Flow field around a finite cone with shock
flowfieldaroundf00mack.pdf (5.495Mb)Abstract
An experimental investigation was made to determine the characterization of the flow over the surface of a 70 degree 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 degree cone at zero angle of attack for five different free stream Mach numbers: 1.49, 1.830, 1.694, 1.86,1.997. It was found that theory gives close agreement with experimental results.
Description
This thesis document was issued under the authority of another institution, not NPS. At the time it was written, a copy was added to the NPS Library collection for reasons not now known. It has been included in the digital archive for its historical value to NPS. Not believed to be a CIVINS (Civilian Institutions) title.