A concept to obtain shock-free transonic flow for design aerodynamics of aircraft and turbomachinery is outlined. The method of elliptic continuation or method of fictitious gas represents a starting point for operational computational procedures to obtain supercritical airfoils and wings. Design examples illustrate the value of shock-free configurations for aerodynamic efficiency enhancement. The application of supercritical flow in aerodynamic concepts is mentioned.
Methods for Design Aerodynamics of Modern Transport Aircraft
1984
74 pages
Report
Keine Angabe
Englisch
Aerodynamics , Aircraft , Jet & Gas Turbine Engines , Aerodynamic configurations , Aircraft design , Cascade wind tunnels , Computer aided design , Supercritical flow , Transport aircraft , Wave front reconstruction , Airfoil profiles , Transonic flow , Turbomachinery , Two dimensional flow , Foreign technology
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