@article{oai:nagoya.repo.nii.ac.jp:00030713,
 author = {Yasuhara, M. and Nakamura, Y. and Tsuboi, K. and Kuwabara, K.},
 issue = {2},
 journal = {Memoirs of the Faculty of Engineering, Nagoya University},
 month = {Mar},
 note = {First, analytical theory of high supersonic flow past basic slender bodies is described, for both paralell and source type flows. In the analysis, the flow field is divided into the inviscid shock layer and the viscous boundary layer. Second, simulations of flow by various methods of computational fluid dynamics (CFD), are described for basic bodies as well as complicated ones like winged bodies. Next, experiments performed by using the Mach 8 shock tunnel at the Nagoya University are described, especially for measuring pressure distributions, shock wave contours and force coefficients. It is shown that, as a whole, theoretical results give good comparisons with experimental ones. Also shown are that, in some cases the simulations by the CFD can proceed beyond analytical method where analyses can not prescribe the flow natures. Nevertheless, it is shown that, presently, the CFD simulations are not yet complete, and some of analytical approaches can give more informations about the flow nature, and further, experimental verifications are always important.},
 pages = {290--359},
 title = {Theory and shock tunnel experiments on flow past hypersonic vehicles},
 volume = {42},
 year = {1991}
}