Results of recent tests of a large-scale axisymmetric mixed-compression inlet system designed for Mach number 2.65 indicate that the performance of the supersonic diffuser and required boundary-layer bleed system can be accurately estimated with relatively new analytic methods. These methods use complex computer programs to calculate both the inviscid and viscous flowfields including the effects of boundary-layer bleed. A bleed system was designed using these programs and the flow characteristics of bleed holes determined from isolated wind-tunnel tests that partially simulated the surface conditions in the inlet. These analytic methods show promise of saving many wind-tunnel testing hours by avoiding much of the usual "cut and try" wind-tunnel development.
Nomenclature
A-area M = Mach number m = mass flow TV = boundary-layer power-law exponent p = static pressure p p = pitot pressure p p i = plenum chamber pressure p t = total pressure p t = area-weighted average total pressure R = cowl lip radius U = velocity x = axial station measured from tip of the centerbody y = distance from surface a = angle of attack 8 = ratio of engine-face total pressure to standard sea-level static pressure 6 = ratio of freestream total temperature to standard sea-level static temperature Subscripts bl = bleed c = capture GRIT = critical e = edge of boundary layer L = local inviscid flow max = maximum min = minimum OP = operating th -throat 2 = engine face oo = freestream
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