At flight speeds above about Mach 2 cross-sectional area of fully-expanded jet nozzle tends to be larger than intake streamtube; principle of integrating this increase in area of propulsion unit with usable volume to reduce after-body drag of combination is discussed and calculations are made to establish order of effect; it is deduced that successful integration of this type can produce worthwhile increases in lift/drag ratio; pertinence to air-breathing engines.
Use of excess engine exit area over intake area to reduce zero-lift drag at high supersonic speeds
Aeronautical Qarterly
Aeronautical Quarterly ; 16 , Part 3
1965
15 pages
Aufsatz (Zeitschrift)
Englisch
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ZERO-LIFT WAVE DRAG CALCULATION USING SUPERSONIC AREA RULE AND ITS MODIFICATIONS
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|Reduction of Drag Due to Lift at Supersonic Speeds
NTIS | 1954
|Reduction of Drag Due to Lift at Supersonic Speeds
NTIS | 1954
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