In support of NASA s Space Launch Initiative Program, stage separation wind tunnel tests of a generic two-stage-to-orbit (TSTO) launch vehicle were conducted to determine the interference aerodynamic forces and moments and to determine the proximity flow environment. The tests were conducted in the NASA Marshall Space Flight Center s Aerodynamic Research Facility using a manual separation fixture for a Mach number range of 2.74 to 4.96 and separation distances up to 80 percent and 35 percent of the body length in the vehicle X and Z coordinates, respectively. For the TSTO bimese, winged-body vehicle configuration, both wing-to-wing and wing-to-fuselage configurations were tested. Individual-body force and moment, schlieren, and surface pressure data were acquired. The results showed that the proximity aerodynamics were dominated by complex bow shock interactions, and that he booster was statically unstable at several separation positions. As compared to the isolated body, the proximity normal force change with pitch angle was found to be nearly the same, and the proximity axial force increased, in general, by 3% for both bodies.


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    Title :

    Stage Separation Wind Tunnel Tests of a Generic Two-Stage-to-Orbit Launch Vehicle


    Contributors:
    W. J. Bordelon (author) / A. L. Frost (author) / D. K. Reed (author)

    Publication date :

    2003


    Size :

    11 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Stage Separation Wind Tunnel Tests of a Generic Two-Stage-to-Orbit Launch Vehicle

    Bordelon, Wayne J., Jr. / Frost, Alonzo L. / Reed, Darren K. | NTRS | 2003


    Stage Separation Wind Tunnel Tests of a Generic TSTO Launch Vehicle

    Bordelon, Wayne / Frost, Alonzo / Reed, Darren | AIAA | 2003


    AIAA-2003-4227 Stage Separation Wind Tunnel Tests of a Generic TSTO Launch Vehicle

    Bordelon, W. / Frost, A. / Reed, D. et al. | British Library Conference Proceedings | 2003