Numerical solution of Space Shuttle Orbiter flowfield

The supersonic viscous laminar flow around the Space Shuttle Orbiter forebody has been computed with a parabolized Navier-Stokes code using a generalized coordinate transformation. The initial solution for the nose part of the Orbiter was obtained with a three-dimensional time-dependent Navier-Stokes solver. It was necessary to employ a wind-axis oriented coordinate system to obtain the initial solution with the time-dependent code. The generalized PNS technique was then used to march the solution downstream from the given initial data surface. An algebraic grid generation scheme was employed which accurately describes the body shape by clustering points at the wing tip and at the wing-body juncture. The computed heat-transfer coefficients, pressure coefficients, and shock shapes are compared with the available experimental data for 0 and 30 deg angle of attack.

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