Experimental Investigation and Fundamental Understanding of a Full-Scale Slowed Rotor at High Advance Ratios

被引:55
作者
Datta, Anubhav [1 ]
Yeo, Hyeonsoo [2 ]
Norman, Thomas R. [3 ]
机构
[1] NASA, Ames Res Ctr, Sci & Technol Corp, USA,Aeroflightdynam Directorate, Moffett Field, CA 94035 USA
[2] NASA, Ames Res Ctr, Aeroflightdynam Directorate AMRDEC, USA,Res Dev & Engn Command, Moffett Field, CA 94035 USA
[3] NASA, Ames Res Ctr, Aeromech Branch, Moffett Field, CA 94035 USA
关键词
TECHNOLOGY;
D O I
10.4050/JAHS.58.022004
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
This paper describes and analyzes the measurements from a full-scale, slowed revolutions per minute (rpm), UH-60A rotor tested at the National Full-Scale Aerodynamics Complex 40- by 80-ft wind tunnel up to an advance ratio of 1.0. A comprehensive set of measurements that includes performance, blade loads, hub loads, and pressures/airloads makes this data set unique. The measurements reveal new and rich aeromechanical phenomena that are unique to this exotic regime. These include reverse chord dynamic stall, retreating side impulse in torsion load, large inboard outboard elastic twist differential, diminishing rotor forces and yet a dramatic buildup of blade loads, and high blade loads and yet benign levels of vibratory hub loads. The objective of this research is the fundamental understanding of these unique aeromechanical phenomena. The intent is to provide useful knowledge for the design of high-speed, high-efficiency, slowed rpm rotors of the future and a database for validation of advanced analyses.
引用
收藏
页数:17
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