Studies of winglet effect on lift Induced drag in aircraft model

Abstract

An aircraft wingbodytail model of suitable size was fabricated so newlineas to fit into the testing wind tunnel The criterion for the model size was that newlineits blockage ratio less than 5 The model was tested using subsonic wind newlinetunnel available at the Department of Aerospace Engineering Madras newlineInstitute of Technology India The test section size of the low speed wind newlinetunnel is 3ft x 4ft and length 6ftThe wind tunnel was calibrated before testing newlinethe model to improve the accuracy of data Pressure transducer Digital Sensor newlineArray DSA which converts pressure to digital using analogue to digital newlineconverter was used It is a temperature compensated device with 16 ports The newlineaircraft model was given internal cavity to accommodate three component newlineinternal balances The balance was connected to sting which in turn was newlineconnected to automated model mounting mechanism newline newline