Flow Field Around a Finite Cone with Shock

Author: MacKinnon, Neil Allan

Year: 1949

Degree: Engineer's thesis

Advisors: Puckett, Allen E.; Nagamatsu, Henry T.

Committee Member: Unknown, Unknown

Option: Aeronautics

DOI: 10.7907/XR4M-9R51

Abstract

An experimental investigation was made to determine the characteristics of the flow over the surface of a 70° cone and at the shock wave for values near the detachment Mach number. The purpose of this investigation was to compare the experimental results obtained with theoretical values.

Tests were made in the GALCIT 2.5" Supersonic Wind Tunnel on a 70° cone at zero angle of attack for five different free stream Mach numbers: 1.49, 1.630, 1.694, 1.86, 1.997.

It was found that theory gives close agreement with experimental results.

This investigation was conducted jointly with Mr. Vincent Muirhead at the California Institute of Technology, Pasadena, California.

Files

• MacKinnon_na_1949.pdf (application/pdf)