The Influence Of The Angle Of Attack Alpha On The Pressure Recovery At Aerodynamics Interface Plane Investigation

In the process of design of an aircraft to know the performance and stability requires testing in a wind tunnel. Similarly, the selection of engines for aircraft design embedded on conducted tests in a wind tunnel model air intake with some variations of the angle of attack. This paper examines the effect of the high angle of attack alpha testing aircraft air intake with a position of beta 0° on the subsonic regime with wind speed of 65 meter persecond. A combat aircraft is flying with an unexpected manoeuvre to avoid enemy attack or to defense against missiles. Often the aircraft must fly to the position of a very high angle of attack. The theoretical value of the pressure recovery is approaching value of one in order to make the machine pinned can work optimally. Experimental observations of pressure recovery are plotted against the variations of the angle of attack alpha. The observations show that the performance design of aircraft engine inlet on the high angle of attack alpha can still give adequate pressure recovery.