A wind tunnel test program was evolved for obtaining experimental performance data on a mach 2.5, two-dimensional, external compression inlet typical of the IPS Tactical Fighter inlet. Tests were conducted at mach numbers of 0.6, 0.85, 0.95, 1.2, 1.3, 1.7 and 2.2. The investigation was intended to provide the data necessary to evaluate installation effects and to substantiate analytic methods of performance predictions. (Author)


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    Titel :

    Propulsion System Integration and Test Program (Steady State). Part IV. Inlet Drag Tests


    Beteiligte:
    T. J. Johnson (Autor:in) / J. H. Huff (Autor:in)

    Erscheinungsdatum :

    1969


    Format / Umfang :

    248 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch