High Reynolds Number Tests of a C141A Aircraft Semispan Model to Investigate Shock-induced Separation |
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16T TRANSITION FIXED 389 FREE PAGE 60 80 REYNOLDS 637 FREE PAGE 80 REYNOLDS NUMBER AEDC 16T TRANSITION airfoil ALPHA A D+ ALPHA POROSITY angle of attack boundary layer C-141 SEMI-SPAN MODEL CFF SMOOTH AEDC CFF TRANSITION FIXED CH141 SEMI-SPAN Compressible Flow Facility configuration correlation D+ XO D+XO DATA REYNOLDS degree angle figures 12 FIXED CFF SMOOTH FLIGHT REFERENCE flight test FLOOR SEALED high Reynolds number highest Reynolds number Lockheed-Georgia Company low Reynolds numbers LSHT 10 DATE LSHT DATE LSWT Mach number NASA outboard stations panel model pressure coefficient pressure distribution pylons and nacelles scale effects SEMI-SPAN MODEL 850 SEMI-SPAN MODEL M=-825 semispan test shock location shock-induced separation SMOOTH AEDC 16T spanwise contamination spanwise station STA 389 FREE STA 637 FREE stagnation pressure station 389 station 637 trailing-edge pressure recovery trailing-edge separation TRANSITION FIXED CFF TRANSITION FIXED REFERENCE wing X/CSH XO A ALPHA