A comparative study of the parabolized Navier-Stokes code using various grid-generation techniques
The parabolized Navier-Stokes 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 \(6\circ\) and 20\(\circ\), obtained using the three grid generators, are compared. The parabolized Navier-Stokes 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 sizes 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.
scientific article; zbMATH DE number 3936815