Parametrics on 2D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet

Abstract

The supersonic diffuser of a Mach 2.68 bifurcated, rectangular, mixed-compression inlet was analyzed using a two-dimensional (20) Navier-Stokes flow solver. Parametric studies were performed on turbulence models, computational grids and bleed models. The computed flowfield was substantially different from the original inviscid design, due to interactions of shocks, boundary layers, and bleed. Good agreement with experimental data was obtained in many aspects. Many of the discrepancies were thought to originate primarily from 3D effects. Therefore, a balance should be struck between expending resources on a high fidelity 20 simulation, and the inherent limitations of 20 analysis. The solutions were fairly insensitive to turbulence models, grids and bleed models. Overall, the k-e turbulence model, and the bleed models based on unchoked bleed hole discharge coefficients or uniform velocity are recommended. 20 Navier-Stokes methods appear to be a useful tool for the design and analysis of supersonic inlets, by providing a higher fidelity simulation of the inlet flowfield than inviscid methods, in a reasonable turnaround time.

Computational study of flow in a rocket-based combined cycle (RBCC) engine inlet

“…Mizukami and Saunders [18] performed a parametric study of various turbulence and bleed models using the 2-D version of NPARC for a Mach 2.68 bifurcated rectangular mixed-compression inlet and presented a comparison of the solution with experimental data. Podleski et al [19] applied NPARC to analyze the flow field through the F/A-18A High Alpha Research Vehicle (HARV) inlet and compared the results with the flight data.…”

“…The computational grid is generated using a two-dimensional version of the grid generation code developed for inlet and nozzle geometries at NASA Glenn Research Center (Reddy) [18]. The geometry of the RBCC inlet considered here was defined by a series of cubic splines and other geometric shapes (Fig.…”

Design and Performance of Hypersonic Intake for Scramjet Engine

“…The locations are along the compression ramp, cowl, sidewall of the intake (Figure 8). Numerical investigation of different bleed models for a mixed compression inlet has been reported by Mizukami et al [6] and Vivek and Mittal [7]. Gawienowski conducted a series of experiments with different bleed slot sizes and mass flow rates to assess the performance of an external compression intake at supersonic speeds [8].…”

Starting characteristics of a rectangular supersonic air-intake with cowl deflection

“…Babinsky et al (20)(21) demonstrated that, use of micro ramp vortex generators controls the boundary layer and leads to improvement in inlet performance. Numerical investigation to study the effect of bleed flow rate, bleed hole geometry is reported by Mizukami et al (22) , Syberg et al (23) and Vivek and Mittal (24) . The effect of wall perforation on the starting of a supersonic intake is reported by Najafiyazdi et al (25) .…”