Aircraft Wind Tunnel Characterization using Modern Design of Experiments

Abstract

The present work focused on the full characterisation of a blended-wing-body UAV airframe recurring to a wind tunnel testing approach known as Modern Design of Experiments (MDOE). The results of this project are going to be applied in the design of a new control system for the aircraft. The tests were completed in a low-speed wind tunnel facility at Council for Scientific and Industrial Research (CSIR) in Pretoria, South Africa. The model was prepared for the wind tunnel tests, which included structural analysis, reinforcement and instrumentation. As part of the MDOE technique, the design of experiment of the test program was considered and analysed prior to the testing itself. The tests were then executed and the data collected and analysed. The final results consist in 12 models that fit the data for the six aerodynamic responses (2 per response): Lift, Drag, Side Force, Pitching Moment, Rolling Moment and Yawing Moment coefficients. All the models were extensively analysed using confirmation points. An example of significant systematic variation for the drag coefficients was detected and corrected. A study of the bias and tolerance trade-off resulting from the data correction for the wind tunnel influences was also conducted.

A novel aerodynamic modeling method for an axisymmetric missile with tiny units

“…where b :, l are the coefficients b 0 , b i , b 1i , and b ij . In this work, a regression model with a linear combination of p chosen functions f j can be used for equation (10). Then,ŷ l (x) can be rewritten aŝ…”

“…The kriging model contains a regression model F and a random function (stochastic process) 23 In this work, a regression model with a linear combination of p chosen functions f j can be used for equation (10). Then,ŷ l (x) can be rewritten aŝ…”

“…This problem promotes the development in the modern design of experiments (MDOE). 10,11 This approach can significantly reduce the testing numbers of WT and CFD and shorten the missile research cycle time. That is because a proper mathematic model which can represent the missile's aerodynamic characteristic well is applied to predict the aero data and to establish the aerodynamic database.…”