Experimental and Numerical Study of Side-Slipping 65-deg Delta and Double-Delta Wings
Farooq Saeed
Farooq Saeed, Department, Aerospace Engineering King Fahd University of Petroleum & Minerals, Dhahran, Saudi Arabia.
Manuscript received on November 25, 2014. | Revised Manuscript received on December 03, 2014. | Manuscript published on December 30, 2014. | PP: 214-221 | Volume-4 Issue-2, December 2014. | Retrieval Number: B3630124214/2013©BEIESP
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© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)
Abstract: The paper presents the results of an experimental and numerical investigation to determine aerodynamic characteristics in terms of lift, drag, side force, pitching moment, yawing moment and rolling moment coefficients for 65-deg delta and 65/40-deg double-delta wings at various pitch and sideslip angles. The study was carried out due to scarcity of such data in literature. The experimental tests were conducted at the KFUPM low-speed wind tunnel facility whereas the numerical tests were performed using the commercial CFD software FLUENT. Results for zero sideslip angles from both experiments and numerical predictions were compared with experimental data found in literature as well as to the theory of Polhamus. The comparison of force and moment data, surface pressure coefficient distribution and vortex breakdown location show good agreement with experiments and CFD predictions found in literature as well as theoretical calculations at zero sideslip angles. Experimental and computational results for non-zero sideslip angles at various pitch angles were then determined and have been reported in this study.
Keywords: Delta wing, Double delta wing, Sideslip, Vortex lift, Vortex breakdown.