The theory (wing experiments in an artificial air stream are subject to error, due to the fact that the wing is not situated in an unlimited body of air) by means of which the given drag correction was obtained, was based on various assumptions (e.g., elliptical distribution of lift) which do not always hold true. For this reason it was desirable to test the equation for the additional drag in regard to its reliability and range of application.
Wind tunnel tests of correction formula for wings of large span
1924-05-01
Miscellaneous
No indication
English
Supersonic wind-tunnel flutter tests of two rectangular wings
TIBKAT | 1958
|Wind-tunnel investigation of wings with ordinary ailerons and full-span external-airfoil flaps
Engineering Index Backfile | 1937
|Wind-tunnel investigation of tapered wings with ordinary ailerons and partial-span split flaps
Engineering Index Backfile | 1937
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