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ABORT SITUATIONS AND INITIAL ENTRY PARAMETERS
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adjacent heat exchanger aerodynamic coefficients aerodynamic shape aerodynamically stable side angle of attack angular velocities atmosphere entry bow shock conducting heat path configuration crossflow velocity vector dimensionless distributions were calculated end-on attitude End-on spinning entry heat pulse equation Dl exchanger during normal fuel capsule heat-source motion heating-rate distributions histories during launch-abort hypersonic speeds internal components Isoloaf initially spinning Isoloaf motion isotope heat source Kaattari km/sec method of reference mirror symmetry NASA nodal heating factor obtained Orbital decay peak heating Plutonium dioxide POCO graphite preferred orientation pressure distributions Pyrolytic graphite reference heating rate resultant angle-of-attack plane roll orientation shock wave shown in figure side-on attitude Side-on spinning Side-on stable single stable sonic points spinning end-on spinning side-on stagnation point stagnation-point velocity gradients steady-state operation Strength member superorbital entry superorbital velocities Tantalum thermal analyses thermal analysis thermal performance thermal requirements trajectory uninsulated side