A parametric study of the leading edge attachment line for the F-16XLA three-dimensional Navier-Stokes code is used to computationally simulate the flow about a modified F-16XL. Transition mechanisms (e.g. attachment line location and crossflow instability) near the swept wing leading edge are analyzed in detail. Flow visualization is used to study the influence of angle-of-attack on the aforementioned transition mechanisms. Validation of the code is accomplished by comparison of numerically generated surface pressures with that obtained by in-flight experiments.
Document ID
19910058932
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Flores, Jolen (NASA Ames Research Center Moffett Field, CA, United States)
Tu, Eugene (NASA Ames Research Center Moffett Field, CA, United States)
Anderson, Bianca (NASA Ames Research Center Moffett Field, CA, United States)
Landers, Stephen (NASA Flight Research Center Edwards, CA, United States)