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By N.F. Krasnov

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Additional info for Aerodynamics: Fundamentals of Theory, Aerodynamics of an Airfoil and Wing; Methods of Aerodynamic Calculation

Sample text

1') and my (~). Let us consider static rolling stability. Assume that in steady motion at the angle of attack ad the craft is turned about the axis Ox through a certain rolling angle 1'. This turn with a constant orientation of the axis Ox relative to the velocity vector V canses the appearance of the angle of attack a ~ ad ~os l' and the sideslip angle ~ ~ ad sin 1'. The slip, in turn, causes a rolling moment to appear whose coefficient mx = m~fJ ~ m~ad sin 1'. Differentiating with respect to 1'.

And also 011 tile physicochemical procel"ses that Illay proceed in it was disregarded. For \'Cry high (hypprsollic) speeds. howeypI', the featmes associated with thp influencp of high temperatures come to the forefront. High temperatures appear owing to clpceleration of thp gas stream whell the kinetic energ',\' of ordered motion of the particles transforms into the internal energy of the gas. 'vels of till' intprnal ellNgy of the oxygPI1 and nitrogen molecllles in the air become:- noticeable. At a tpmperatnre of about 3000 K and a pressurp of t0 5 Pa.

I. Theory. 0 I\. 4 \ Fig. 17) where n1Z0 is the coeffieient of the moment about a point on the leading edge at c y = 0 (Fig. 6). 17) determines the increment of the moment associated with a change in the normal-force coefficient. If we choose the point Fa on a chord whose coordinate Xn = XF tl is determined by the condition (see Fig. 18) the coefficient of the moment about this point will not depend on and at all (small) angles of attack it will be a constant quantity. This pcint is Cil1led the aerodynamic centre (AC) of the given body.

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