A computational/experimental study of the flow around a body of revolution at angle of attack
Abstract
The incompressible NavierStokes equations are numerically solved for steady flow around an ogivecylinder (fineness ration 4.5) at angle of attack. The threedimensional vortical flow is investigated with emphasis on the tip and the near wake region. The implicit, finitedifference computation is performed on the CRAY XMP computer using the method of pseudocompressibility. Comparisons of computational results with results of a companion towing tank experiment are presented for two symmetric leeside flow cases of moderate angles of attack. The topology of the flow is discussed and conclusions are drawn concerning the growth and stability of the primary vortices.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 September 1986
 Bibcode:
 1986STIN...9011254Z
 Keywords:

 Angle Of Attack;
 Bodies Of Revolution;
 Cylindrical Bodies;
 Flow Characteristics;
 Three Dimensional Flow;
 Vortices;
 Aerodynamic Characteristics;
 Flow Equations;
 NavierStokes Equation;
 Fluid Mechanics and Heat Transfer