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The balance of moments and the static longitudinal stability of airplanes (1929)
NASA Technical Reports Server (NTRS) · leaf 16
Fig-8 0- -2- < —a CD bD to -6-1 I o Q -8- -10-I 7°^ Moment coefficient, Cjjj Demanded: M-t=Mii=0 for CL(.=0° ^^io.33 Required: l.x:t=0.44 2-<^theor=^+^^ =0°-3..9°=-2.9 •^•^hO tlieor=ci-to-^- -7°+2.90=-4.1° . Tail lift coef f icient, c.,h 1.0 … Tail angle of attack,aJJ ^-^g^j. Fig.8 Stability nomogram.NASA Technical Reports Server (NTRS)
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