@article{oai:jaxa.repo.nii.ac.jp:00034584,
 author = {OGUCHI, Hakuro},
 issue = {8},
 journal = {東京大學航空研究所報告, Report/Aeronautical Research Institute, University of Tokyo},
 month = {Nov},
 note = {This paper is concerned primarily with the problem of flow in which the viscous layer is so thick that the flow field behind the shock wave is no longer distinctly divided into the viscous and inviscid regions. A theoretical method is presented on the basis of the simplifying assumptions that the flow is incompressible downstream of the shock wave and furthermore the radial distance γ is nearly equal to the distance χ measured along the surface from the stagnation point. These simplifications may be considered to lead to good approximation, so far as the ratio between the densities ahead of and just behind the shock wave is sufficiently small and the field under consideration is restricted to the vicinity of the nose. Then the method yields the solution of the Navier-Stokes equations, both of conditions at the shock wave and on the surface being satisfied. Due to the method, however, the solution can be evaluated only by the numerical integration. The alternative method is presented, yielding an analytical expression of the solution, but being applicable only to the case where the Reynolds number is large. The results due to both methods were found very close to each other down to the lower Reynolds number than anticipated. The main results are summarized as follows : (1) There exists a similar solution consistent with the conditions both at the shock wave and on the body surface. (2) The surface pressure coefficient obeys the modified Newtonian law independently of the effect of viscosity. (3) The distance of the shock wave from the body increases with 1/√<R_c> (R_c : Reynolds number based on the uniform velocity and radius of curvaturs of the shock wave) and the rate of its increase becomes small as R_c decreases. (4) The skin friction increases almost linearly with 1/√<R_c>, at least, over the range of R_c where the present analysis may be applied., 資料番号: SA2404785000},
 pages = {189--209},
 title = {Hypersonic Flow Near the Forward Stagnation Point of a Blunt-Nosed Body of Revolution},
 volume = {24},
 year = {1958}
}