Aircraft performance by Maido Saarlas

By Maido Saarlas

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To find this point on the drag curve, any one of the drag expressions given above, say Eq. 26) Substituting Eq. 26 back into the drag equation Eq. 27) which states that the minimum drag occurs when the parasite and induced drags are equal and it is independent of altitude. From the drag coefficient, Eq. 18, it follows then, since both of the drag terms are equal (this can be seen also from Fig. 29) Since the minimum drag occurs at the minimum value of D/L, the latter ratio can be determined immediately by use of Eqs.

The drag has been calculated from Eq. 4 for the aircraft weight ranging from 10,000 to 14,000 lb. Also shown are the individual curves for the induced and parasite drags for a weight of 10,000 lb. 2). 375 ϭ 893 ft/sec Also, the ceiling can be read off directly where the (imaginary) thrust line is tangent to 12,000 lb drag curve—at about 41,000 ft. Determining the other results such as rate of climb, a more precise ceiling, and so on, will be discussed later in appropriate chapters. 40 THE BASICS The Aproximate Approach This method provides quick results with less labor but also with a possible loss of accuracy.

This restates the conclusion already obtained that one of the nondimensional velocities must be larger than, and the other smaller than, unity. Thus, if one solution is known, the other can be easily found from this condition. 48) Substituting for the thrust from Eq. 49) Caution should be exercised in applying Eq. 3a and Appendix D). The maximum velocity can be calculated from V2. Substituting T and recalling the definition of V, one obtains from Eq. 50) Eq. 50 gives the maximum velocity, at a given altitude, for given T, W, S, k, CD.

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