Experimental and numerical investigation of flow separation in a supersonic nozzle

Capability of two-dimensional Reynolds-averaged Navier—Stokes simulations for two-dimensional thrust vectoring nozzles

“…The magnitude and direction of the resulting force can be controlled by deflector position, height, and angle. In reference [3], the height and the angle deflector related to the vertical axis of the Cartesian coordinate system were 30 per cent and 30 • , respectively.…”

“…The results of steady flow computations given in reference [3] indicated difficulties in obtaining the second-order accuracy in the case with the highest deflector that produces the largest region of separated flow. For this reason, the highest deflector at the exit plane served for checking grid dependence.…”

“…Three optical methods namely, shadow, schlieren, and interferometry, are used for flow visualization [3,4]. In recent times, these methods are used as comparative bases for numerical ones.…”

“…The interaction of a turbulent boundary layer with a shock wave is one of the most interesting and challenging problems that have been experimentally and numerically analysed since the 1960s. Since then, a considerable progress has been made especially in visualization and in developing efficient numerical algorithms, while far less advance has been done with turbulence models, leading to the often quoted statement that turbulent modelling is the pacing item in computational fluid dynamics (CFD) [1][2][3][4][5][6][7][8][9][10][11][12][13][14][15][16].…”

“…Such a flow appears in a two-dimensional (2D) supersonic nozzle with a deflector placed at the exit of the nozzle. The deflector generates flow asymmetry in the divergent part of the nozzle, serving for thrust vectoring, controlled by the height and angle of the deflector [1,[3][4][5][6][7][8]]. An oblique shock wave is created in the nozzle.…”