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Experimental and analytical studies of a model helicopter rotor in hoverA benchmark test to aid the development of various rotor performance codes was conducted. Simultaneous blade pressure measurements and tip vortex surveys 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.
Document ID
19820004169
Document Type
Conference Paper
Authors
Caradonna, F. X. (NASA Ames Research Center Moffett Field, CA, United States)
Tung, C. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 4, 2013
Publication Date
September 1, 1981
Subject Category
AERODYNAMICS
Report/Patent Number
A-8332
NASA-TM-81232
USAAVRADCOM-TR-81-A-23
Meeting Information
European Rotorcraft and Powered Lift Aircraft Forum(Bristol)
Funding Number(s)
PROJECT: RTOP 922-21-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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