Generalised similarity solutions for three dimensional, laminar, steady compressible boundary layer flows on swept, profiled cylinders
Abstract
Solutions for the laminar, steady, compressible, three dimensional boundary layer equations for flows over swept wings are derived using the method of generalized similarity. The model configuration is that of an infinitely long, swept, profiled cylinder in an ideal gas flow whose dynamic viscosity is a linear function of temperature. The pressure distribution, Pr (Prandtl) and Ma (Mach) numbers, as well as the angle of sweep (beta) and the temperature (T) boundary condition can be chosen arbitrarily. A universal mathematical model which can be integrated numerically is derived. With reference to transonic swept wings, the numerical calculations are performed for values in the vicinity of Pr = 0.72, Ma = 0.82, beta = 21 degrees, T(sub w)/T(sub 0) = 0.98 (isothermal wall). The influences of variations in Ma number, angle of sweep and wall temperature on the characteristic boundary layer properties between the stagnation point and the separation point are presented.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 January 1991
 Bibcode:
 1991STIN...9120441S
 Keywords:

 Boundary Layer Equations;
 Compressible Boundary Layer;
 Compressible Flow;
 Laminar Flow;
 Similarity Theorem;
 Steady Flow;
 Three Dimensional Flow;
 Differential Equations;
 Mach Number;
 Numerical Integration;
 Prandtl Number;
 Swept Wings;
 Three Dimensional Models;
 Viscosity;
 Fluid Mechanics and Heat Transfer