Inviscid Hypersonic Flow Over Unyawed Circular Cones

Abstract

R E F E R E N C E S 1 Charyk, Joseph V., (Ed.), Speed Aerodynamics and Jet Propulsion, Vol. IX, Part 1, Ladenburg, R. W., (Ed.), Physical Measurements in Gas Dynamics and Combustion, Eber, G. R., Shielded Thermocouples, pp. 186-197, Princeton University Press, 1954. 2 Goldstein, D. L., and Scherrer, R., Design and Calibration of a Total Temperature Probe for Use at Supersonic Speeds, NACA TN 1885, May, 1949. 3 Winkler, E. M., Stagnation Temperature Probes for Use at High Supersonic Speeds and Elevated Temperatures, Navord Report 3834, October, 1954. 4 Wood, R. D., An Experimental Investigation of Hypersonic Stagnation Temperature Probes, GALCIT Hypersonic Research Project Memorandum No. 50, July, 1959. If t h e f ree-s t ream M a c h n u m b e r is sufficiently h igh, t h e shock layer is t h i n a n d t h e n o r m a l ve loc i ty c o m p o n e n t v c an be expec t ed t o r e m a i n smal l w i th in t h e shock l aye r r e l a t i ve t o t h e local speed of sound . As a consequence , i t a p p e a r s r e a s o n a b l e t o neglec t v/a in compar i son t o one . W i t h t h i s a s s u m p t i o n , E q . (1) becomes