Response surface smoothing for wind tunnel testing based on design of experiment with subspace partitioning

This paper presents a new approach in resolving discontinuities between subspaces when the subspace partitioning method is applied to measure aerodynamic coefficients. The discontinuities between response surfaces in each subspace are hard to resolve in an analytical method, but it can be smoothened by overlapping between subspaces and integrating with proper interpolation. The traditional One Factor at a Time (OFAT) method is used for gathering aerodynamic force and moment coefficient data before applying the Design of Experiments (DOE) method for the purpose of later validation of the suggested method. In each subspace, the Central Composite Design (CCD) is used to reduce experimental points. The Separated Response Surface Model compared to the Integrated Response Surface Model. Quality of fit of the Developed Integrated Model calculated with OFAT data for validation. The test model base is the lambda wing configuration of the UCAV 1303. The study was carried out at the low speed wind tunnel of the Agency for Defense Development (ADD-LSWT).