Numerical study of the effect of tangential leading edge blowing on delta wing vortical flowA numerical simulation of tangential blowing along the leading edge of a delta wing is analyzed as a means of controlling the position and strength of the leading-edge vortices. The computation is done by numerical solutions of the three-dimensional thin-layer Navier-Stokes equations. Numerical results are shown to compare favorably with experimental measurements. It is found that the use of tangential leading-edge blowing at low to moderate angles of attack tends to reduce the pressure peaks associated with leading-edge vortices and to increase the suction peak around the leading edge, such that the integrated value of the surface pressure remains about the same.
Document ID
19890037917
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Yeh, David T. (Stanford Univ. CA, United States)
Tavella, Domingo A. (Stanford Univ. CA, United States)
Roberts, Leonard (Stanford University CA, United States)