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A METHOD OF DETERMINING AERODYNAMIC-INFLUENCE COEFFICIENTS FROM WIND-TUNNEL DATA FOR WINGS AT SUPERSONIC SPEEDS
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C
AD-25594N1 602 100, 6054, 6869, 3504, 2131, 3668, 2079, 102, 4812, 6464, 6859, 6242 ad-255 95Div. 9u 3 May 61 OTS prce 0.75 NATIONAL Aeronauics and Space dminstration, Washington, d. c. invesigation at high ubsonic speeds of the use of low auxiliry tal surfces having iheal to mprove the longudinal and ireional stality of a t-tail model at high lift, by Wiliam C. LEEMAN, r. apr 61, 23p. inl. s. Technil note D-804 upesedes NA Research Memorandm L5724, AD- Unclassified report lso available from NSA, WASHINGTON , D. C., as NASA echncal note D-804. descriptors SUBSONC FLOW, AILS, SABILI TY Longitudinal, Model tests, lift, Aero dync configurions, airfols, aspect rio, Stabilizers 9hozontl tail urface, sta blity, staility Lateral, Wind unnel mod els, swept wings. an investigaion of the use of low uxlary hoizonal-al srfaces to aleviate the pitchup tendency at high lift of an airpane configuration having a T-tail was concted in the Langley high-speed 7- by 10-foot unnel. The bc model hd a wing with an spect ratio of 3, a taper raio of 0.143, and an unswept 80-percent chord line. The Mach nuber for most of the tes extended from 0.60 to 0.94 1nd the angleof-attak range was from -2 degrees to approxitely 4 degrees at the lowet test Mach number. A preliinary dy of a systematc seies of auxary ails indiated that the pitch-up tendency at high ift encountered on the ic model could be gretly levted by use of a relatively sall, very low-spet-raio auxliry hoizontl tail. This al ws loted rialy with respet to the fuselage center line with 30 degrees negative dihedral and therefore provided a signifiant favorable increment to direcional stbility of the model throughout mot of the tet angle-of-attack range. Author