Wing ceases to deflect after application of its normal maximum load. This is accomplished by means of an internal bracing system which only comes into operation when maximum deflection has been reached.
The parker variable camber wing
Nat. Advisory Committee Aeronautics, report
1920
41 pages
25 Figs.
Report
English
© Metadata Copyright Elsevier B. V. All rights reserved.
The Parker Variable Camber Wing
NTRS | 1920
|NTIS | 1973
NTIS | 1973
NTIS | 1973
Variable wing area and variable camber
Engineering Index Backfile | 1920
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