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Experimental Data for a Hovering Rotor

This page presents a set of steady experimental data pertaining to a hovering rotor. The original model was tested in the Army Aeromechanics Laboratory's hover test facility, which is a large chamber with special ducting designed to eliminate room recirculation. The rotor was equipped with a hub-mounted Scanivalve assembly which permitted the measurement of pressure at 120 points on the rotor. Wake measurements were also performed with traversing hot wires. The avaliable data relates to several high-speed hover tests with tip Mach numbers ranging from 0.439 to 0.890.


Geometry

The rotor model for this test employed two cantilever-mounted, manually adjustable blades with half degree precone. The blades used an NACA 0012 profile and were untwisted and untapered. An aspect ratio of 6.0 was used, and the rotor diameter was set at 7.5 ft. Click on the image below to enlarge it.

geometry_sm.gif


Data

We have chordwise surface pressure data for collective pitch angles, θc = 0°, 2°, 5°, and 8°. Use the following links to download a plain text data file with the relevant data for each collective pitch angle and tip Mach number. Each file contains data at five radial locations, r/R along the blades.


References

1. F.X. Caradonna and C. Tung, "Experimental and Analytical Studies of a Model Helicopter Rotor in Hover," NASA Technical Memorandum 81232, National Aeronautics and Space Administration, 1981.


CASE Lab URL: http://www.caselab.okstate.edu/research/experiment/rotor.html
Revised: April 11, 2001 [TJC]
Webmaster: caselab@gmail.com
Oklahoma State University