Estimation of the Wing Lift Distribution of the STOL Experimental Aircraft, “ASKA”

We estimated the wing lift distribution from the ASKA's flight tests, utilizing the stress data of the wing and the horizontal tail fin ¹⁾. The wing lift distribution was estimated, by dividing the wing into three kinds of parts; the center wing part, the USB (Upper Surface Blowing) flap parts, and the outer wing parts.

The results are that the lift of the center wing part is relatively high in all configurations. Particularly, it is higher than the lift of the USB flap parts in the STOL* take off configuration and in the clean configuration.

The induced drag of a USB type powered lift STOL aircraft was calculated from the estimates of the wing lift distribution. The results were compared with an aerodynamics model drag estimated by flight test data.