Accession Number ADA566027
Title Loads Correlation of a Full-Scale UH-60A Airloads Rotor in a Wind Tunnel.
Publication Date May 2012
Media Count 24p
Personal Author E. A. Romander H. Yeo
Abstract Wind tunnel measurements of the rotor trim, blade airloads, and structural loads of a full-scale UH-60A Black Hawk main rotor are compared with calculations obtained using the comprehensive rotorcraft analysis CAMRAD II and a coupled CAMRAD II/OVERFLOW 2 analysis. A speed sweep at constant lift up to an advance ratio of 0.4 and a thrust sweep at constant speed into deep stall are investigated. The coupled analysis shows significant improvement over comprehensive analysis. Normal force phase is better captured and pitching moment magnitudes are better predicted including the magnitude and phase of the two stall events in the fourth quadrant at the deeply stalled condition. Structural loads are, in general, improved with the coupled analysis, but the magnitude of chord bending moment is still significantly underpredicted. As there are three modes around 4 and 5/rev frequencies, the structural responses to the 5/rev airloads due to dynamic stall are magnified and thus care must be taken in the analysis of the deeply stalled condition.
Keywords Aerodynamic loading
Bending moments
Helicopter rotors
Helicopters
Measurement
Moments
Pitch(Motion)
Structural response
Thrust
Uh-60a aircraft
Velocity
Wind tunnel tests


 
Source Agency Non Paid ADAS
NTIS Subject Category 51C - Aircraft
51F - Test Facilities & Equipment
Corporate Author Army Research Development and Engineering Command, Ames Research Center, Moffett Field, CA. Aviation Aeroflight Dynamics Directorate.
Document Type Technical report
Title Note N/A
NTIS Issue Number 1306
Contract Number N/A

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