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Assessment of NASA and RAE viscous-inviscid interaction methods for predicting transonic flow over nozzle afterbodiesThe Langley Research Center of the National Aeronautics and Space Administration and the Royal Aircraft Establishment have undertaken a cooperative program to conduct an assessment of their patched viscous-inviscid interaction methods for predicting the transonic flow over nozzle afterbodies. The assessment was made by comparing the predictions of the two methods with experimental pressure distributions and boattail pressure drag for several convergent circular-arc nozzle configurations. Comparisons of the predictions of the two methods with the experimental data showed that both methods provided good predictions of the flow characteristics of nozzles with attached boundary layer flow. The RAE method also provided reasonable predictions of the pressure distributions and drag for the nozzles investigated that had separated boundary layers. The NASA method provided good predictions of the pressure distribution on separated flow nozzles that had relatively thin boundary layers. However, the NASA method was in poor agreement with experiment for separated nozzles with thick boundary layers due primarily to deficiencies in the method used to predict the separation location.
Document ID
Document Type
Conference Paper
Putnam, L. E.
(NASA Langley Research Center Transonic Aerodynamics Div., Hampton, VA, United States)
Hodges, J.
(Royal Aircraft Establishment Aerodynamics Dept., Bedford, United Kingdom)
Date Acquired
August 11, 2013
Publication Date
July 1, 1983
Subject Category
Report/Patent Number
AIAA PAPER 83-1789
Distribution Limits
No Preview Available