Lé 65 1h. 10 102 80 22 35.2 71 15 11 96 8h 12 18.5 17 3 20 4.80 85 395 L476 23 ho her 85 336 350 29 6 hh 36 85 261 268 TABLE TIT 9 TEMPERATURE SURVEY Run #81 Duration of Run 1)5.2 sec. Motor M-272 Fuel 80% Aniline 20% FUOH Oxidizer 6 1/2% RPNA Mixture Ratio 2.36 Distance Aft of Nozzle 26.5 f t. |lpistance | Thermo- | Time of Temp. of Temp. Rise from couple Reading Thermos Corrected Number after Temp. couple Temp. for of Motor Start before Rise Thermo. of Run Run Response inches Sec. oF oF AT Ale 27 4 22 25 56 466 h1g 31 5 225 35 56 190 202 37 { 6 190 36 56 15 162, 3 7 121 ho 56 81 BL.5 L9 9 93 2 53 51 52.5 55 10 80 LZ 56 37 38 61 11 66 hi 5h 22 22.4 Run #82 Fuel 80% Aniline TABLE DW 2 Duration of Run lO sec, 20% FUOH TEMPERATURE SURVEY Motor M-293 Oxidizer WPNA Mixture Ratio 1.75 Distance Aft of Nozzle 2.5 ft. Distance Thermo- |Time of | | Temp. of Temp. Rise from couple Reading Therno- Corrected Number after Temp. couple Temp. for — of Motor Start before Rise Thermo. of Run Run Response incthes Sec of of aT Atk hi 3 9 2 8 72 100 352 li? 5 10 172 72 62 167 53 6 11 13h 72 35 100 59 7 1h 106 71 20 5h 65 9 15 92 72 10 28 71 10 16 82 72 6 13 77 11 18 78 72 5 8 83 ) lg 77 7é 2 6 89 1h 20 7h 72 3 3 95 15 51 an 71 12 r TABLE IVb TEMPERATURE SURVEY Run #83 Duration of Run 15.3 sec. Motor M-29% Fuel FUOH Oxidizer WFNA Mixture Ratio 1.77 Distance Aft of Nozzle 2.5 ft. pitrom | couple. [Reading | thermos Corrected Number after Temp. couple Temp. for of Motor Start before Rise Thermo. of Run Run Response inches Sec. of oe AT AT: Th 3 15 226 63 163 218 7 y) 23 187 6h, 124 13 53 6 26 132 58 7h 83.5 59 7 33 102 62 ho La 65 9 38 70 55 15 16 71 10 39 69 62 7 7 77 il Lo 67 62 5 5 83 13 2 67 62 5 5 89 Ly TS) 66 63 3 3 95 15 hh 6; 62 2 2 TABLE Wa TEMPERATURE SURVEY Run #85 Duration of Run 49.9 sec. Motor M-29% Fuel FUOH Oxidizer WENA Mixture Ratio 2,22 Distance Aft of Motor e2 ft. Distance| Thermo- | Time of Temp. of Temp.Rise from couple Reading Thermo- Sorrected Number after Temp. couple Temp. for | of Motop Start before Rise Thermo. of Run Run Response inches Sec. oF oe AT AT. ral 3 11 134, 60 7h 11), L7 y 13 116 68 U7 67 53 6 19 8h, 68 16 30 59 7 20 74 68 6 7 65 9 25 73 68 5 6 71 10 26 70 68 2 B) 77 ie 27 69 68 l 1 83 13 30 69 66 3 3 89 wy 31 66 6h, 2 2 95 15 52 69 66 3 5 Run #87 Fuel FUOH Oxidizer WFNA TABLE Vb TEMPERATURE SURVEY Duration of Run 15 sec. Motor M-29% Ww Mixture Ratio 2.16 Distance Aft of Nozzle 22 ft. Distance | Thermo- |Time of Temp. of Temp. Ris from couple | Reading Thermo-~ Corrected Numb er after Temp. couple | Temp. for — of Motor Start before | Rise Thermo, of Run Run Response inches Sec. all °F AT AT, 36 5 1h 12 58 8h 116 ha 6 16 100 58 he 55 8 7 18 80 58 22 28 5h, 9 21 72 58 1h 17 60 10 23 65 58 7 8 66 11 ey 63 58 5 6 72 13 28 63 58 5 6 78 1h 29 62 58 4 in 8. 15 30 62 58 Ly mn * 2 36 136 58 78 82 30 3 38 188 58 130 135 REMOTE PITOT TEMPERATURE TABLE We TEMPERATURE SURVEY Run #88 Duration of Run 1)1).8 sec. Motor WM-29% Fuel FUOH Oxidizer WFNA Mixture Ratio 2.22 Distance Aft of Nozzle 22 ft. Distance | Thermo- Time of Temp. of Temp. Rise from couple Reading Thermo- Corrected Number after Temp. couple Temp. for — of Motor Start before Rise Thermo. of Run Run Response inches See. °F °F AT AT. * 2 21 150 68 82 99 30 3 27 201 72 129 15 36 ‘5 28 155 72 83 92 he 6 29 122 72 50 D5 Lg 7 30 106 72 yn 37 5h 9 32 93 72 21 23 60 10 33 82 72 10 11 66 11 3h 78 72 6 6 7e 13 39 78 72 6 6 78 uy ho 76 72 4 y 8h, 15 a 76 72 in hy & REMOTE PITOT TEMPERATURE TABLE Wd TEMPERATURE SURVEY Run #98 Duration of Run 15.6 sec. Motor M293 Fuel FUOH Oxidizer 90% WFNA & 10% H»50 Mixture Ratio 2.10 Distance Aft of Motor 22 ft. Distance | Thermo- | Time of Temp. of Temp.Rise from couple Reading Thermo- Corrected Number after Temp. couple Temp. for of Motor Start before Rise Thermo. of Run Run Response inches Sec. F °F AT AT? 36 5 17 280 76 20k 262 ha 6 26 221 76 wh5 163 Lé 7 27 186 76 110 123 at 9 51 136 76 60 65 56 10 32 116 76 ho 13 60 1l 33 101 76 25 27 65 13 lo 90 76 1h 15 70 iy WL 80 7h 6 6 75 15 2 78 76 2 2 Run #89 Fuel FUOH TABLE WL a TEMPERATURE SURVEY Duration of Run 111.4 sec. - Oxidizer WFNA Motor M-+294 Mixture Ratio 1.7 Distance Art of Nozzle 19 ft. Distance | Thermo- Time of Temp. of Temp. Rise from coup le Reading Thermo- Corrected of Motor Number Stet Tome before aise Thermo. of Run Run Response inches Sec. oe" oe AT At. 30 3% 18 270 8h. 186 236 36 5 21 191 85 106 128 hie 6 22 wyh 85 59 70 Le 7 25 1h 85 29 3h 5h 9 26 9h 8h; 10 LL 60 10 28 88 8h, in ky 66 11 29 86 8h. 2 2 72 13 30 86 8h, 2 2 78 Ly 31 85 8h, 1 1 8h 15 32 83 83 0 0 TABLE VI b TEMPERATURE SURVEY Run #90 Duration of Run 15,2 sec. Motor M-293 Fuel FUOH Oxidizer Mixture Ratio 1.73 Distance Aft of Nozzle 19 ft. Distance | Thermo- Time of Temp. of Temp. Risa from couple Reading Thermo-~ Corrected Number after Temp. couple Temp. for — of Motor Start before Rise Thermo. of Run Run Response inches Sec. 7 °F AT ATe 30 3 1D 277 73 20h, 267 %6 5 17 200 73 127 163 he 6 20 14h, 73 61 73 8 7 22 92 72 20 2k 5h, 9 25 Bh, 72 12 1h, 60 10 26. 83 72 11 12 66 11 27 82 73 9 10 72 13 29 81 72 9 10 78 Ly 30 81 72 9 10 8h. 15 41 80 72 8 9 * 2 49 236 6h. 172 179 * REMOTE PIToT TEMPERATURE TABLE YIoc TEMPERATURE SURVEY Run #91 Duration of Run U5 sec. Motor M-29% Fuel FUOH Oxidizer 90% WFNA 10% HoO Mixture Ratio 2.01 Distance Aft of Nozzle 19 ft, Distance| Thermo- Time of Temp. of Temp. Ris¢ from couple Reading Thermo- Corrected ¢ Kumb er after Temp. couple Temp. for | of Motor Start before Rise Thermo, of Run Run Response inches Sec. of oe AT AT. #18 2 21 97 72 22 26 30 3 23 230 77 153 178 36 5 26 158 77 81 91 he 