A comparative study of the parabolized Navier-Stokes code using various grid-generation techniques

• Published in: Computers & fluids Vol. 13; no. 4; pp. 421 - 441
• Main Authors: kaul, Upender K., chaussee, Denny S.
• Format: Journal Article
• Language: English
• Published: Legacy CDMS Elsevier Ltd 1985; Elsevier Science
• Subjects: Aerodynamics; Applied fluid mechanics; Exact sciences and technology; Fluid dynamics; Fundamental areas of phenomenology (including applications); Physics; Shock layer; Navier Stokes equation; Digital simulation; Aeronautics; Aerodynamics; Hypersonic flow; Flow field
• ISSN: 0045-7930; 1879-0747
• DOI: 10.1016/0045-7930(85)90012-X

The parabolized Navier-Stokes (PNS) equations are used to calculate the flow-field characteristics about the hypersonic research aircraft X-24C. A comparison of the results obtained using elliptic, hyperbolic and algebraic grid generators is presented. The outer bow shock is treated as a sharp discontinuity, and the discontinuities within the shock layer are captured. Surface pressures and heat-transfer results at angles of attack of 6° and 20°, obtained using the three grid generators, are compared. The PNS equations are marched downstream over the body in both Cartesian and cylindrical base coordinate systems, and the results are compared. A robust marching procedure is demonstrated by successfully using large marching-step size with the implicit shock fitting procedure. A correlation is found between the marching-step size. Reynolds number and the angle of attack at fixed values of smoothing and stability coefficients for the marching scheme.