Publication Date:
2019-06-27
Description:
A general method developed for the analysis of inviscid hypersonic shock layers is discussed for application to the case of the shuttle vehicle at high (65 deg) angle of attack. The associated extensive subsonic flow region caused convergence difficulties whose resolution is discussed. It is required that the solution be smoother than anticipated.
Keywords:
FLUID MECHANICS
Type:
NASA-CR-132453
,
MML-TR-74-5C
Format:
application/pdf
Permalink