UH-60A Rotor Performance and Loads Correlation at High Advance Ratios-Reference-Cited by-同舟云学术

UH-60A Rotor Performance and Loads Correlation at High Advance Ratios

Published:2018-01 Issue:1 Volume:55 Page:275-293
ISSN:0021-8669
Container-title:Journal of Aircraft
language:en
Short-container-title:Journal of Aircraft

Author:

Bowen-Davies Graham¹,Yeo Hyeonsoo²

Affiliation:

1. Science and Technology Corporation, Moffett Field, California 94035

2. U.S. Army Aeroflightdynamics Directorate (AMRDEC), Moffett Field, CA 94035

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

https://arc.aiaa.org/doi/pdf/10.2514/1.C034492

Reference12 articles.

1. WheatleyJ. B.HoodM. J. “Full-Scale Wind-Tunnel Tests of a PCA-2 Autogiro Rotor,” NACA Rept. 515, 1935.

2. JenkinsJ. L. Jr. “Wind Tunnel Investigation of a Lifting Rotor Operating at Tip-Speed Ratios from 0.65 to 1.45,” NASA TN D-2628, 1965.

3. McCloudJ. L.BiggersJ.StroubR. H. “An Investigation of Full-Scale Helicopter Rotors at High Advance Ratios and Advancing Tip Mach Numbers,” NASA TN-D-4632, 1968.

4. CharlesB. D.TannerW. H. “Wind Tunnel Investigation of Semirigid Full-Scale Rotors Operating at High Advance Ratios,” U.S. Army Aviation Materiel Labs. TR 69-2, Fort Eustis, VA, Jan. 1969.

5. HarrisF. D. “Rotor Performance at High Advance Ratio: Theory Versus Test,” NASA CR-2008-215370, 2008.

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