By W. Austyn Mair, David L. Birdsall
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Extra info for Aircraft Performance (Cambridge Aerospace Series 5)
In general this 'parallel' condition may not be exactly satisfied and there will then be some variation of Vec with height and thrust setting. 9. The conditions for maximum rate of climb will be examined in Chapter 4 and at this stage only a brief discussion will be given, based on consideration of energy. In a climb at constant speed there is no change of kinetic energy and the energy added to the aircraft all appears as potential energy. The rate of increase of potential energy is WVC and this must be equal to the difference between the thrust power FV and the rate at which Introduction to climbing performance 23 energy is dissipated by drag DV.
E. when L = W. The speed Vc* is defined as the EAS for minimum /J when this condition is satisfied, but when y is not small and L = W cos y, the EAS for minimum )8 is different because it depends on the relation between/, y and /? 3). 15) becomes Then since PVe*2 = QVe*~2 = (PQ)V2 = (AT,A:2)1/2 = |/3 m , the general expression for the drag/lift ratio (with cos y = 1) becomes j8 = ^ m ( v 2 + u"2). 5 /! 5. Components of p/Pm for straight and level flight. 19) and of course all the results to be derived later in terms of v can be expressed in terms of nx if required.
10 shows that the maximum rate of climb occurs at an EAS greater than Vc*, with an angle of climb that is less than the maximum. The speed for maximum rate of climb increases as the available thrust increases, either because of reduced height (OA instead of OB) or because the throttle setting is higher as explained earlier. 10, with Ve = Vc*. 10. For propeller aircraft it is sometimes assumed that the shaft power transmitted to the propeller is independent of forward speed. e. minimum fiVe. 10, so that in practice the useful speed for maximum rate of climb may be rather greater than the speed for minimum pve.