Accession Number:

ADA089780

Title:

Experimental and Analytical Studies of a Model Helicopter Rotor in Hover

Descriptive Note:

Corporate Author:

ARMY RESEARCH AND TECHNOLOGY LABS MOFFETT FIELD CA

Personal Author(s):

Report Date:

1980-01-01

Pagination or Media Count:

20.0

Abstract:

The present study is a benchmark test to aid the development of various rotor performance codes. The study involves simultaneous blade pressure measurements and tip vortex surveys. Measurements were made for a wide range of tip Mach numbers including the transonic flow regime. The measured tip vortex strength and geometry permit effective blade loading predictions when used as input to a prescribed wake lifting surface code. It is also shown that with proper inflow and boundary layer modeling, the supercritical flow regime can be accurately predicted.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE