Geometric Evaluation of Axisymmetric Thrust-Vectoring Nozzles for Aerodynamic Performance Predictions

Abstract

Nomenclature A = area, m 2 A j e =A j t = nozzle area control ratio @ j D E , G CD = ow coef cient at the nozzle throat M = Mach r = radius, m V c = effective nozzle expansion volume, m 3 W = gas ow rate, kg/s x = nozzle expansion length, m x n = length of divergent nozzle aps, m; x G = cos ® @ ± Gy;z D 0 ® = nozzle divergence angle, rad = nozzle convergence angle, rad ± = nozzle jet de ection angle, rad » = one-dimensionalradial elongation of r E t Subscripts c = control constant E = effective e = exit G = geometric i = variable (yaw or pitch) t = throat x = body-axis direction y = yaw direction z = pitch direction 7 = nozzle entrance station number 8 = nozzle throat station number ? = normal to A G t Superscript j = variable (effective or geometric)

Performance research of axisymmetric vectoring nozzle based on numerical simulations

“…With the development of aeronautical technology, thrust vectoring nozzle has shown its advantages in many ways [1,2] .A series of investigations had been conducted to study the performance and flow characteristics of thrust vectoring nozzles [3][4][5][6][7][8] . Research results show that nozzle pressure ratios and geometric vectoring angle have significant influences on nozzles' performance.…”