Mounting the SDB II proposed a challenge because it was necessary to see the aerodynamic effects on the fuselage without it being affected by a mounting device. To solve this problem, endplates were attached to the wind section in order to mount the model. The aerodynamics effects of the endplates were then subtracted from the final result.
“This approach allowed us to measure 52 pressures on the afterbodies and the bases over a wide range of angle of attack, with negligible effects from the model-support system,” said Raytheon Missile Systems Engineering Fellow David R. Carlson.
According to Raytheon test engineers, the wind tunnel data collected during this test may be the most comprehensive database for base and boattail pressures in the presence of deflected and undeflected control surfaces that has ever been acquired by any organization.
NIAR’s Aerodynamics Lab centers around the recently modernized Walter H. Beech Memorial Wind Tunnel, a premier low-speed, closed return wind tunnel. The lab also includes a flow visualization tunnel, and has access to the WSU College of Engineering’s 3x4-foot subsonic wind tunnel and two super-sonic wind tunnels. To learn more visit