Pressure, force and moment measurements on aircraft model at subsonic wind tunnel

Pressure distribution, force and moment on aircraft model is estimated using a pressure scanner, six component balance and data acquisition system in the subsonic wind tunnel at Madras institute of technology, India. A wing-bodytail model of aircraft model of suitable scale to fit in the test section of subsonic wind tunnel is designed and fabricated with pressure ports at suitable points. The model is to be tested at range of pitch angles from -10° to 30°, in steps of 10 degrees. For each pitch angle the velocity is constant and the variation of coefficient of pressure on the surface of the model is determined using a suitable data acquisition system. The experiment is done for zero yaw angle and readings are taken for the calibration model. Pressure plots and aerodynamic coefficient plots are made for constant velocity and different pitch angle.