AIAA Entry Technology Conference, Williamsburg & Hampton, Va., October 12-14, 1964 |
Common terms and phrases
ablation altitude analysis angle applied approximately assumed atmosphere body boundary layer calculations char chemical coefficient cone considered constant convective decreases density determined distance distribution disturbance edge effect emission energy enthalpy entry equations equilibrium experimental experiments Figure flight flow flux ft/sec function gage given heat gage heat transfer higher hypersonic increases indicate integrated laminar limit loss lower Mach number Mars mass material maximum measurements method normal nose noted obtained parameter performance predicted present pressure profiles properties radiation radiative heating radius range ratio reference reflected region Reynolds number rotor shape shock layer shock wave shown shown in Fig smooth solution species speed stagnation point stream surface temperature theory thickness tion trajectory transition tube turbulent variation vehicle velocity wake wall weight