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0iEi 0OkO 3EOO angle of attack annulus b1eed basic inlet bleed system boundary bypass bypass duct centerbody bleed circular internal-compression inlet compression ramp Compressor rake deflector plate drag coefficient entire angle-of-attack range exit rake flow-deflector plate forebody four inlets four turbojet engines fuselage highest pressure recovery horizontal ramp inlet inlet at angles inlet center line inlet entrance inlet hooded inlet inlet obtained inlet operating inlets tested internal area distribution Internal compression inlet investigated layer main duct mass-flow measuring station mass-flow ratio maximum pressure recovery NACA RM number of 2.0 oblique shock OEO0 OEOO OiE1 percent plote pressure fluctuations pressure recovery decreased Ramp bleed ramp deflection angle second ramp second-ramp angle shock structure shock wave shown in figure Side Inlets slot three external-compression inlets Three-shock horizontal ramp three-shock horizontal-ramp inlet three-shock vertical-ramp inlet total-pressure distortion two-shock vertical-ramp inlet wave drag XEOO