Review of theoretical work done at Royal Aircraft Establishment, which was limited to case of zero incidence; results do not depend on lift theories, and belong entirely to field of classical hydrodynamics; method used is that of sources and sinks and is really linear perturbation theory for thin airfoils.
Critical mach numbers for swept-back wings
Aeronautical Quarterly
Aeronautical Quarterly ; 2 , Part 2
1950
26 pages
Aufsatz (Zeitschrift)
Englisch
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Critical Mach Number Prediction on Swept Wings
AIAA | 2017
|Critical Mach Number Prediction on Swept Wings (AIAA 2017-0266)
British Library Conference Proceedings | 2017
|Engineering Index Backfile | 1950
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