NDLI: Aerodynamic limitations of the uh-60a rotor

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Aerodynamic limitations of the uh-60a rotor

Content Provider	NASA Technical Reports Server (NTRS)
Author	Bousman, William G. Coleman, Colin P.
Copyright Year	1996
Description	High quality airloads data have been obtained on an instrumented UH-60A in flight and these data provide insight into the aerodynamic limiting behavior of the rotor. At moderate weight coefficients and high advance ratio limiting performance is largely caused by high drag near the blade tip on the advancing side of the rotor as supercritical flow develops on the rotor with moderate to strong, shocks on both surfaces of the blade. Drag divergence data from two-dimensional airfoil tests show good agreement with the development of the supercritical flow regions. Large aerodynamic pitching moments are observed at high advance ratio, as well, and these pitching moments are the source of high torsional moments on the blade and control system loads. These loads occur on the advancing side of the disk and are not related to blade stall which does not occur for these weight coefficients. At high weight coefficients aerodynamic and structural limits are related to dynamic stall cycles that begin on the retreating side of the blade and, for the most severe conditions, carry around to the advancing side of the blade at the presumed first frequency of the blade/control system.
File Size	806501
Page Count	22
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19960049728
Archival Resource Key	ark:/13960/t9m37rk27
Language	English
Publisher Date	1996-08-01
Access Restriction	Open
Subject Keyword	Aerodynamics Flight Tests Pitching Moments Blade Tips Supercritical Flow Rotors Airfoils Drag Uh-60a Helicopter Aerodynamic Characteristics Torsion Stability Derivatives Aerodynamic Stalling Aerodynamic Loads Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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