Higherorder accurate calculations of the compressible boundary layers on a prolate spheroid
Abstract
A higherorder accurate finitedifference procedure is used to compute the compressible boundary layers over fuselagetype configurations, in particular, a prolate spheroid. The firstorder boundary layer theory is used and twopoint compact scheme with a fourthorder accuracy is used to solve the governing equations in transformed coordinates. The accuracy of the present method has been checked for well known documented test cases. Then, the subsonic viscous flowfields of prolate spheroid is computed. The inviscid flow solution is obtained numerically. It is found that the present calculations are with a fourthorder accuracy, and stable. Therefore, it is desirable to use the present higherorder numerical method in the stability analysis of laminar flows or in the viscous/inviscid interacting procedures. Also, it is advised to use the secondorder boundary layer theory to account for the pressure gradient across the boundary layer.
 Publication:

AIAA, ASME, SIAM, and APS, National Fluid Dynamics Congress
 Pub Date:
 1988
 Bibcode:
 1988aiaa.conf..893R
 Keywords:

 Compressible Boundary Layer;
 Finite Difference Theory;
 Flow Distribution;
 Inviscid Flow;
 Laminar Flow;
 Prolate Spheroids;
 Boundary Layer Equations;
 Computational Fluid Dynamics;
 Cross Flow;
 Pressure Gradients;
 Reynolds Number;
 Shear Stress;
 Skin Friction;
 Fluid Mechanics and Heat Transfer