6 30 109 77 3e 35 k8 7 1 90 77 7) 14 5h 9 33 87 77 10 11 60 10 au, 87 77 10 11 66 11 36 87 77 10 11 72 13 Lo 86 76 10 10 78 1h yn 86 76 10 10 8h, 15 2 86 76 10 10 L_ “Distance aft of Motor ly in. Run #97 Fuel FUOH TABLE WL d TEMPERATURE SURVEY Duration of Run ll).6 sec. Oxidizer 90% WFNA & 10% Hoo Motor M~293 Mixture Ratio 2.19 Distance Aft of Motor 19 ft. Distance Thermo- Time of Temp. of Temp.Rise from couple Reading Thermo- Corrected Number after Temp. couple Temp. for — of Motor Start before Rise Thermo, of Run Run Response inches Sec. °F °F AT AT. 33 p) 30 285 88 197 216 28 6 42 217 88 129 139 43 7 34, 155 87 68 72 18 9 36 121 86 35 37 53 10 47 97 86 11 12 57 1 39 91 86 5 5 62 13 hi 87 86 1 1 TABLE WIL a TEMPERATURE SURVEY AN Run #92 Duration of Run 5 sec. Motor M29 Fuel FUOH Oxidizer 90% WFNA & 10% Hp0 Mixture Ratio 2.20 Distance Aft of Motor 16 ft. Distance | Thermo- Time of Temp. of Temp. Risa from couple Reading Thermo- Corrected Numb er after Temp. couple Temp. for — of Motor Start before Rise Thermo. ; of Run Run Response inches Sec. OF CF AT AT; 30 z 28 256 90 166 185 36 5 32 186 89 97 lok, he 6 3h, 122 91 31 33 L8 7 oy) 98 89 9 5h 9 39 9h, 88 6 60 10 ko 93 89 h \y 66 1 Li 93 89 in in 72 13 he 92 88 L, Ly 78 Lb L3 92 88 Ly mn 8h 15 Lh 91 88 3 3 TABLE VIL b TEMPERATURE SURVEY Run #93 Duration of Run Ll.7 sec. Motor M-293 Fuel FUOH Oxidizer 90% WFNA & 10% Ho0 Mixture Ratio 2.17 Distance Aft of Motor 16 ft. Distance | Thermo- Time of Temp. of ffemp. Rise Prom couple Reading Thermo-~ corrected Number after Temp. couple Temp. for of Motor Start before Rise Thermo. of Run Run Response inches Sec. °F °F AT At; 72 13 16 96 97 -1 #1 78 1h, 17 96 97 -1 -1 8h 15 18 96 97 ~1 -1 30 3 al 215 98 117 13, 36 5 28 134, 98 36 ho he 6 29 105 98 7 8 L8 7 30 100 98 2 2 5h 9 3a 99 98 1 1 60 10 33 98 98 ) ) 66 11 3h, 98 98 @) ) Run #95 Fuel FUOH TABLE Wile TEMPERATURE SURVEY Duration of Run 5. sec. Oxidizer 90% WFNA & 10% Hp0 Motor M294 Mixture Ratio 1.73 Distance Aft of Mator 16 ft. Distance| Thermo- Time of Temp. of Temp. Ris¢ from couple Reading Thermo- Corrected Numb er after Temp. couple Temp. for of Motor Start before Rise Thermo. of Run Run Response inches Sec. °F °F AT ATe 30 3 el, 321 94 227 256 36 5 31 205 93 112 121 2 6 32 131 93 38 2 48 7 (33 112 9% 19 20 Bu ? 39 109 93 16 17 60 10 36 107 93 uy 15 66 11 37 105 93 12 1 72 13 Lo 10), 93 11 11 78 1h Pe 103 9h 9 9 8h, 15 he 99 94, y) y) Run #96 Fuel Oxidizer 90% WFPNA & 10% Hod FUOH TABLE VII da TEMPERATURE SURVEY Duration of Run L5.4 sec. Motor Distance Aft of Motor 16 ft, M-293 Mixture Ratio 2,01 Distance! Thermo- Time of Temp. of Temp,.Rise from couple Reading Thermo-=- Corrected Number after Temp. couple Temp. for | of Motor Start before Rise Thermo. of Run Run Response inche $s 5 ec. a OF AT AT, 3% 5 22 260 95 165 195 38 