The thermal regime of a 12-inch diameter liquid rocket motor, while carried by F4B and A6A aircraft, is investigated. Aerodynamic heating is measured during carriage by the F4B aircraft. Aerodynamic cooling is investigated during flights of up to 4 1/2 hours on A6A aircraft. The report includes figures which give the heating and cooling profiles, and tables. (Author)
Aerodynamic Heating and Cooling Temperature Criteria Determination for Air-Launched Liquid Rocket Motors
1969
47 pages
Report
No indication
English
Rocket Engines & Motors , Physics , Missile Technology , Aircraft , Naval aircraft , Air to surface missiles , Liquid propellant rocket engines , Thermal analysis , Aerodynamic heating , Cooling , Tables(Data) , Flight testing , External stores , Meteorological phenomena , Jet fighters , Attack bombers , Jet bombers , Aerodynamic cooling , A-6a aircraft , A-6 aircraft , Bullpup missiles , F-4 aircraft , F-4b aircraft
Rocket Motors for Ground-Launched Munitions
British Library Conference Proceedings | 2000
|Engineering Index Backfile | 1962
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