A computer program for the determination of the acoustic pressure signature of helicopter rotors due to blade thickness [PDF]
A computer program is presented for the determination of the thickness noise of helicopter rotors. The results were obtained in the form of an acoutic pressure time history.
Farassat, F., Mall, G. H.
core +1 more source
The effect of helicopter configuration on the fluid dynamics of brownout [PDF]
, 2008 Brown’s Vorticity Transport Model, coupled to an additional particle transport model, is used to simulate the development of the dust cloud that can form around a helicopter when operating in dusty or desert conditions.
Brown, R., Phillips, C.
core +1 more source
The cost of applying current helicopter external noise reduction methods while maintaining realistic vehicle performance [PDF]
Analytical methods were developed and/or adopted for calculating helicopter component noise, and these methods were incorporated into a unified total vehicle noise calculation model.
Bowes, M. A.
core +1 more source
Model helicopter rotor high-speed impulsive noise: Measured acoustics and blade pressures [PDF]
A 1/17-scale research model of the AH-1 series helicopter main rotor was tested. Model-rotor acoustic and simultaneous blade pressure data were recorded at high speeds where full-scale helicopter high-speed impulsive noise levels are known to be dominant.
Boxwell, D. A. +3 more
core +1 more source
Forces on Obstacles in Rotor Wake – A GARTEUR Action Group [PDF]
, 2017 The paper describes the objectives and the structure of the GARTEUR Action Group HC/AG-22 project which deals with the basic research about the forces acting on obstacles when immersed in rotor wakes.
Bakker, Richard +13 more
core +1 more source
Flight testing the fixed-wing configuration of the Rotor Systems Research Aircraft (RSRA) [PDF]
The Rotor Systems Research Aircraft (RSRA) is a unique research aircraft designed to flight test advanced helicopter rotor system. Its principal flight test configuration is as a compound helicopter. The fixed wing configuration of the RSRA was primarily
Hall, G. W., Morris, P. M.
core +1 more source
An unsteady helicopter rotor: Fuselage interaction analysis [PDF]
A computational method was developed to treat unsteady aerodynamic interactions between a helicopter rotor, wake, and fuselage and between the main and tail rotors.
Egolf, T. Alan, Lorber, Peter F.
core +1 more source
A flight dynamics investigation of compound helicopter configurations [PDF]
, 2013 Compounding has often been proposed as a method to increase the maximum speed of the helicopter. There are two common types of compounding known as wing and thrust compounding.
Ferguson, K., Thomson, D.
core
Aeroacoustic analysis of main rotor and tail rotor interaction [PDF]
, 2008 The increased restrictions placed on helicopter noise levels over recent decades have encouraged manufacturers to better understand tail rotor noise and its aerodynamic sources.
Brown, R.E. +2 more
core +1 more source
Aeromechanical Stability of Rotor/Fuselage Coupling System in Helicopter Ground Taxiing
AerospaceWhen a helicopter is ground taxiing, the dynamic characteristics of the landing gear wheels change with the taxiing speed, and the rotor generates significant aerodynamic forces. Therefore, the dynamic stability of the rotor/fuselage coupling system when
Junhao Zhang, Jie Yang, Pinqi Xia
doaj +1 more source