Comparisons of calculated and experimental transonic unsteady pressures and airloads for four of the AGARD Two Dimensional Aeroelastic Configurations and for a rectangular supercritical wing are presented. The two dimensional computer code, XTRAN2L, implementing the transonic small perturbation equation was used to obtain results for: (1) pitching oscillations of the NACA 64A010A; NLR 7301 and NACA 0012 airfoils; (2) flap oscillations for the NACA 64A006 and NRL 7301 airfoils; and (3) transient ramping motions for the NACA 0012 airfoils. Results from the three dimensional code XTRAN3S are compared with data from a rectangular supercritical wing oscillating in pitch. These cases illustrate the conditions under which the transonic inviscid small perturbation equation provides reasonable predictions.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Experience with Transonic Unsteady Aerodynamic Calculations


    Contributors:
    J. W. Edwards (author) / S. R. Bland (author) / D. A. Seidel (author)

    Publication date :

    1984


    Size :

    23 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Experience with transonic unsteady aerodynamic calculations

    Edwards, J. W. / Bland, S. R. / Seidel, D. A. | NTRS | 1984


    Experience with transonic unsteady aerodynamic calculations

    Edwards, J. W. / Bland, S. R. / Seidel, D. A. | NTRS | 1985