Application of an upwind algorithm to the parabolized Navier-Stokes equations
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The Department of Aerospace Engineering seeks to instruct the design, analysis, testing, and operation of vehicles which operate in air, water, or space, including studies of aerodynamics, structure mechanics, propulsion, and the like.
History
The Department of Aerospace Engineering was organized as the Department of Aeronautical Engineering in 1942. Its name was changed to the Department of Aerospace Engineering in 1961. In 1990, the department absorbed the Department of Engineering Science and Mechanics and became the Department of Aerospace Engineering and Engineering Mechanics. In 2003 the name was changed back to the Department of Aerospace Engineering.
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1942-present
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- Department of Aerospace Engineering and Engineering Mechanics (1990-2003)
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- College of Engineering (parent college)
- Department of Engineering Science and Mechanics (merged with, 1990)
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Abstract
A new computer code for the solution of the three-dimensional parabolized Navier-Stokes (PNS) equations has been developed. The code employs a state-of-the-art upwind algorithm to capture strong shock waves. The algorithm developed in this work is implicit, uses finite-volumes, and is second-order accurate in the crossflow directions. The new code is validated through application to several laminar supersonic and hypersonic flows. In two dimensions, calculations were performed for supersonic laminar flow past a flat plate, hypersonic laminar flow past a 15(DEGREES) compression corner, and hypersonic laminar flow into a converging inlet. Results obtained using the present algorithm are in excellent agreement with experimental data as well as with previous numerical calculations. The method was validated for three-dimensional flow by computing hypersonic flows past two simple body shapes: a circular cone of 10(DEGREES) half-angle and a generic all-body hypersonic vehicle. Cone flow solutions were computed at angles of attack of 12(DEGREES), 20(DEGREES), and 24(DEGREES) and results are in agreement with experimental data. Results are also presented for the flow past the all-body vehicle at angles of incidence of 0(DEGREES) and 10(DEGREES).