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Experimental Data for an 80° Delta Wing

This page presents a set of steady experimental data pertaining to an 80° delta wing at a pitch angle of 30° and various static roll angles. The original experiment was performed at the University of Notre Dame in the Hessert Center for Aerospace Research low speed wind tunnel. The Reynolds number for this experiment was 400,000, and the flow should be considered to be nearly incompressible.


The geometry for this test was a slender delta wing with 80° leading edge sweep, a root chord of 16 5/8 inches, a total wing span of 5 7/8 inches measured at the base of the delta wing, and a thickness of 1/4 inch. The figure below shows a sketch of the actual experimental aparatus. Click on the image to enlarge it.



The following plots show surface pressure distributions on the upper and lower surfaces of the delta wing for various roll angles. Click on any of the images to enlarge.

Zero Roll Angle
Roll Angles from 0° to 30°
Roll Angles from 40° to 90°

The data in the above plots has also been carefully transcribed into text format for easy comparison with CFD data. Use the following links to download a plain text data file with the relevant data from each figure.


1. Arena, A.S., "An Experimental and Computational Investigation of Slender Wings Undergoing Wing Rock," Ph.D. Dissertation, Department of Aerospace and Mechanical Engineering, Notre Dame, April 1992.

Revised: March 7, 2001 [TJC]
Oklahoma State University