Flowpath design of an axisymmetric Mach 7.0 nozzle for T4

An axisymmetric contoured nozzle tailored for specific flight conditions of M = 7, p0 = 6.035 MPa, T0 = 2432.2 K has been designed for the T4 reflected shock tunnel facility. It has a throat diameter of 0.021 m and an exit diameter of 0.273166 m, which corresponds to a throat-to-exit area ratio of 169.2. The nozzle has a throat-to-exit length of 1 m. The nozzle produces a uniform core flow diamond with a maximum axial length of 1.1 m and a maximum diameter of 0.2 m. Cross-sectional flow profiles taken at the exit plane of the nozzle show that the Mach number varies by ± 0.4% and the flow angularity varies by ± 0.13◦. The initial design was based on scaling an existing nozzle that was designed for a nearby operating condition. Starting with this scaled contour for the supersonic part of the nozzle contour, a B`ezier curve description of the contour was systematically perturbed to improve the estimated test flow conditions according to a Navier-Stokes computation that included high temperature effects.