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By N.F. Krasnov

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Pb < pool. Characteristic Geometric DimE'nsions. The absolute value of an aerodynamic coefficient. which is arbitrary to a certain extent. Ch. 1. -c~ntr" 45 vicw of a wing: chord, bt-till lind b-Iocal chord chord. depends on the choice of the characterigtic geometric dimensions S rand L. e practical calculations. however, a characterb~ tic geometric quantity is dlOsen beforehand. In aerogpace technology, the area of the mid-section (the largest cross section) of the body Sr = SlIllri is usually chosen ag the characteristic area, and the length of the rocket is taken as the characteristic linear dimension L.

For this purpose, one mnst use the relations C1Sl = C 2 S 2 (for the force coeflicients). and TnISIL I = Tn 2S 2 {'2 (for the moment coefficients) obtained from tilC conditions of th(' constancy 46 Pt. I. Theory. Aerodynemics 01 en Air/oil end eWing Fill. l Constructing 8 "polar of the first kind of a craft: a-e'l'a vs. I-Cyll. vs. a; c-polsr ot hrst kind of the forces and moments acting on the same craft. These relations are used to fmd the coefficients C 2 and m 2 , respectively, converted to the new characteristic dimensions 8 2 and L 2: c2 = c1 (8 1 /8 2 ), m 2 = ml (8 1 L I /8 2L 2) where the pr~vious dimensions 8 1 , L] and aerodynamic coefficients c1 ' ml , as well as the new dimensions 8 2 , L2 are known.

Are the same, the quantity K equals the slope of a vector drawn from the origin of Coor(JiIf the scales of eVA Ch. I. ' ~ " '. UA 'x ))rag polar or the second kind nates (the pole) to the point of the polar diagram corresponding to the· chosen angle of attack. We can usc a polar to determine tbe optimal angle of attack "oPt corresponding to the maximum lift·lo-drag ratio: K maz = tan "oPt (CUO')· if we draw a tangent to the polar from the origin of coordinates. d is achieved nl. amlll and tht' corresponding values of the angle of all lick and the lift coeflicient.

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