Accession Number : ADA046152


Title :   Design and Analysis of Winglets for Military Aircraft. Phase 2


Descriptive Note : Final rept. Jun-Nov 1976


Corporate Author : BOEING COMMERCIAL AIRPLANE CO SEATTLE WA


Personal Author(s) : Ishimitsu, K K ; Zanton, D F


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a046152.pdf


Report Date : May 1977


Pagination or Media Count : 131


Abstract : 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.


Descriptors :   *WING TIPS , *SWEPTBACK WINGS , MATHEMATICAL PREDICTION , MODEL TESTS , TANKER AIRCRAFT , AERODYNAMIC CHARACTERISTICS , WIND TUNNEL TESTS , FUEL CONSUMPTION , JET TRANSPORT AIRCRAFT , WINGS , FLIGHT SIMULATION , RETROFITTING , DRAG REDUCTION , EXTENDABLE STRUCTURES , MILITARY AIRCRAFT , MODIFICATION


Subject Categories : Transport Aircraft


Distribution Statement : APPROVED FOR PUBLIC RELEASE