Abstract:

Experiments were conducted to investigate the aerodynamic characteristics of a74 degree swept deltaw ing model equipped w ith an apex flap s and leadingedge vo rtex2flap s under thecondit ions of steady state w ith the angle of at tack varying from 0°to 90°and the unsteady p itch ingstate w ith the frequencies 0. 4, 0. 8 and 1. Hz asw ell as the effects of flow cont ro l via flap deflect ion. Comparisons betw een the results go t from experiments and the computat ion by so lving N Sequat ions w ere made. The unsteady p itch ing mo t ion caused the hysteret ic variat ion of the aerodynam ic coefficients to occur; how ever the advantageous effects of flap cont ro lw ere basically kep t asin the steady state. Experimental results such as the liftcoefficients obtained from the calibrat iontests of the basic delta w ing w ith no flap s w ere comparable to the co rresponding values found inreferences, and thus enhanced the reliability of the p resent tests.

Key words: steady?unsteady flow, largeincidence, flap control, experiment and N S computation