The NASA Langley Laminar-Flow-Control Experiment on a Swept Supercritical Airfoil: Basic Results for Slotted Configuration

By National Aeronautics and Space Administration

The effects of Mach number and Reynolds number on the experimental surface pressure distributions and transition patterns for a large chord, swept supercritical airfoil incorporating an active Laminar Flow Control suction system with spanwise slots are presented. The experiment was conducted in the Langley 8 foot Transonic Pressure Tunnel. Also included is a discussion of the influence of model/tunnel liner interactions on the airfoil pressure distribution. Mach number was varied from 0.40 to 0.82 at two chord Reynolds numbers, 10 and 20 x 1,000,000, and Reynolds number was varied from 10 to 20 x 1,000,000 at the design Mach number. Harris, Charles D. and Brooks, Cuyler W., Jr. and Clukey, Patricia G. and Stack, John P. Langley Research Center BOUNDARY LAYER CONTROL; LAMINAR FLOW; SUPERCRITICAL AIRFOILS; SWEPT WINGS; TRANSONIC FLOW; WING SLOTS; COMPUTATIONAL FLUID DYNAMICS; INTERACTIONAL AERODYNAMICS; MACH NUMBER; PRESSURE DISTRIBUTION; REYNOLDS NUMBER; SUCTION; WIND TUNNEL TESTS...

• Format: Paperback
• Language: English
• ISBN: 1731325258
• ISBN13: 9781731325259
• Release Date: November 2018
• Publisher: Independently Published
• Length: 122 Pages
• Weight: 0.66 lbs.
• Dimensions: 0.3" x 8.5" x 11.0"