Flight tests were conducted on a Bell P-39N-1 airplane to determine the variation with Mach and Reynolds numbers of the maximum lift coefficient obtainable. The tests were made with the propeller in the constant-speed high-pitch setting and with the power off in order to minimize the effect of power and the propeller. The investigation covered a Mach number range of 0.146 to 0.655 and a Reynolds-number range of 4,900,000 to 17,100,000.The results of the investigation indicated that the maximum lift coefficient obtainable decreased markedly with an increase in Mach number for a given Reynolds number and exhibited a tendency to increase with an increase in Reynolds number for a given Mach number up to a Mach number of 0.55.


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    Title :

    Effect of Mach and Reynolds Numbers on the Power-Off Maximum Lift Coefficient Obtainable on a P-39N-1 Airplane as Determined in Flight


    Contributors:

    Publication date :

    1944-06-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English





    Effect of Mach and Reynolds numbers on maximum lift coefficient

    Spreiter, John R. / Steffen, Paul J. | TIBKAT | 1946


    Effect of Mach and Reynolds Numbers on Maximum Lift Coefficient

    Spreiter, John R / Steffen, Paul J | NTRS | 1946


    Effect of Mach and Reynolds Numbers on Maximum Lift Coefficient

    J. R. Spreiter / P. J. Steffen | NTIS | 1946


    Effect of Mach and Reynolds numbers on maximum lift coefficient

    Spreiter, J.R. / Steffen, P.J. | Engineering Index Backfile | 1946