A computational study of incipient leading-edge separation on a 65-deg delta wing at M = 1.60A computational study on a 65-deg delta wing at a freestream Mach number of 1.60 has been conducted by obtaining conical Reynolds-averaged Navier-Stokes solutions on a parametric series of geometries which varied in leading-edge radius and/or circular-arc camber. The computational results showed that increasing leading-edge radius or camber can delay the onset of leading-edge separation on the leeside of a delta wing at a specific angle of attack. Reynolds number was varied from 1 x 10 to the 6th to 5 x 10 to the 6th for a turbulent boundary-layer and was shown to have a minor effect on the effectiveness of leading-edge radius and/or camber in delaying the onset of leading-edge separation. Both laminar and turbulent boundary-layer models were investigated at a Reynolds number of 1 x 10 to the 6th, and the predicted flow pattern was found to change from attached flow for the turbulent boundary-layer model to separated flow for the laminar boundary-layer model. Based upon these results, three wind-tunnel models have been designed to be tested in the Langley Unitary Plan Wind Tunnel.
Document ID
19900058816
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mcmillin, S. Naomi (NASA Langley Research Center Hampton, VA, United States)
Pittman, James L. (NASA Langley Research Center Hampton, VA, United States)
Thomas, James L. (NASA Langley Research Center Hampton, VA, United States)