Effect of ground on flow characteristics and aerodynamic performance of a non-slender delta wing

Tümse, Sergen; Tasci, Mehmet Oguz; Karasu, İlyas; Şahi̇n, Beşi̇r

doi:10.1016/j.ast.2020.106475

Cited by 24 publications

(7 citation statements)

References 32 publications

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“…In order to simplify the problem, only the internal flow characteristics of the inlet during pitch maneuver and yaw maneuver are investigated [41][42][43]. In the course of pure pitch maneuver with constant incoming flow conditions, the angle of attack of the aircraft is equal to the angle of pitch; The angle of attack of the aircraft is equal to the sideslip angle during the simple yaw maneuver with the inflow conditions unchanged.…”

Section: Analysis Of Transient Flow Characteristicsmentioning

confidence: 99%

Internal Aerodynamic Performance Enhancement for Aircraft with High Maneuver by Designing a Distributed Submerged Inlet

Zhang

2023

Applied Sciences

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Submerged inlet has been widely used in UAVs and cruise missiles due to its good stealth characteristics, but it also brings the disadvantage of poor aerodynamic characteristics. Especially in large maneuvering flight, the flow field near the fuselage has a strong unsteady effect, and the total pressure recovery coefficient and distortion characteristics have deteriorated sharply. In order to investigate the steady and transient aerodynamic characteristics of the submerged inlet in large maneuver flight and improve its maneuver envelope, a design scheme of a distributed submerged inlet for large maneuver flight is proposed in this paper. Taking a cruise missile as the research object, the steady and transient analysis of the conventional submerged inlet and the distributed submerged inlet is carried out using CFD numerical method. The results show that the distributed submerged inlet can significantly improve the inlet performance and enhance the sideslip limit of the submerged inlet during large sideslip maneuver flight. When the sideslip angle is 30°, compared with the conventional submerged inlet configuration, the outlet total pressure recovery coefficient of the distributed submerged inlet configuration is increased by 44.2%, and the total pressure distortion index is reduced by 66.3%.

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Section: Analysis Of Transient Flow Characteristicsmentioning

confidence: 99%

Internal Aerodynamic Performance Enhancement for Aircraft with High Maneuver by Designing a Distributed Submerged Inlet

Zhang

2023

Applied Sciences

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“…For detailed information about this subject and the schematic demonstration of the experimental setup, please refer to Tumse et al [7]. The upper section of the wind tunnel was used to represent the ground.…”

Section: Experimental Setup Of Lift Coefficient Measurementsmentioning

confidence: 99%

“…According to Lee et al [6], lift and drag coefficients, CL and CD, were detected to increase by increasing anhedral as the distance between the ground and trailing edge of the anhedraled reversed delta wing gets smaller. Tumse et al [7] concluded that lift and drag coefficients, CL and CD, get higher with descending from the unbounded flow region under the ground effect at each angle of attack. According to them, the most effective dimensionless ground distance normalized by chord length, h/c is 0.1 in terms of the aerodynamic performance since the highest CL/CD ratio is acquired at h/c=0.1.…”

Section: Introductionmentioning

confidence: 99%

Yer Etkisi Altındaki Delta Kanat Üzerinde Oluşan Taşıma Katsayısının Yapay Sinir Ağı Kullanılarak Tahmin Edilmesi

Tümse¹,

Bilgili²,

Şahi̇n³

2021

Çukurova Üniversitesi Mühendislik Fakültesi Dergisi

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The estimation of the lift coefficient, CL of a non-slender delta wing under the ground effect, is performed by employing an artificial neural network (ANN). The purpose of the study is to estimate the lift coefficient, CL acting on the delta wing for the ground distance h/c=0.4 by utilizing the actual lift coefficient, CL for the ground distances h/c=1, 0.7, 0.55, 0.25 and 0.1. In this ANN model, the angle of attack, α and ground distance, h/c were used as input parameters and lift coefficients, CL as the output parameter. While mean absolute percentage error (MAPE) and root mean squared error (RMSE) were found as 1.60% and 0.0114 in the testing stage, they were calculated as 1.77% and 0.01 in the training stage. Hence, this investigation shows that the lift coefficient, CL of the delta wing in ground effect can be correctly estimated by developing an ANN model.

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“…The propulsion effectiveness of both airfoils diminished as the distance to the ground increased, with the NACA0015 airfoil having a higher efficacy than the Bio airfoil. Tumse et al 30 investigated the aerodynamic efficiency and vortical flow structure of a delta wing during take-off and landing stages. Because of the incomplete development of vortices, the ground reduced the size of the peak values of main and secondary vortices.…”

Section: Introductionmentioning

confidence: 99%

“… 29 NACA0015& Dragonfly Flapping Numerical (FVM) 1100 1.2-4 0.06 Ref. 30 Delta wing Static Experimental 0.1-0.7 – …”

Section: Introductionmentioning

confidence: 99%

Numerical investigation on the aerodynamic efficiency of bio-inspired corrugated and cambered airfoils in ground effect

Abdizadeh

Farokhinejad

Ghasemloo

2022

Sci Rep

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This research numerically investigates the flapping motion effect on the flow around two subsonic airfoils near a ground wall. Thus far, the aerodynamic efficiency of the dragonfly-inspired flapping airfoil has not been challenged by an asymmetric cambered airfoil considering the ground effect phenomenon, especially in the MAV flight range. The analysis is carried out on the basis of an unsteady Reynolds-averaged Navier-stokes (URANS) simulation, whereby the Transition SST turbulence model simulates the flow characteristics. Dragonfly-inspired and NACA4412 airfoils are selected in this research to assess the geometry effect on aerodynamic efficiency. Moreover, the impacts of Reynolds number (Re), Strouhal number (St), and average ground clearance of the flapping airfoil are investigated. The results indicate a direct relationship between the airfoil’s aerodynamic performance ($$C_l$$ C l /$$C_d$$ C d ) and the ground effect. The $$C_l$$ C l /$$C_d$$ C d increases by reducing the airfoil and ground distance, especially at $$h_{0}=c$$ h 0 = c . At $$Re=5\times 10^4$$ R e = 5 × 10 4 , by increasing the St from 0.2 to 0.6, the values of $$C_l$$ C l /$$C_d$$ C d decrease from 10.34 to 2.1 and 3.22 to 1.8 for NACA4412 and dragonfly airfoils, respectively. As a result, the $$C_l$$ C l /$$C_d$$ C d of the NACA4412 airfoil is better than that of the dragonfly airfoil, especially at low oscillation frequency. The efficiency difference between the two airfoils at St=0.6 is approximately 14%, indicating that the $$C_l$$ C l /$$C_d$$ C d difference decreases substantially with increasing frequency. For $$Re=5\times 10^3$$ R e = 5 × 10 3 , the results show the dragonfly airfoil to have better $$C_l$$ C l /$$C_d$$ C d in all frequencies than the NACA4412 airfoil.

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Effect of ground on flow characteristics and aerodynamic performance of a non-slender delta wing

Cited by 24 publications

References 32 publications

Internal Aerodynamic Performance Enhancement for Aircraft with High Maneuver by Designing a Distributed Submerged Inlet

Internal Aerodynamic Performance Enhancement for Aircraft with High Maneuver by Designing a Distributed Submerged Inlet

Yer Etkisi Altındaki Delta Kanat Üzerinde Oluşan Taşıma Katsayısının Yapay Sinir Ağı Kullanılarak Tahmin Edilmesi

Numerical investigation on the aerodynamic efficiency of bio-inspired corrugated and cambered airfoils in ground effect

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