DID YOU KNOW? DTIC has over 3.5 million final reports on DoD funded research, development, test, and evaluation activities available to our registered users. Click
HERE to register or log in.
Accession Number:
ADP002268
Title:
The Effects of Wing Tip Devices on the Performance of the BAe (British Aerospace) Jetstream,
Descriptive Note:
Corporate Author:
BRITISH AEROSPACE PLC WOODFORD (ENGLAND)
Report Date:
1983-07-01
Pagination or Media Count:
11.0
Abstract:
The formation of a strong tip vortex has an undesirable effect on the drag of a lifting surface. Firstly, it induces a strong downwash field locally which increases the vortex drag and secondly introduces a strong cross flow around the tip causing separation on the top surface. Tip devices seek to remove these effects. Sails unwind the tip vortex and in doing so experience a thrust, like stators behind a fan. Their nose to tail arrangement gives them the ability to carry high lift coefficients, in the manner of cascades or slotted aerofoils. Winglets, or tip fins attenuate the tip vortex by dissipating the shed vorticity along their length, thereby reducing the downwash induced at the wing tip region. In order to asses these effects, it was proposed that a 110th scale model of a BAe Jetstream Figure 1 should be tested at Cranfield Institute of Technology in the 8 x 6 low speed wind tunnel with sails and winglets. The first objective of the tests was to demonstrate a measurable drag reduction for a Jetstream fitted with tip devices over the range of operational lift coefficients. The second objective was to estimate the increase in wing root bending moment due to either device in order to compare their relative merits with simple tip extensions. In the past this had been done with wing only half model with encouraging results, but an estimate for the complete aircraft configuration was highly desirable.
Distribution Statement:
APPROVED FOR PUBLIC RELEASE
