| Abstract: | A model configuration of a hypersonic vehicle realizing the principle of compression convergence along spatially-convergent directions of the entire jet captured by an air-intake is studied. The configuration includes a convergent air-intake, whose gasdynamic design is performed using the axisymmetric supersonic flow in an internal convergent channel. The air-intake is integrated with the swept transversely-concave nose surface of the vehicle, which forms at high supersonic velocities a three-dimensional compression flow, also convergent. The results of numerical and experimental studies at freestream Mach numbers 4 and 6 are presented; they reveal the salient features of the gasdynamic pattern of the flows near the nose and the external compression wedge of the air-intake, as well as in the internal channel. |
