Accession Number : ADA018715

Title :   Calculation of Three-Dimensional Supersonic Flow Fields about Aircraft Fuselages and Wings at General Angle of Attack,


Personal Author(s) : Chu,Chong-Wei

Report Date : MAR 1973

Pagination or Media Count : 32

Abstract : A new algorithm for the three-dimensional method of characteristics is applied to the calculation of steady inviscid supersonic flow about aircraft fuselages and wings at general angle of attack. After a brief discussion of the new method, computed results of flow over an elliptic cone and a blunt circular cone at angles of attack are presented and compared with available experimental data. Good agreement is observed. Application to fuselage flow field calculation then follows. Calculated examples of flow about typical fuselages under different flight conditions are presented, discussed, and compared with available experimental data with good agreement. Finally, the computed pressure distribution on a thin wing (an elliptic cone of 20:1 axis ratio) is presented and discussed. The present method can be used to obtain flow field information for aircraft design or to provide inviscid solutions for boundary layer analysis. (Author)

Descriptors :   *Supersonic flow, *Fuselages, Wings, Wing body configurations, Three dimensional flow, Flow fields, Angle of attack, Inviscid flow, Blunt bodies, Conical bodies, Boundary layer flow, Pressure distribution, Numerical analysis

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE