Oscillating 65 Deg. Delta Wing, Numerical PDF Download

Author: Willy Fritz
Publisher:
ISBN:
Category :
Languages : en
Pages : 6

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Book Description
This data set consists of steady and unsteady numerical solutions of a sharp-edged cropped delta wing with a leading edge sweep of 65 undergoing a pitching oscillation. The geometry of the wing corresponds with the geometry of the wind tunnel model described in the previous data set (chapter 17B), the difference being the absence of the fuselage in the numerical model. The presence of the fuselage on the upper surface flow is believed to have an effect at small angles of attack only on the forward region of the wing and to have an effect on the location of vortex breakdown at large angles of attack. The pitching oscillation has an amplitude of 3 deg, the mean angle of attack is 9'. The position of the oscillation axis and the reduced frequency have been set to match one of the reduced frequencies of the aforementioned experiment, while the Mach number & has been increased from the experiment's Mach number 0.12 to 0.4 to reduce computational time. The data set includes field solutions from Euler as wellt as from Reynolds averaged Navier-Stokes (RANS) calculations for four equidistant instants within one oscillation cycle and for the corresponding static solution (a = 9'). Comparison of the Euler and RANS solutions shows the well known differences in strength and spanwise location of the primary vortex-induced suction peak due to the absence of a secondary vortex in the Euler solution. The agreement with the experimental results is very good.