Research Memorandum
E I RESEARCH MEMORANDUM AERODYNAMIC CBAFLACTERISTICS OF A WING WITH QUARTER-CHOFCO I LINF, SWEPT BACK No,ASPECT RATIO 4, TAPER i FLAT10 0.6,AND NACA 65A006 AIRFOIL SECTION TRANSONIC-BUMP METHOD By Thomas f. .Erg;Jr., and Boyd C. Myers, II Langley Aeronautical Laboratory Langley Air Force Base, Va. """- .NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS WASHINGTON September 6, 1949 UNCUSSiFfg-? P a RATIO 0.6,. e NAGA 6s006 -OIL SF,CTkON t . AB part of a transonic resemch.prog??am, a series of win@Oay combinations qe being investigated in the Langley high-peed 7- by 1o"foot' tunnel over a Mach nmiber range from about 0.60 to 1.18, by use of the tranaonic4Ump test technique. i This paper presents the results-of the investigation of a win-ane and a wing-frmelage configuration amploykg a wing with quartemhard line swept back 600, aspect ratio 4, taper ratio 0.6, and an WA65~006 airfpii section. The results are presentedas lift, drag, pitchine moment, and bendineanent coefficients for'both confipatim. The effect of a wing fence on the wing-fuselage charsbteristics was also investigated. In addition,e.ffective downwaah angles and point dynamic 'pressures for a range of tail heights at a probable tail .length &e presented. for the two configuratiomFnvestlgated. Only a brief ' Wsie is given in order to facilitate the publiehhg of the data. IIJTRODUCTION A series of wiwfuselage canbinations ISbeing inveetigated in the Langley high-peed 7- by 10-foot tunnel to study the effects of,- gemtry on longitudinal stability characteristic8 at transonic speeda.
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