6 e7 179 9h, 85 95 8 7 29 119 9h, 25 27 23 9 31 102 9h, 8 9 57 10 42 100 9h 6 6 62 12 33 96 93 3 3 67 oy) 37 oh 91 y 3 r Te uy 38 9b 91 3 3 F 77 15 39 93 91 2 2 TABLE WIL a TEMPERATURE SURVEY Run #99 Duration of Run U5 sec. Motor M-29%3 Fuel FUOH Oxidizer 90% WFNA & 10% H,0 Mixture Ratio 1.2) Distance from € © 2)" Distance Thermo- Time of Temp. of Temp.Rise Aft. couple Reading Thermo~ Corrected of Number a fter Temp. couple Temp. for | Motor Start before Rise Thermo. of Run Run Response inches Sec. CF °F AT AT, 33 9 in 110 52 68 19h, 27 10 5 100 63 37 92 21 11 6 86 61 25 5h 15 13 8 8h 6h, 20 36 9 1h 9 8h 66 18 31 3 15 10 82 66 16 26 51 5 42 2ho 62 278 299 Run #100 Fuel FUOH TABLE VIIT pb TEMPERATURE SURVEY Duration of Run 59.9 sec. Oxidizer 90% WFNA & 10% Hoo Motor M-294 Mixture Ratio 2.78 Distance from ¢ of Motor 36" Distance | Thermo- | Time of Temp. of Temp.Rise Aft couple Reading Thermo~ Corrected uotor | | Stare | | berore | Rise | Thermo. of Run Run Response inches See. °F °F AT Ate 61 2 50 115 60 55 55 55 4 51 86 60 26 26 ai y) oy) 96 29 39 39 k5 6 56 98 29 37 37 39 7 at 99 58 37 37 15 9 60 88 59 37 29 27 10 ho ge 29 33 3h 21 11 2 91 59 32 33 oy) 15 uh 96 29 29 38 9 1 L5 8h, 59 25 26 3 15 L6é 80 59 21 21 | TABLE IX VELOCITY SURVEY Distance Art of Motor 2.5 ft. Distance gAlcohol Ambient Direct | Speed from Temp. |(inches| Run Air with with ion of of of Number Temp. | rack rack of flow Motor Alcohol) to of| at flow Motor 470 inches OF inches OF H/ere | #/f£t© Degrees | ft/sec 40 65 1.32 98 76 (7.6)% | 5.h2 2xx | 69.0 3h, 69 1.32 83 62 5.4 | 35 65 0.95 98 76 (h.7) 9290 6 6.5 ho 69 0.61 83 62 2.5 | ho 65 0.35 | 98 76 | (2.5) | Leb 3 L6.9 6 69 0.12 83 62 0.9 . h5 65 o.1h 98 76 (0.70) | 0.58 6 2.6 52 69 0.01 | 83 62 0.04 . ke) 65 0.07 98 76 (0.10) | 0.29 6 9.4, * () ux Degrees are positive when flow is toward Numbers derived from data not in () in this colum. of Motor. TABLE X VELOCITY SURVEY Distance Aft of Motor 22 ft. DistancéAlcohol Ambient Direct | Speed from Temp. |(inches] Run Air with with ion of of of |Number | Temp. rack rack of flow Motor Alcohol) to of at, flow Motor 37 inches| OF inches oF |#/ete | #/rt? | degrees! ft/sed 30 65 1.98 86 6l, 8.14 (6.6) ~50 85.3 32 75 1.31 97 86 | 5 3h 36 65 0.74 86 6h, 3.0, | (1.9) +2 52.1 38 75 0.29 97 86 | 1.2 . 2 65 0.14 86 6, 0.58 | (0.60) | 22 23.6 Lb 75 0.10 97 86 | 0.41 L8 65 0.00) 86 on 0.016 | (0.05) | 6 6.7 50 75 0.003 97 86 0.012 TABLE XI VELOCITY SURVEY Distance Aft of Motor 19 ft. Distanc¢ from Alcohol|(inches| Run | Ambient with | Direct | Speed Xe) Temp. of Number Air rack ion of Motor Alcohol Temp. at of Plow 37° flow inches| °F inches oF tee degrees] ft/sec 24 66 342 90 72 23 82 0,63 96 2.56 -11° 221 29 66 1,03 90 72 29 82 0.32 96 1.3 -10° 125 TABLE XII VELOCITY SURVEY Distance Aft of Motor 16 ft. Distance ; from