By Maido Saarlas
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Extra resources for Aircraft performance
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.