Active control of aerodynamic chracteristics of next-generation SST wing by lateral blowing

An experimental study on the improvement of aerodynamic characteristics of an arrow wing by lateral blowing in low and high speed flow, has been conducted. An arrow wing, which is one of the baseline configurations of next-generation SST, is selected for the experiments. As compared to the delta wing, it is known that an arrow wing has higher the ratio of lift to drag and improvement of stability in low speed region because of the supersonic leading edge. However for being economically feasible more L/D is required for the development of SST. The testing model is the combination of a body of a circular cylinder and conical apex and a modified arrow wing with aspect ratio of 1.91. The lateral blowing is realized by injecting a pair of steady jets in a direction parallel to the trailing edge of the wing. The experiments have been performed in the transonic and supersonic wind tunnel located at ISAS under the testing conditions of M_∞(free-strcam Mach number) = 0.3 ~2.3, Re unit (unit Reynolds number) = 1.06×10⁷ ~3.10×10⁷[1/m], α (angle of attack) = - 15° ~30° and C_j (jet momentum coefficient) = 0.0084 ~0.0316. The results show that the C_L and L/D is increased by lateral blowing while C_D is slightly increased for positive a. The results suggest that the lateral blowing can be useful for the improvement of aerodynamic characteristics of the arrow wing in low and high speed flow.