The results of an analysis of the motion and heating during atmospheric reentry of manned space vehicles has shown the following: 1. Flight-corridor depths which allow reentry in a single pass decrease rapidly as the reentry speed increases if the maximum deceleration is limited to 10 g. 2. Use of aerodynamic lift can result in a three-to five fold increase in corridor depth over that available to a ballistic vehicle for the same deceleration limits. 3. Use of aerodynamic lift to widen these reentry corridors causes a heating penalty which becomes severe for values of the lift-drag ratio greater than unity for constant lift-drag entry. 4. In the region of most intense convective heating the inviscid flow is generally in chemical equilibrium but the boundary-layer flows are out of equilibrium. Heating rates for the nonequilibrium boundary layer are generally lower than for the corresponding equilibrium case. 5. Radiative heating from the hot gas trapped between the shock wave and the body stagnation region may be as severe as the convective heating and unfortunately occurs at approximately the same time in the flight.
Motion and Heating During Atmosphere Reentry of Space Vehicles
1960
20 pages
Report
No indication
English
Unmanned Spacecraft , Manned Spacecraft , Aerodynamic heating , Reentry effects , Reentry vehicles , Manned spacecraft , Convective heat transfer , Atmospheric entry , Stagnation point , Shock waves , Lift drag ratio , Inviscid flow , High temperature gases , Deceleration , Chemical equilibrium , Boundary layers
Motion and heating during atmosphere reentry of space vehicles
Engineering Index Backfile | 1960
|Motion and heating during atmosphere reentry of space vehicles
TIBKAT | 1960
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