A sailplane being developed at NASA Dryden Flight Research Center will support a high-altitude flight experiment. The experiment will measure the performance parameters or an airfoil at high altitudes (70,000 - 100,000 ft), low Reynolds numbers (2 x 10(exp 5) - 7 x 10(exp 5)), and high subsonic Mach numbers (0.5 and 0.65). The airfoil section lift and drag are determined from pilot and static pressure measurements. The locations of the separation bubble, Tollmien-Schlichting boundary-layer instability frequencies, and vortex shedding are measured from a hot-film strip. The details of the planned flight experiment are presented as well as several predictions of the airfoil performance.
Design and Predictions for High-Altitude (Low Reynolds Number) Aerodynamic Flight Experiment
2000
6 pages
Report
Keine Angabe
Englisch
Aerodynamics , Aircraft , Test Facilities & Equipment , Performance tests , Aerodynamic drag , High altitude , Low reynolds number , Pressure measurement , Flight characteristics , Experiment design , Airfoil profiles , Boundary layers , Bubbles , Gliders , Lift , Mach number , Position(Location) , Static pressure , Subsonic speed , Vortex shedding