By Maido Saarlas
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Eq. 6 also establishes the well-known relationship V 2CL ϭ 2W ϭ const S for a constant altitude (and fixed W) flight. 2 STALLING SPEED 21 The force balance along the flight path, Eq. 8) Eq. 7 is the thrust required for level unaccelerated flight. Eq. 5 shows that, for a given altitude, the lift depends only on the lift coefficient and the velocity. However, for a fixed weight and altitude, a flight attitude exists that gives a maximum value to the lift coefficient CL max (although the latter depends also on lift augmentation devices like flaps and slats), which, in turn, indicates a minimum flight velocity in order to satisfy the above equation.
Increasing W, n, S, and CD0 increases the drag and curves shift upward. Thus, the drag curve depends on five parameters, out of which only the reference area S will usually remain constant during the flight. Although n is unity for steady level flight, as considered in most of these chapters, it will be included here explicitly for basic development. This will permit an easy transfer to other cases in later chapters. 1 Total Drag, Induced Drag, and Parasite Drag V 30 THE BASICS For low-speed flight regime (where the Mach number effects can be ignored), it is convenient to rewrite Eq.
Eq. 5 shows that, for a given altitude, the lift depends only on the lift coefficient and the velocity. However, for a fixed weight and altitude, a flight attitude exists that gives a maximum value to the lift coefficient CL max (although the latter depends also on lift augmentation devices like flaps and slats), which, in turn, indicates a minimum flight velocity in order to satisfy the above equation. 9) L max Eq. 9 represents the minimum flight velocity at which steady sustained flight is possible. It depends on the altitude, maximum lift coefficient, and, to some extent, on power at high angle of attack that must be determined experimentally.
