Accession Number : AD1020455


Title :   Wind Tunnel Model and Test to Evaluate the Effectiveness of a Passive Gust Alleviation Device for a Flying Wing Aircraft


Descriptive Note : Technical Report,30 Sep 2014,31 Dec 2015


Corporate Author : Cranfield University Bedford United Kingdom


Personal Author(s) : Guo,Shijun ; Sensburg,Otto


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/1020455.pdf


Report Date : 04 Oct 2016


Pagination or Media Count : 104


Abstract : This report presents the work and results of Wind Tunnel Model and Test to Evaluate the Effectiveness of a Passive Gust Alleviation Device for a Flying Wing Aircraft. The gust response of the aircraft by using the PGAD integrated at the wing tip was analyzed in a procedure starting from design to numerical modeling and optimization. The previous results show that the PGAD leads to gust response reduction by 18 of the elastic deflection at wingtip, and 15 of the bending moment at the wing root respectively when the wing is constrained at root. For the aircraft with free rigid-body symmetric motion in transverse direction, the wingtip deflection and bending moment relative to the root is reduced by over 20 and 17 respectively. Based on the scaled wing model, a wind tunnel test was performed to validate the effectiveness of PGAD for gust alleviation. The model test results show that a maximum reduction of gust response by 9.4 can be achieved.Finally, the study was further extended to aeroelastic tailoring of the full-scale composite wing for minimum gust response. Together with the PGAD, 28.5 gust alleviation has been achieved.


Descriptors :   Wind tunnel models , test and evaluation , gusts , Tailless aircraft , wind tunnel tests , gust loads , wing tips


Distribution Statement : APPROVED FOR PUBLIC RELEASE