Transition aerodynamics for 20-percent-scale VTOL unmanned aerial vehicle

By: Nasa, National Aeronautics and Space Adm

An investigation was conducted in the Langley 14- by 22-Foot Subsonic Tunnel to establish a transition data base for an unmanned aerial vehicle utilizing a powered-lift ejector system and to evaluate alterations to the ejector system for improved vehicle performance. The model used in this investigation was a 20-percent-scale, blended-body, arrow-wing configuration with integrated twin rectangular ejectors. The test was conducted from hover through transition conditions with variations in angle of attack, angle of sideslip, free-stream dynamic pressure, nozzle pressure ratio, and model ground height. Force and moment data along with extensive surface pressure data were obtained. A laser velocimeter technique for measuring inlet flow velocities was demonstrated at a single flow condition, and also a low order panel method was successfully used to numerically simulate the ejector inlet flow. Kjerstad, Kevin J. and Paulson, John W., Jr. Langley Research Center...

• Format: Paperback
• Language: English
• ISBN: 1730730892
• ISBN13: 9781730730894
• Release Date: January 1
• Publisher: Independently Published
• Length: 54 Pages
• Weight: 0.33 lbs.
• Dimensions: 0.1" x 8.5" x 11.0"