Forebody pneumatic devices at low angles of attack and transonic speed

A wind tunnel test was conducted on an F-16 forebody to study the effectiveness of forebody blowing at low angles of attack and transonic speeds. The yawing moments generated were significantly less than had been shown in previous tests at higher angles of attack, but were sufficient for directional control during typical ingress maneuvers. Optimal nozzle position and pointing angle were similar to those established during previous F-16 forebody tests. At low angle of attack a horizontal slotted nozzle was more effective than a vertical slotted nozzle. Low frequency pulsed blowing showed promise as a way of reducing mass flow. (Author)