Initial results obtained using the TranAir transonic full-potential code are presented for a fully configured F-16A geometry, including two 370-gal under-wing fuel tanks, at freestream Mach numbers of 0.6 and 0.9 and angle of attack of 4 deg. The geometry is modeled using surface panels, and the flow field is defined by a rectangular array of flow-field grid points. The paneled geometry is embedded within this rectangular flow field. By avoiding the use of surface-conforming flow-field grids, the modeling generality afforded by surface panels can be utilized to analyze very complex configurations in the transonic flow regime.
Transonic analysis of the F-16A with under-wing fuel tanks - An application of the TranAir full-potential code
1987-06-01
Conference paper
No indication
English
CST Transonic Optimization Using Tranair++
AIAA | 2008
|CST Transonic Optimization Using Tranair++
British Library Conference Proceedings | 2008
|