Accession Number:

ADA011270

Title:

Rotor Induced Power

Descriptive Note:

Final rept.

Corporate Author:

ARMY AVIATION SYSTEMS COMMAND ST LOUIS MO

Personal Author(s):

Report Date:

1975-05-01

Pagination or Media Count:

37.0

Abstract:

Methodology is presented for rapid estimation of the induced power requirements of a helicopter rotor. Operating ranges treated are hover in or out of ground effect, vertical climb, and level flight. Earlier work on this subject is modified by more recent flight test information on ground effect enlarged in scope by the consideration of a generalized trapezoidal inflow velocity scope by the consideration of a generalized trapezoidal inflow velocity distribution at the rotor and refined to account for the influence of level flight on the effect of a non-uniform induced velocity distribution at the rotor.

Subject Categories:

  • Aerodynamics
  • Helicopters

Distribution Statement:

APPROVED FOR PUBLIC RELEASE