2015
DOI: 10.5139/ijass.2015.16.1.8
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Numerical simulation of aerodynamic characteristics of a BWB UCAV configuration with transition models

Abstract: A numerical simulation for a nonslender BWB UCAV configuration with a rounded leading edge and span of 1.0 m was performed to analyze its aerodynamic characteristics. Numerical results were compared with experimental data obtained at a free stream velocity of 50 m/s and at angles of attack from -4 to 26°. The Reynolds number, based on the mean chord length, is 1.25×106. 3D multi-block hexahedral grids are used to guarantee good grid quality and to efficiently resolve the boundary layer. Menter's shear stress t… Show more

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Cited by 5 publications
(4 citation statements)
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“…We investigated the highly nonlinear behaviors of the aerodynamic force and moment coefficients in more detail from a physics perspective by analyzing flow field parameters including contours and streamlines. Figures 8,11,and 12 show the contours of the pressure coefficient and skin friction line, which we calculated streamline from the wall shear stress at three angles of attack (0°, 12°, and 16°) and three sideslip angles (0, 8, and 20°). We observed symmetric skin friction lines and pressure contours with respect to the wing root at a sideslip angle of zero (Figures 8(a), 11(a), and 12(a)), which is consistent with the simulation results of Park et al [24] which considered the geometry with half of the body irrespective of the sideslip angle.…”
Section: Flow Field Resultsmentioning
confidence: 99%
See 1 more Smart Citation
“…We investigated the highly nonlinear behaviors of the aerodynamic force and moment coefficients in more detail from a physics perspective by analyzing flow field parameters including contours and streamlines. Figures 8,11,and 12 show the contours of the pressure coefficient and skin friction line, which we calculated streamline from the wall shear stress at three angles of attack (0°, 12°, and 16°) and three sideslip angles (0, 8, and 20°). We observed symmetric skin friction lines and pressure contours with respect to the wing root at a sideslip angle of zero (Figures 8(a), 11(a), and 12(a)), which is consistent with the simulation results of Park et al [24] which considered the geometry with half of the body irrespective of the sideslip angle.…”
Section: Flow Field Resultsmentioning
confidence: 99%
“…The behavior of the vortex on this type of planform is sensitive to some parameters such as the swept angle [2,3], the sharp or rounded leading edge [4,5], the angle of attack and angle of sideslip, and the Reynolds number. Many experimental [4,6,7] and CFD (computational fluid dynamics) studies [5,[8][9][10][11] were conducted to understand the flow behavior including the leading edge vortex around the low swept delta wings. The vortical flow around the SACCON configuration was investigated through both wind tunnel experiments and numerical simulation by Schütte et al [12].…”
Section: Introductionmentioning
confidence: 99%
“…Chandrasekhara [10] assessed experimentally, in a wind tunnel, the aerodynamics of a UCAV (wingspan = 9 in). Jo et al [11] evaluated, through numerical simulations, the aerodynamic characteristics of a BWB-UCAV (wingspan = 0.7 m). The same BWB-UCAV used by Jo [11], has been tested experimentally in a wind tunnel in Shim and Park's work [12].…”
Section: Introductionmentioning
confidence: 99%
“…Jo et al [11] evaluated, through numerical simulations, the aerodynamic characteristics of a BWB-UCAV (wingspan = 0.7 m). The same BWB-UCAV used by Jo [11], has been tested experimentally in a wind tunnel in Shim and Park's work [12]. These works have focussed on the aerodynamics characterization of BWB-UAVs and UCAVs; however, they neither address the propulsion system integration with the airframe, nor BLI integration features.…”
Section: Introductionmentioning
confidence: 99%