Detailed pressure distribution measurements obtained on several configurations of an aspect-ratio-7 variable twist wing
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7-Meter Tunnel 72 independently rotatable a+ Aa a+Aa angle of attack chord chordwise Cl and Cl,p Cl,cb CL)P cn FOR y/s cn versus y/s Concluded configurations encompassed span Continued cp versus x/c Detailed pressure distribution DISTRIBUTION MEASUREMENTS OBTAINED electronic scanning pressure encompassed span loads Figure group III VTW independently rotatable wing INTEGRATED cn Langley Research Center lift coefficient lift was included lower surface measurements for group measurements of lift multisegmented wing model NACA NASA nominal Cl obtain 580 surface part-span-flap plots and tabulations Potential Flow pressure distribution measurements pressure-orifice range of span-load RESULTANT scanning pressure transducers semispan simple flapped wings span loads ranging surface o Interpolated trailing edge y/s untwisted upper-surface spoilers attached VALUES OF cn variable twist wing VTW configurations VTW1 VTW2 VTW3 VTW4 VTW5 VTW6 VTW7 VTW7S3P VTW7Si wing centerline wing segments wing to simple Wing twist configuration Wing twist distributions wing-chord Reynolds number X/C 7/r VALUES x/c y/s