Wind tunnel tests were conducted in a 14- inch wind tunnel with a 0.004 scale model of the space shuttle launch vehicle in order to (1) determine the cause and possible aerodynamic alterations required to eliminate the Orbiter rolling moment couple; (2) determine configuration alterations to alleviate the forward Orbiter external tank loads; and (3) provide data to verify previous data.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Results of Two Tests in the Msfc 14 by 14-Inch Trisonic Wind Tunnel, FA 27 (Twt-655) and FA 28 (Twt-656)


    Beteiligte:
    W. F. Braddock (Autor:in)

    Erscheinungsdatum :

    1979


    Format / Umfang :

    884 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch