Wind Tunnel Model Design and Fabrication of a 5.75% Scale Blended-Wing-Body Twin Jet Configuration (Invited)

Dickey, Eric D.; Princen, Norman; Bonet, John; Ige, Gary K.

doi:10.2514/6.2016-0008

Cited by 10 publications

(6 citation statements)

References 1 publication

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“…The research model in this paper is a typical configuration of a BWB aircraft designed by the CARDC, which is similar to the model in reference [41]. It represents the basic characteristics of BWB layout, although the appearance and parameters are different.…”

Section: Bwb Aircraftmentioning

confidence: 99%

Geometric Effects Analysis and Verification of V-Shaped Support Interference on Blended Wing Body Aircraft

Xiao-hong

Liu

et al. 2020

Applied Sciences

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A special V-shaped support for blended wing body aircraft was designed and applied in high-speed wind tunnel tests. In order to reduce the support interference and explore the design criteria of the V-shaped support, interference characteristics and geometric parameter effects of V-shaped support on blended wing body aircraft were numerically studied. According to the numerical results, the corresponding dummy V-shaped supports were designed and manufactured, and verification tests was conducted in a 2.4 m × 2.4 m transonic wind tunnel. The test results were in good agreement with the numerical simulation. Results indicated that pitching moment of blended wing body aircraft is quite sensitive to the V-shaped support geometric parameters, and the influence of the inflection angle is the most serious. To minimize the pitching moment interference, the straight-section diameter and inflection angle should be increased while the straight-section length should be shortened. The results could be used to design special V-shaped support for blended wing body aircraft in wind tunnel tests, reduce support interference, and improve the accuracy of test results.

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Section: Bwb Aircraftmentioning

confidence: 99%

Geometric Effects Analysis and Verification of V-Shaped Support Interference on Blended Wing Body Aircraft

Xiao-hong

Liu

et al. 2020

Applied Sciences

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“…An investigation was conducted through a combination of numerical simulation and wind tunnel experimentation. The research model is a BWB aircraft (Figure 1), which is similar to the model in Grellmann, 18 Vicroy et al, 24 and Dickey et al 25 and can represent the typical characteristics of the BWB layout. The two flat inner flow channels are symmetrically mounted on the back of the fuselage and are independent of each other.…”

Section: Research Modelmentioning

confidence: 99%

“…24 The inner flow channel is usually mounted on the back of BWB fuselage; hence, the coupling effect of internal and external flows is serious. 25 The interaction between internal and external flows must be considered during the correction of test results. Consequently, the internal drag must be measured in the entire flow-through model.…”

Section: Introductionmentioning

confidence: 99%

Design and experimental validation of a specialized pressure-measuring rake for blended wing body aircraft’s unconventional inner flow channel

Xiao-hong

Liu

Cheng

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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The internal drag of the unconventional inner flow channel of blended wing body aircraft must be measured accurately to correct the air intake effect of the blended wing body flow-through model in wind tunnel tests. In this study, the pressure distribution of the inner flow channel under the interaction of internal and external flows was obtained through numerical simulation. A specialized pressure-measuring rake was designed based on the numerical results, and a validation test was conducted in a 2.4 m × 2.4 m transonic wind tunnel. Compared with the flow in traditional inlets/nozzles, the flow in the unconventional inner channel in the current research is asymmetric, the distortion index is higher, and the internal drag is more sensitive to flow changes. The wind tunnel test results have a good correlation with the numerical results, and the repeatability of the test results is satisfactory, indicating that the measurement accuracy and precision of the pressure-measuring rake are acceptable. The design method of the specialized rake is feasible, and it can be used to guide the measurement of complex flow in unconventional inner flow channels of blended wing body aircraft.

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“…The gap between trailing edge of the Krueger and the main element was varied during acoustic testing and was denoted by a matrix type notation as shown in Figure 2(a). Following this notation, a leading-edge Krueger configuration with a 40 deflection and the smallest gap, is denoted by 40 (3,3). Two leading-edge Krueger shapes were tested; the aerodynamic baseline and the acoustic Krueger are shown in Figure 2(b).…”

Section: Test Modelmentioning

confidence: 99%

“…The leading-edge Krueger and brackets were removed for the model cruise configuration. More details on the model development can be found in Dickey et al 3…”

Section: Test Modelmentioning

confidence: 99%

Phased acoustic array measurements of a 5.75% hybrid wing body aircraft

Burnside

Horne

Elmer

et al. 2017

International Journal of Aeroacoustics

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Detailed acoustic measurements of the noise from the leading-edge Krueger flap of a 5.75% hybrid wing body aircraft model were acquired with a traversing phased microphone array in the Arnold Engineering Development Complex NFAC 40-by 80-foot wind tunnel. The spatial resolution of the array was sufficient to distinguish between individual support brackets over the full-scale frequency range of 100 to 2875 Hz. For conditions representative of landing and takeoff configuration, the noise from the brackets dominated other sources near the leading edge. Inclusion of flight-like brackets for select conditions highlights the importance of including the correct number of leading-edge high-lift device brackets with sufficient scale and fidelity. These measurements support the development of a Krueger noise model which includes cove and bracket noise.

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Wind Tunnel Model Design and Fabrication of a 5.75% Scale Blended-Wing-Body Twin Jet Configuration (Invited)

Cited by 10 publications

References 1 publication

Geometric Effects Analysis and Verification of V-Shaped Support Interference on Blended Wing Body Aircraft

Geometric Effects Analysis and Verification of V-Shaped Support Interference on Blended Wing Body Aircraft

Design and experimental validation of a specialized pressure-measuring rake for blended wing body aircraft’s unconventional inner flow channel

Phased acoustic array measurements of a 5.75% hybrid wing body aircraft

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