To model propeller noise expected for a turboprop aircraft, the pressure ratio across the shock at the propeller tip was calculated and compared with noise data from three propellers. At helical tip Mach numbers over 1.0, using only the tip shock wave, the model gave a fairly good prediction of the noise for a bladed propeller and for a propeller swept for aerodynamic purposes. However for another propeller, which was highly swept and designed to have noise cancellations from the inboard propeller sections, the shock strength from the tip over predicted the noise. In general the good agreement indicates that shock theory is a viable method for predicting the noise from these supersonic propellers but that the shock strengths from all of the blade sections need to be properly included.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    A Shock Wave Approach to the Noise of Supersonic Propellers


    Beteiligte:
    J. H. Dittmar (Autor:in) / E. J. Rice (Autor:in)

    Erscheinungsdatum :

    1981


    Format / Umfang :

    19 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    A shock wave approach to the noise of supersonic propellers

    Dittmar, J. H. / Rice, E. J. | NTRS | 1981


    Supersonic propellers

    Hilton, W.F. | Engineering Index Backfile | 1951


    Shock wave noise of supersonic aircraft

    Ryhming, I.L. / Yoler, Y.A. / Aoki, Y. | Engineering Index Backfile | 1960


    SHOCK WAVE NOISE OF SUPERSONIC AIRCRAFT

    RYHMENG, I. L. / AOKI, Y. / YOLER, Y. A. | SAE Technical Papers | 1960


    Shock wave noise problem of supersonic aircraft

    Engineering Index Backfile | 1959