Accession Number : ADP005858

Title :   Wing Divergence of Trimmed Aircraft,

Corporate Author : ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (UNITED KINGDOM)

Personal Author(s) : Niblett, T.

Report Date : 03 OCT 1986

Pagination or Media Count : 9

Abstract : By means of a simple theoretical model it is shown that wing divergence of a free aircraft can be defined using the static case of trimmed level flight. The same model also shows that the control angle per 'g' goes to zero at a speed near the fixed-root divergence speed and that there is a large change in the spanwise distribution of airload in going from a low speed to speeds above that of fixed-root divergence.

Descriptors :   *AERODYNAMIC LOADING, *TRIM(AERODYNAMICS), *WINGS, LOAD DISTRIBUTION, AEROELASTICITY, SWEPTFORWARD WINGS, FLIGHT SPEEDS, GREAT BRITAIN.

Subject Categories : Aerodynamics

Distribution Statement : APPROVED FOR PUBLIC RELEASE