A concept to obtain shock free transonic flows for design aerodynamics of aircraft and turbomachinery is outlined. The method of elliptic continuation or method of fictitious gas represents a starting point for a number of operational computational procedures to obtain supercritical airfoil and wings. Design examples illustrate the value of shock free configuration for aerodynamic efficiency enhancement. The application of supercritical flow in aerodynamic concepts is mentioned.
Aerodynamic Design Methods for Modern Transport Aircraft
1985
82 pages
Report
No indication
English
Aerodynamic Design of Transport Aircraft
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