A study of the design and analysis of winglets for military aircraft has been completed. This study is a continuation of the work reported in AFFDL-TR-76-6. The program consisted of investigating analytically the AFFDL/Boeing winglet on the take-off and landing configuration of the KC-135A. Also investigated analytically were th effect of a wing leading-edge device on the performance of the AFFDL/Boeing winglet and the design of a compromise high-speed/low-speed winglet. Two wind tunnel tests were conducted by the NASA-Langley Research Center 8-foot transonic tunnel. A high-speed and low-speed test were conducted to determine the effect of the AFFDL/Boeing winglets on the KC-135A's aerodynamic performance and longitudinal and lateral-direction stability. A preliminary plan for a KC-135A winglet retrofit program was developed and its cost estimated. Based on a 1979 program start, the retrofit costs would be recovered by the start of 1984.
Design and Analysis of Winglets for Military Aircraft. Phase II
1977
134 pages
Report
No indication
English
Aircraft , Aerodynamics , Wing tips , Sweptback wings , Fuel consumption , Retrofitting , Wind tunnel tests , Flight simulation , Modification , Model tests , Aerodynamic characteristics , Drag reduction , Wings , Jet transport planes , Extendable structures , Mathematical prediction , Military aircraft , Tanker planes , Winglets , KC-135A aircraft , Induced drag , C-135 aircraft
Design and Analysis of Winglets for Military Aircraft
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