1994 年 42 巻 487 号 p. 503-509
Radiative heat transfer from the strong shock layer generated around a hypersonic flight model is experimentally investigated by using a ballistic range (two-stage light-gas gun). A plastic projectile of 1.2cm diameter is accelerated in this facility up to 5.3km/s (M=15), and the radiation spectra and global power emission from the projectile are measured. As a result, radiation spectra from some carbon-containing molecules such as CN and CO, were observed along with the air spectra, and the radiative heat transfer rate was estimated. Since the projectile launched in a ballistic range is two orders of magnitude smaller than the actual space vehicles, the model-dimension effect on shock layer structure is examined by analytical and numerical considerations, and a scaling law has been developed. Radiative heat transfer rate around a projectile was calculated, and the validity of conventional numerical model is discussed by comparing the computed result with the measured one.