Experimental and numerical investigation of 65-deg delta and 65/40-deg double-delta wings in sideslip

In this study, an experimental and numerical investigation is being carried out to obtain lift, drag, side force, pitching moment, yawing moment and rolling moment data for 65-deg delta and 65/40-deg double-delta wings at various pitch and sideslip angles. The experimental tests were conducted at the KFUPM low-speed wind tunnel facility whereas the numerical tests are being performed using the commercial CFD software FLUENT. Results for zero sideslip angles from both experiments and numerical predictions were compared to other experimental data found in literature as well as to the theory of Polhamus. The results of comparison of surface pressure coefficient distribution and vortex breakdown location show good agreement with experiments. Overall the comparison of result shows good agreement between different experimental studies as well as good agreement with the CFD predictions and the theoretical calculations at zero sideslip angles. Experimental results for various pitch and sideslip angles have been completed and included in this abstract. Numerical computations for non-zero sideslip angles are currently underway and will be included in the final paper. An extended abstract of the work that has been accomplished is given in the following sections.