An unsteady rotor/fuselage interaction methodAn analytical method has been developed to treat unsteady helicopter rotor, wake, and fuselage interaction aerodynamics. An existing lifting line/prescribed wake rotor analysis and a source panel fuselage analysis were modified to predict vibratory fuselage airloads. The analyses were coupled through the induced flow velocities of the rotor and wake on the fuselage and the fuselage on the rotor. A prescribed displacement technique was used to distort the rotor wake about the fuselage. Sensitivity studies were performed to determine the influence of wake and body geometry on the computed airloads. Predicted and measured mean and unsteady pressures on a cylindrical body in the wake of a two-bladed rotor were compared. Initial results show good qualitative agreement.
Document ID
19880030059
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Egolf, T. Alan (United Technologies Research Center East Hartford, CT, United States)
Lorber, Peter F. (United Technologies Research Center East Hartford, CT, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1987
Subject Category
Aerodynamics
Meeting Information
Meeting: National Specialists'' Meeting on Aerodynamics and Aeroacoustics