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Rectilinear Flight in a Non-Uniform Atmosphere

Published online by Cambridge University Press:  04 July 2016

R. H. W. Annenberg
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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

Type
Technical Notes
Information
The Aeronautical Journal , Volume 66 , Issue 613 , January 1962 , pp. 53 - 54
Copyright
Copyright © Royal Aeronautical Society 1962

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References

1.Control and Stability of Aircraft. Duncan: C.U. Press.Google Scholar
2. Royal Aeronautical Society Data Sheets; Performance: EG3/1.Google Scholar