Computational Test Cases for a Clipped Delta Wing with Pitching and Trailing-Edge Control Surface Oscillations

By National Aeronautics and Space Administration

Computational test cases have been selected from the data set for a clipped delta wing with a six-percent-thick circular-arc airfoil section that was tested in the NASA Langley Transonic Dynamics Tunnel. The test cases include parametric variation of static angle of attack, pitching oscillation frequency, trailing-edge control surface oscillation frequency, and Mach numbers from subsonic to low supersonic values. Tables and plots of the measured pressures are presented for each case. This report provides an early release of test cases that have been proposed for a document that supplements the cases presented in AGARD Report 702.Bennett, Robert M. and Walker, Charlotte E.Langley Research CenterCOMPUTATIONAL FLUID DYNAMICS; DELTA WINGS; AIRFOIL PROFILES; CONTROL SURFACES; PITCH (INCLINATION); WIND TUNNEL TESTS; UNSTEADY AERODYNAMICS; TRANSONIC FLOW; COMPUTERIZED SIMULATION; ANGLE OF ATTACK; TRAILING EDGES; MACH NUMBER; WIND TUNNEL MODELS; ATTITUDE CONTROL; OSCILLATIONS...

• Format: Paperback
• Language: English
• ISBN: 1723946060
• ISBN13: 9781723946066
• Release Date: January 1
• Publisher: Independently Published
• Length: 92 Pages
• Weight: 0.52 lbs.
• Dimensions: 0.2" x 8.5" x 11.0"