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1 INTRODUCTION a
2c EXPERIMENTAL APPARATUS AND PROCEDURE
3 EXPERIMENTAL RESULTS
4 other sections not shown
adverse pressure gradient amplification factor angle of injection apparatus blast wave theory boundary layer separation Broadwell calculated Charwat and Allegre determined downstream due to Wu equations exit plane experimental program experimental results free stream inch increments inflection point injected gas INJECTION ANGLE injection port injection slot area Mach number mass flow rate momentum thrust nozzle axis nozzle blocks nozzle design nozzle wall plotted versus point of injection pressure taps primary and secondary primary flow primary stagnation pressures primary stream primary weight flow psig secondary gas injection secondary injection secondary jet secondary plenum chamber secondary stagnation pressure secondary stream secondary to primary secondary weight flow separated region SHADOWGRAPH OF SHOCK SHOCK SYSTEM side force produced slot width sonic specific heat ratio stagnation temperature static pressure supersonic stream Theory and Experiment theory due thrust vector control value of pressure versus the secondary weight flow rate wind tunnel Zukoski and Spaid