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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Transonic analysis of the F-16A with under-wing fuel tanks - An application of the TranAir full-potential code


    Contributors:

    Publication date :

    1987-06-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    CST Transonic Optimization Using Tranair++

    Bogue, David / Crist, Nick | AIAA | 2008


    Application of the TranAir full-potential code to the F-16A

    Erickson, L. L. / Madson, M. D. / Woo, A. C. | NTRS | 1987


    CST Transonic Optimization Using Tranair++

    Bogue, D. / Crist, N. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2008



    TRANAIR - A computer code for transonic analyses of arbitrary configurations

    SAMANT, S. / BUSSOLETTI, J. / JOHNSON, F. et al. | AIAA | 1987