Experimental study of compressible boundary layer on a cone at angles of attack
compressible boundary layer、hypersonic boundary layer、angle of attack、High frequency、wind tunnel、Mach number、model、different、study、means、end
25
O3(力学)
the Russian Foundation for Basic Research08-01-91956-NN10;ADTP RNP 2.1.1/3963 and Program RAS11/9
2009-08-27(万方平台首次上网日期,不代表论文的发表时间)
共9页
325-333