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Rectilinear Flight in a Non-Uniform Atmosphere
Published online by Cambridge University Press: 04 July 2016
Extract
The equations showing how to correct for the effect of non-uniformity of the Atmosphere when computing the angle-of-climb (or descent) are well known and can be found in Refs. 1 and 2.
From Ref. 1, a climb at constant Mach number M implies a factor F on the Aircraft Weight to give the true angle-of-climbs (in our units for R) given by the expression
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