Transonic solutions for a multielement airfoil using the full-potential equationTransonic flow solutions are obtained over a multielement airfoil (augmentor-wing) using the full-potential equation. Solutions obtained for a subcritical case and a strong shock case show good quantitative agreement with experiment in regions not dominated by viscous effects. In those regions where viscous effects are dominant, the results are still in good qualitative agreement. For the strong shock case, Mach number and angle-of-attack corrections were necessary to match experimental coefficient of lift. Typical results from the transonic augmentor-wing Potential Code on the Cray-1S computer require about 10 sec of CPU time for a three-order-of-magnitude drop in the maximum residual. The speed with which solutions can be generated, and the associated low cost, will make this code a practical tool for the design aerodynamicist.
Document ID
19840035220
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Flores, J. (NASA Ames Research Center Moffett Field, CA, United States)
Holst, T. L. (NASA Ames Research Center Moffett Field, CA, United States)
Sorenson, R. L. (NASA Ames Research Center Moffett Field, CA, United States)