NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login

Press Enter or click the Search button to begin your search.

Back to Results
Development and validation of a combined rotor fuselage induced flow field computational methodA potential-flow panel method was modified to calculate the effects of a rotor wake on the time-averaged surface pressure and velocity distributions on a helicopter fuselage. The rotor-induced velocities are calculated by using a vortex-tube wake model. The calculated pressure distributions are found to compare well with experimental data obtained from tests of a wind-tunnel model.
Document ID
19800016803
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Freeman, C. E. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
June 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
AVRADCOM-TR-80-B-3
NASA-TP-1656
L-13363
Report Number: AVRADCOM-TR-80-B-3
Report Number: NASA-TP-1656
Report Number: L-13363
Accession Number
80N25296
Funding Number(s)
PROJECT: RTOP 505-42-23-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available