lcoholf{inches | Run [Ambient | with with |Direct Speed of Temp. of Number Air rack rack ion of Motor Alcohol) Temp. |to of at of flow Motor 47° flow inches op inches oF #/et’ | #/ete | degrees ft/sec 23 75 2.5 92 89 10.2 23 82 3.4 | 95 93 13.8 | 35° 11h 29 75 0.61 92 89 2.5 29 82 0.8 95 93 3.41] 35° 57 FIGURE | TES | PIT (Looking toward motor) FIGURE 2 TEST Bly ; (Looking aft from motor. Rack in right foreground. ) Ae dIngert wires into porcelein Sucloces tu i° Twist wires ag shown in the enlarged ciarras and braze, walsine @ smell bead of metal whish mey be blackened with soot. Vier x ist the wires as shown but cub So wires cross oly once. oo 6 w am Silver solder this junction, ‘3 ae , G. ith either method { yor Be )} the finished thermocouple will be as follows: | i ~. ia _ > 4 FIGURE BROWN POTENTIOMETER 5 FIGURE RACK Pitot tube (a) Prandtl Thermocouple (bd) Stagnation temperature probe (c ) vb ge , Walp I ~K iy ? ACHP TIS PF] i FD : © See pepe IG Od so Sepeareys SE Pi, f paays STAs G-Bl HK : ) ¥ + . . \ 2 | bai f PAS FS AEDS S-c/. / Y BP ANGIOWHSAHL Gea aHS od Q BHM! i a ae eds Te et eaten aaa vee! i ; i \ { a ne i | “Ve i Pek os je | sma ane donate, we tes ae, noma 4 Ki i Ly sneer Sr 3 ne, : Se aed ‘ x ; ~ . detnetncnens an ee ee ee ec AIAOHO AALAWOHAd TWWOLLdo ‘ON ONIMVEO Luv 4HOISM “MDI Aq P r NOILVDISISSV1D LOaroudd NOIMoas NOILYNDISA GaLON ASIMYSHLO SSSAINN O1O SONVYa10L aiva waiiat ADOTONHOFL JO FLALILSMI VINUOAITYO NOlidiv¥5S30 LID1VD ‘AWOLVHOGYT NOISTNdOUd 13 — = soy. AD GAaBNOD YY 30 ve ony & ee 3 Se wy ine). iy Snes Ff Sawada 3 ae ‘ a = soe Snme : : wr = : ; 1-8 APs sash ee = om = ove NL “A a" See a anh eee ei ee Badciv Wiza — wd ene oe ove 15a NOILDaS 725 }\ NOLLVYNOISAG LoSroud — ~~ ssw ed | as eee TIO1WS “AMOLWUONVT WOISTRAOd a| 2212v SecomD BN ~a hss sue NI GOW YS ee ge ( a eyo iSv4 ee a ; S : B90 oo Ne 2 cu & 77K ee ee i) ay Wee SSIMUID ssayun Wid Ves FQSy — ee se | [1 jones 39m. Bids oD wid § «FON tor S Sa. Be OS { Baer ayim-ssminvs vid as \4/ aN ‘ = Ss ; d a nee wees SEAR wet A lege Pesce R |, | SON 1 Wows Zon. asad vid 2h NS os yo ON eae ches Bete ce aX] ana vi | ¢ 1aas Vid Vas: SS MX eos BARS Spee enema CS aaa aaa Bese Pet i Mas § | { . } { SA IS i y Vy Inicd 1 g s es : oa . ——— ‘ f = Saree | ht Ry ae HISOWS GHY AaTICS i q HALIM ASAT WIS ‘ tage ts eS aad S\'o ; : { (SNilwid Sugano 7 a } pees NAY me Assy hiac ey } Woad Inaiced) eo * | Ve Ea S| om 2 ee egy Soy ee eo 7h Ry AAeniassy asia HSIed xdaddy ia HLOOWS TO. 1S 20 AY Malay Sina x 5 \ ‘Wadd SVS SsZi'c = ‘ fp . ) 4 ON SNIMVHO *mo] Aq p F wy eSouordsy ; + NOMVoIsISSV1> Loaroud ABOTONHOIL 40 FIMLIISNI VINHOSIIVO NOILDAS > NOILYND5ISad Loaroud SONVHD 43137 LIQTWS AWOLVYORVT NOISTNdOUd Lar NOIlLdiaDsag pajoy ISIMUBYIO SSaIUN [O° = JONVESTIOSL ANIMeg NOWVDISISSVID 1LDSrOud LIDTVO—-NdPr . FIGURE (1 