Aerodynamic Characteristics of Several 6-percent-thick Airfoils at Angles of Attack from 0 Degrees to 20 Degrees at High Subsonic Speeds

Report presenting two-dimensional tests of eight 6-percent-thick symmetrical airfoils of the supersonic and subsonic types. Static pressures along the surfaces of each airfoil measured over a range of Mach numbers and angles of attack. Results regarding lift coefficient, drag coefficient, quarter-chord pitching-moment coefficient, and schileren photographs of the pressure distributions are provided.