Flow Control and High-Lift Performance for Flying-Wing Unmanned Combat Air Vehicle Configurations by inserting slots

Ali, Usman; Chadwick, EA

doi:10.21152/1750-9548.10.2.117

Cited by 2 publications

(5 citation statements)

References 13 publications

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“…A similar behavior was observed in the study of Ali and Chadwick [45]. Hence, it can be concluded that the present numerical model is sufficient to study the aerodynamic performance of lambda wing models.…”

Section: B Validationsupporting

confidence: 88%

“…The present study examines the aerodynamic characteristics of constant and non-constant LE sweep angle lambda wing configurations using OpenFOAM for various AOA. The parameters such as coefficients of lift ( ), drag ( ) and pitching moments ( ) are compared with the experimental data of Ali and Chadwick for validation [45]. coefficient reduces with an increase in AOA, and they exhibit a larger deviation from experimental data at higher AOA.…”

Section: B Validationmentioning

confidence: 99%

“…Based on the above discussion, it is evident that the LE sweep angle is a critical parameter that affects the aerodynamic performance of UCAV wings. Furthermore, the performance, signature, and weight considerations of the real UCAVs often result in adopting planforms with swept edge-aligned of (40 ≤ Λ ≤ 60 ) [25,[44][45][46] with associated medium aspect ratios, which are adequate to induce LE vortex separations during the maneuver, nevertheless less than conventional slender wing values [40]. However, the UCAVs must operate in complex conditions and expand their maneuvering envelope to higher AOA.…”

mentioning

confidence: 99%

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Numerical Investigations on Low-Speed Aerodynamic Characteristics of Generic Unmanned Combat Aerial Vehicle Configurations

Aleisa

Kontis

Nikbay

2023

Journal of Aircraft

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The leading-edge sweep angle significantly influences the flight performance of swept wings. The vortex flow structures affect the flow behavior of the moderate to highly swept wings, which form at low angles of attack because of leading-edge flow separation. This topic of investigation gained momentum due to its application to unmanned combat aerial vehicle (UCAV) configurations that are significantly affected by flow separation at high angles of attack. The present work investigates the flowfield and low-speed aerodynamic characteristics of the generic UCAV models with a constant and nonconstant leading-edge sweep for a wide range of angles of attack. The open-source computational fluid dynamics code OpenFOAM 8.0 is employed for the numerical simulations. The present numerical simulation results agree well with the experimental data in the literature. It is demonstrated that the lift and drag characteristics of the UCAV are sensitive to the leading-edge sweep angle, and a nonconstant leading-edge sweep angle variant exhibits delayed stall and enhanced aerodynamic performance.

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Section: B Validationsupporting

confidence: 88%

Section: B Validationmentioning

confidence: 99%

mentioning

confidence: 99%

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Numerical Investigations on Low-Speed Aerodynamic Characteristics of Generic Unmanned Combat Aerial Vehicle Configurations

Aleisa

Kontis

Nikbay

2023

Journal of Aircraft

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“…Generally, the numerical results are compared with experimental or analytical results for validation. As the current UCAV model lacks experimental results at the moment, for validation, the generic lambda wing models at the low speed [21] and SACCON, DLR-F17E models at high speed [50] are compared with their corresponding experimental results following the same numerical approach adapted for the present UCAV model. As shown in (Fig.…”

Section: Validation Of the Numerical Approachmentioning

confidence: 99%

“…The UCAV configurations used in military applications must operate in a high-threat environment with sufficient operating range, endurance, and manoeuvrability which is appropriate for long-distance attacks, great depth, and stealth penetrations. Most of the UCAV conceptual designs available in the literature [7][8][9][10][11][12][13][14][15][16][17][18][19][20] are tailless flying wing configurations with a low to moderate aspect ratio (AR), internal weapon carriage, concealed propulsion systems, absence of high lift devices, and moderate to high leading-edge (LE) sweep angle edge-aligned wings (40 ≤ Λ ≤ 60 deg) [21,22]. However, the design of UCAV configurations is a complex task because it requires a high level of integration within the subsystems combined with vorticial flow structures.…”

mentioning

confidence: 99%

Conceptual Design of a Nonconstant Swept Flying Wing Unmanned Combat Aerial Vehicle

Aleisa¹,

Kontis²,

Pirlepeli³

et al. 2023

Journal of Aircraft

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The design of unmanned combat aerial vehicles (UCAVs) is primarily governed by the low-observability requirement for military applications rather than aerodynamic performance. The conceptual design and optimization of UCAV models via size and shape variables for different missions in different flow regimes form a research area for military vehicle design. Flying wing UCAVs experience flow separation during takeoff and landing, and furthermore exhibit stability issues. The aerodynamic performance of these UCAVs can be significantly improved by redesigning their leading-edge sweep angle and wing planform. In the present work, the initial weight determination, aerodynamic sizing, and planform with and without inlet lip integration, and the conceptual design of a nonconstant leading-edge flying wing UCAV configuration are performed. Next, the obtained conceptual design is downscaled 1:20 to be used as a wind-tunnel model and optimized for low-speed conditions using a kriging-based surrogate model with a vortex-lattice method to maximize the lift-to-drag ratio. Later, the optimized design is validated using an open-source computational fluid dynamics code, OpenFOAM 8.0, to verify the accuracy of the surrogate model and to investigate the aerodynamic characteristics. The optimized UCAV design exhibited improved aerodynamic characteristics in terms of the lift-to-drag ratio. Furthermore, the aerodynamic performance and flowfield of the optimized UCAV model with and without inlet lip integration have been evaluated at low and high speeds.

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Flow Control and High-Lift Performance for Flying-Wing Unmanned Combat Air Vehicle Configurations by inserting slots

Cited by 2 publications

References 13 publications

Numerical Investigations on Low-Speed Aerodynamic Characteristics of Generic Unmanned Combat Aerial Vehicle Configurations

Numerical Investigations on Low-Speed Aerodynamic Characteristics of Generic Unmanned Combat Aerial Vehicle Configurations

Conceptual Design of a Nonconstant Swept Flying Wing Unmanned Combat Aerial Vehicle

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