NASA NTRS · 19900058792
Supersonic flow computations for an ASTOVL aircraft configuration
Abstract
A multi-zonal, unified, space/time marching method has been used to solve the Euler and Reynolds-averaged Navier-Stokes equations for supersonic flow past an Advanced Short Take-Off and Vertical Landing (ASTOVL) aircraft configuration. Lift, drag and pitching moment values obtained from the computations compare well with wind-tunnel measurements. The calculations demonstrate the capability of the method used to accurately predict design parameters such as lift, drag and pitching moment for very complex aircraft configurations.
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Ramakrishnan, S. V., Szema, K. Y., Chakravarthy, S. R., Bihari, B. L.. 1990-01-01. Supersonic flow computations for an ASTOVL aircraft configuration. https://ntrs.nasa.gov/citations/19900058792
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