An Investigation of Wind Tunnel Wall Effects at High Mach Numbers

Authors: Leydon, John Koebig; Miller, Walter Bernard

Year: 1945

Degree: Engineer's thesis

Advisors: Liepmann, Hans Wolfgang; Puckett, Allen E.

Committee Member: Unknown, Unknown

Option: Aeronautics

DOI: 10.7907/HNBB-CK44

Abstract

This paper presents the results of an investigation of wind tunnel wall interference in a two-dimensional wind tunnel at high Mach numbers. The results are presented in the form of curves of lift coefficient versus the ratio of model chord to tunnel height, as functions of Mach number and angle of attack. The investigation was carried out by the authors at the Guggenheim Aeronautical Laboratory of the California Institute of Technology during the school year 1944-45.

Tests were carried out on the NACA low drag airfoil section 65,1-012 at Mach numbers from .60 to .80, and angles of attack of from 1 to 3 degrees. Models were 1", 2", 4" and 6" chord, giving values of the chord to tunnel height ration of .1 to .6. Schlieren photographs were made of shock waves where they occurred.

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