Transonic aerodynamic characteristics of the Viking entry and Lander configurations
Wind tunnel tests to determine aerodynamic characteristics of Viking spacecraft entry and lander configurations at transonic speed
Mc Ghee, R. J.↗
Engineering topics
Mc Ghee, R. J.
Publications and source records attributed to Mc Ghee, R. J..
Effects of a retronozzle located at the apex of a 140 deg blunt cone at Mach numbers of 3.00, 4.50, and 6.00
Effects of retronozzle located at apex of 140 deg blunt cone at Mach numbers of 3.00, 4.50, and 6.00
Mc Ghee, R. J.↗
Flow field resulting from forward-facing nozzles exhausting near a large cylindrical body at free-stream Mach numbers of 3.0, 4.5, and 6.0
Measurement of flow distribution caused by forward facing nozzles exhausting near large cylindrical body at hypersonic speed
Martin, J. A.↗
Jet-plume-induced flow separation on axisymmetric bodies at Mach numbers of 3.00, 4.50, and 6.00
Jet-plume-induced flow separation on asymmetric bodies at 3.00, 4.50, and 6.00 Mach numbers
Mc Ghee, R. J.↗
Abort separation including aerodynamic, dynamic, propulsive, and trajectory influences
Aerodynamic effects on safe abort separation for space shuttles
Decker, J. P.↗
Jet-plume-induced flow separation on a lifting entry body at Mach numbers from 4.00 to 6.00
Jet plume induced, flow separation on lifting entry model flat bottom by pressure distribution analysis
Mc Ghee, R. J.↗
Aerodynamic investigation of sharp cone- cylinder spikes on 120 degree blunted cones at Mach numbers of 3.00, 4.50, and 6.00
Aerodynamic investigation of sharp cone-cylinder spikes on 120 degree blunted cones at Mach numbers of 3, 4.5, and 6
Mc Ghee, R. J.↗
Exploratory investigation of flow field resulting from forward-facing nozzles exhausting near a large cylindrical body at free-stream Mach numbers of 3.0 and 6.0
Flow field from forward facing nozzles exhausting near large cylindrical body at free-stream Mach numbers of 3.0 and 6.0
Martin, J. A.↗
Effects of jet pluming on the static stability of five rocket models at Mach numbers of 4, 5 and 6 and static pressure ratios up to 26,000
Jet pluming effect on static stability of five cone cylinder-flare finned rocket models at Mach numbers of 4, 5, and 6 and static pressure ratios up to 26,000
ROCKET EXHAUST↗
Some effects of jet pluming on the static stability of ballistic bodies at a Mach number of 6.0
Effects of jet pluming on static stability of ballistic bodies at Mach number of 6.00
BALLISTIC VEHICLE↗
Effects of bluntness on the subsonic drag of an elliptical forebody
Effects of bluntness on subsonic drag of elliptical forebody
CYLINDRICAL AFTERBODY↗