TILTING MULTIPLE MANOMETER (in the 14.5 ° position) FIGURE 2 REMOTE CONTROLLED PITOT TUBE (Assembled ) FIGURE 12 REMOTE CONTROLLED PITOT TUBE (Disassembled) (a) Aluminum shield (d) Pitot tube (b) Rubber tubes (e) Motor (¢) Synchro (f) Adjustable support aoc%§$ca FIGURE |4 SYNCHRO CONTROL Rectifier (220 a.c. to 244d.c.) Inverter (24dc. to !11|0a¢c.400~) Amplifier Synchro i id a Srget Control Synchre slave Syrshro| \ Oa d 2a Motor i 4007 } | ey Sys. ‘ panies, ‘aectesagmiene 7 seats, sonra Sanit SRIRRREIEK 4A A aI amen “A AL Aan 1 ck ARS tad 5 I ee wmreneae desneenr — { q | ; A A ROE NA NS Ha oc, MOQ FIGURE «5 Electrical Gireuit Por The fg tee : ae a ‘ ra) wha tic iia OF 16 FIGURE INCLINED MANOMETER SMALL : ‘ : i i : i oO 5 >. << t : H | (inches) | z:(@) SURVEY eras s (@) : : a ! =O} ! S ; Ue Sophos cb ab pao pcb opps pc: Ja Dod one aj Sbophrpiiiti pbowrubs vrdivtibniviiccybosnrprir: : _ > Bo otporpit boodbsscboccbes fb cnstt desc cunpciske. cbocuberikeocckiosdoss bevesbeocnpocndbe . ant Zz 3 an ce ~~ pits APM : “ Hepp : ann oe a a o ° re LS En cl wo . oR 3 . Saeeene Dene fs iene teee bine beet gr ae feces 2 nebece ? gg) BH | I i i cueene OB great Ol aes a 1g | (a we a ! ob ini Cereal oe obo NE to & = 8 a Li-DISTAN - 20 | RADIA SF had LOD. 30 3656. Zou 5OH0 a EL : an oan C- { a : : eeceen poner eb a | aa Rane na rn bo Oo > aie 2. pee 7 _ Fe i NCE TOT UTTESEET RaCESET GUIDE! MDE OSI ea i pots t ad — a pet me a Phe , (oa ae ' a: Beem enmins ence ho ne: ones ec Ck dee cintnbes peep: _ an oe os | : =e co) nae 3 oo ns ae Ou bE Oe . coe a ee Led i a PO ge pat = oO my: : ; 7 i mets n— eoaeeee QO } a ou ~ ‘ pe as) ‘al = ~ : - - ae. a : § a : aa aed Py Pan ee ee Oe Oe Cs ee ee _ Me vid 7 ; : pen ppb pes pro Pr oe pn “Tf ow a a mange bok AL aon \ | as | Senne) Ceres Oe ee ae : / : a Q nom ~ [i en cr rs Oo a er, ee PY PEO aca go amen H : i : ‘ i |: : _ SO COS CASE COS OE OS on are in —_ * iy - q i i “2 pos ig WO og Pr on. : OQ: : po pe 8 _. a : ee Pbposb ly poicbas shes Oo : a o. a Doo) EQ - yo}. whee meu ge libs ao uk. Pon aM ot: TS ob: * ens a oo ee 4 i ce coca a a . nN a &. as - Qo. . : eh alt Map eb ot boven pons Poop. 4 we Yn OO 2ez ze pe ~-| 5 : us 4 pa i= ye reads Cs beeen Core Os Se DO ns ee oot obese Bp pe ee be re coe tee pa oO Ls. eo : eee Caen ee gpd : " : : piniie: + * : x coeur - BM fe : oe ere co ad a: Mie adeel oe oa reeeen eens cae eerenueeceens seet cree aes ean . es Senne oo 4 - * — 49 ip) gi re Sere eee CO Oe Se Oe Se Oe Oe Rs ed Oe OOS OE OEE Cee ao : i v . wo . - —— oo - neon : - ~ ce ben a |... oO a aa ! Se en 4 vee Le 7 ~4 ol an anne - _ " > oy - | ee nee : oo SBI BUOUNESdN SL Yeo id ow; i H i i geeton eect eae oe + emai t SEP EEE ; ; 4 - r i can + pote dehy im oe ero ecco ‘tt ; F ne i ‘a + E 4 pie} 7 4 : 2 1 aan " x : a 4 ¢ 3 ia} eames i: amen + i } + of 4 + $ : - i