Author: Danny R. HoadPublisher:
ISBN:
Category :
Languages : en
Pages : 164
Book Description
Laser Velocimeter Survey about a NACA 0012 Wing at Low Angles of Attack
Author: Danny R. HoadNASA Technical Note
Author: NASA Technical Paper
Author: Scientific and Technical Aerospace Reports
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 666
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Monthly Catalog of United States Government Publications
Author: Monthly Catalogue, United States Public Documents
Author: Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 944
Book Description
Monthly Catalog of United States Government Publications
Author: United States. Superintendent of DocumentsPublisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1122
Book Description
NASA Technical Memorandum
Author: Application of Laser Doppler Velocimeter to Chemical Vapor Laser System
Author: Luther R. GartrellFlow Environment Study Near the Empennage of a 15-Percent Scale Helicopter Model
Author: Susan Althoff GortonPublisher:
ISBN:
Category : Helicopters
Languages : en
Pages : 32
Book Description
Development of advanced rotorcraft configurations has highlighted a need for high-quality experimental data to support the development of flexible and accurate analytical design tools. To provide this type of data, a test program was conducted in the Langley 14- by 22-Foot Subsonic Tunnel to measure the flow near the empennage of a 15-percent scale powered helicopter model with an operating tail fan. Three-component velocity profiles were measured with laser velocimetry (LV) one chord forward of the horizontal tail for four advance ratios to evaluate the effect of the rotor wake impingement on the horizontal tail angle of attack. These velocity data indicate the horizontal tail can experience unsteady angle of attack variations of over 30 degress due to the rotor wake influence. The horizontal tail is most affected by the rotor wake above advance ratios of 0.10. Velocity measurements of the flow on the inlet side of the tail fan were made for a low-speed flight condition using conventional LV techniques. The velocity data show an accelerated flow near the tail fan duct, and vorticity calculations track the passage of main rotor wake vortices through the measurement plane.