Preliminary Study on Lift Coefficient of Biplane Airfoil in Smoke Wind Tunnel

Kashitani, Masashi; Yutaka, Yamaguchi; Kai, Yoshiharu; Hirata, Kenichi; Kusunose, Kazuhiro

doi:10.2514/6.2008-349

Cited by 10 publications

(6 citation statements)

References 5 publications

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“…Recently, Kusunose proposed using the Busemann's biplane concept to the next generation supersonic transport design. His research group carried out a series of studies including both computational fluid dynamic (CFD) methods and wind-tunnel experimental methods [7][8][9][10][11][12][13][14][15][16].…”

Section: Introductionmentioning

confidence: 99%

Adjoint-Based Aerodynamic Optimization of Supersonic Biplane Airfoils

Jameson

Wang

2012

Journal of Aircraft

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This paper addresses the aerodynamic performance of Busemann type supersonic bi-plane at off-design conditions. An adjoint based optimization technique is used to optimize the aerodynamic shape of the biplane to reduce the wave drag at a series of Mach numbers ranging from 1.1 to 1.7, at both acceleration and deceleration conditions. The optimized biplane airfoils dramatically reduces the effects of the choked flow and flow-hysteresis phenomena , while maintaining a certain degree of favorable shockwave interaction effects at the design Mach number. Compared to a diamond shaped single airfoil of the same total thickness, the wave drag of our optimized biplane is lower at almost all Mach numbers, and is significantly lower at the design Mach number.

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Section: Introductionmentioning

confidence: 99%

Adjoint-Based Aerodynamic Optimization of Supersonic Biplane Airfoils

Jameson

Wang

2012

Journal of Aircraft

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“…Figure 7(a) shows the lift coefficient results obtained by the flow pattern technique and numerical simulation. The calculation method based on sc in the case of flaps was clarified in the previous studies [5] [6]. In this study, the lift coefficient results were obtained using the modified Yamana's method based on the height y s , as were the airfoil baseline's results in Figure 6(a).…”

Section: Estimation Of Lift Coefficientmentioning

confidence: 98%

“…Since the distance of y s is larger than sc, it is considered that the measurement of y s can obtain a better resolution, and the measurement of y s is easier than sc. where sc cal is the displacement of the center of pressure obtained from the Equations (4) and (5). The value y s can be directly measured by G3 data software from the pictures.…”

Section: Estimation Of Lift Coefficientmentioning

confidence: 99%

“…In the study, the method was applied to investigate the lift characteristics of a double-wedge airfoil and modified double-wedge airfoil [4]. To take into account the displacement of the center of pressure when a small high-lift device is attached to the airfoils, Kashitani et al [5] [6] and Nguyen et al [7] [8] calculated the lift coefficient by modified Yamana's method that considered the displacement (sc) of the center of pressure in the streamwise direction. The methods of obtaining the lift coefficient from sc and from y s are both included in the original Yamana's method [1].…”

Section: Introductionmentioning

confidence: 99%

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Low-Speed Aerodynamic Characteristics of Supercritical Airfoil with Small High-Lift Devices from Flow Pattern Measurements

Duong¹,

Kashitani²,

Taguchi³

2020

JFCMV

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In this paper, the lift coefficients of SC-0414 airfoil are estimated by applying modified Yamana's method to the flow visualization results, which are obtained by utilizing the smoke tunnel. The application of the modified Yamana's method is evaluated with two calculation methods. Additionally, the lift estimation, wake measurements, and numerical simulations are performed to clarify the low-speed aerodynamic characteristics of the SC airfoil with flaps. The angle of attack was varied from −5˚ to 8˚. The flow velocity was 12 m/s and the Reynolds number was 1.6 × 10 5. As a result, the estimated lift coefficients show a good agreement with the results from reference data and numerical simulations. In clean condition, the lift coefficients calculated from the two methods show quantitative agreement, and no significant difference could be confirmed. However, the slope of the lifts calculated from y s is higher and closer to the reference data than those obtained from sc, where y s denotes the height where the distance from the streamline to the reference line is the largest, and sc denotes the displacement of the center of pressure from the origin of the coordinate, respectively. In the case of flaps, the GFs have an observable effect on the aerodynamic performance of the SC-0414 airfoil. When the height of the flap was increased, the lift and drag coefficients increased. The installation of a GF with a height equal to 1% of the chord length of the airfoil significantly improved the low-speed aerodynamic performance of SC airfoils.

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“…Qualitative flow characteristics, mainly the effect of shock wave -expansion wave interference, are obtained indirectly by using schlieren visualization on wind tunnels, and the resulting images are later compared to CFD calculations, [6][7][8][9]. Smoke based visulaization in combination with force measurements has also been applied, with the aim to investigate the biplane behaviour at liftoff or nondesign conditions, [9,10]. The pressure distribution on the surface of the biplane has been experimentally measured by pressure and temperature sensitive paints, [7,8,11], and in the work of Saito et al some boundary layer effects were observed.…”

Section: Introductionmentioning

confidence: 99%

Review of background oriented schlieren and development for ballistic range applications

Gojani

Kamishi

Obayashi

2013

EPJ Web of Conferences

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Abstract. Quantitative measurements of fluid flow can be achieved by flow visualization techniques, and this paper reviews and outlines background oriented schlieren, with emphasis on its performance: measurement sensitivity and uncertainty. Since the technique depends on cross-correlation, an assessment of image evaluation is also conducted. Background oriented schlieren is applied to two flows: shock reflection from a wedge in a shock tube, and natural cooling by convection. It is estimated that the technique can be applied to ballistic facilities.

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Preliminary Study on Lift Coefficient of Biplane Airfoil in Smoke Wind Tunnel

Cited by 10 publications

References 5 publications

Adjoint-Based Aerodynamic Optimization of Supersonic Biplane Airfoils

Adjoint-Based Aerodynamic Optimization of Supersonic Biplane Airfoils

Low-Speed Aerodynamic Characteristics of Supercritical Airfoil with Small High-Lift Devices from Flow Pattern Measurements

Review of background oriented schlieren and development for ballistic range applications

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