Aerodynamic Characteristics of Several 6-Percent-Thick Airfoils at Angles of Attack From 0 degs to 20 degs at High Subsonic Speeds
Abstract
Two-dimensional tests of eight 6-percent-thick symmetrical airfoils of the supersonic and subsonic types were conducted in the Langley rectangular high-speed tunnel. Static pressures along the surfaces of each airfoil were measured over a Mach number range from 0.3 to the choking Mach number (about 0.92 at alpha = 0 deg) at angles of attack from 0 deg to 8 deg. Total-pressure surveys in the wake were obtained for the same Mach number range at angles of attack from 0 deg to 8 deg. Schlieren photographs of the air flow were also obtained for representative conditions. The aerodynamic characteristics of each of the airfoils have been determined from the measured pressure data. These results showed that the lift-curve slope of each of the airfoils decreased rapidly to a positive value approaching zero at angles of attack near 90 and roughly maintained this value up to the highest angle of attack tested. When the maximum thickness was located at the 0.3-chord station rather than at the 0.7-chord station, the circular-arc and wedge-type airfoils produced higher lift-curve slopes and maximum lift coefficients, lower drag coefficients for a given lift coefficient, and improved pitching-moment characteristics. The variations with Mach number of the lift, drag, and pitching-moment coefficients are generally similar for the various types of airfoils tested. There appeared to be no factors which would prohibit the use of the sharp-leading-edge type of profiles at the subsonic speeds tested.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1955
- Accession Number
- ADA377293
Entities
People
- Bernard N. Daley
- Douglas R. Lord
Organizations
- National Aeronautics and Space Administration