FEASIBILITY OF WING SHIELDING OF THE AIRPLANE INTERIOR FROM THE SHOCK NOISE GENERATED BY SUPERSONIC TIP SPEED PROPELLERS

A high tip speed turboprop is being considered as a future energy conservative airplane. The high tip speed of the propeller, combined with the speed of the airplane, results in supersonic relative flow on the propeller tips. These supersonic blade sections could generate noise that is a cabin environment problem. The feasibility of using wing shielding to lessen the impact of this supersonic propeller noise was investigated. An analytical model is chosen which considers that shock waves are associated with the propeller tip flow and indicates how they would be prevented from impinging on the airplane fuselage. An example calculation is performed where a swept wing is used to shield the fuselage from significant portions of the propeller shock waves.

  • Corporate Authors:

    Department of the Navy

    The Pentagon
    Washington, DC  USA  20350
  • Authors:
    • DITTMAR, J H
  • Publication Date: 1978-12

Media Info

  • Pagination: 25 p.

Subject/Index Terms

Filing Info

  • Accession Number: 00191991
  • Record Type: Publication
  • Source Agency: National Technical Information Service
  • Report/Paper Numbers: NASA-TM-79042
  • Files: TRIS
  • Created Date: Jul 11 1979 12:00AM