Aerodynamic Performances of Battle-Damaged and Repaired Wings of an Aircraft Model

Djellal, S.; Ouibrahim, A.

doi:10.2514/1.36460

Cited by 11 publications

(6 citation statements)

References 14 publications

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“…The most common type of damage used in simulations is the circular hole [6]. The study of other shapes reported by Mani and Render [5] has not shown noticeable differences.…”

Section: Damage Modellingmentioning

confidence: 95%

“…The first study by Irwin at Loughborough University was extensively reported [2,3] and by many other authors; Render et al Djellal and Ouibrahim [6]. Recently Saaedi et al in this field.…”

Section: Introductionmentioning

confidence: 94%

“…In order to validate the numerical results, obtained values have been compared with those of experimental investigations led by the previous authors [2,5,6,8].…”

Section: Introductionmentioning

confidence: 99%

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Numerical study of battle damaged two-dimensional wings

Djellal¹,

Azzam²,

Djellab³

et al. 2012

Advances in Fluid Mechanics IX

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The flow around a NACA 64 1 -412 airfoil with circle damage is numerically investigated using the Ansys Fluent package. Several diameter values are considered for the damage which is located at either quarter or mid chord. The numerical domain is covered with a multiblock structured hexagonal grid consisting of 344,680 cells in the undamaged case and 351,540 cells in the damaged case. Inside the damage hole, a structured tetragonal mesh is used. Turbulence effects are taken into account via the k- model. The results show that the presence of the damage hole decreases the lift coefficient and increases the drag coefficient, resulting in a loss of airfoil performance (fineness decrease). The numerical simulations show that the flow through the damage corresponds either to a weak or a strong jet. In the first case an attached wake forms giving the smallest change in the force coefficients whereas the second case shows a separated wake with a reverse flow giving the highest force coefficient change. The present paper also compares the structure of the damage through flow with previously published experimental results. Finally, the numerical solution is qualitatively and quantitatively validated using available experimental results.

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“…The most common type of damage used in simulations is the circular hole [6]. The study of other shapes reported by Mani and Render [5] has not shown noticeable differences.…”

Section: Damage Modellingmentioning

confidence: 95%

“…The first study by Irwin at Loughborough University was extensively reported [2,3] and by many other authors; Render et al Djellal and Ouibrahim [6]. Recently Saaedi et al in this field.…”

Section: Introductionmentioning

confidence: 94%

See 1 more Smart Citation

Numerical study of battle damaged two-dimensional wings

Djellal¹,

Azzam²,

Djellab³

et al. 2012

Advances in Fluid Mechanics IX

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show abstract

“…A summary of this can be found in Irwin and Render (3) , while a full description can be found in Irwin (2) . As well as Irwin’s work, investigations have been carried out into the effects of damage holes with different shapes (Mani and Render) (4) , damage from live fire (Robinson and Leishman) (5) and three-dimensional tests using wings of finite span (Samaad-Suhaeb) (6) and (Djellal) (7) . The technique developed by Irwin is now the most commonly used method to test battle damage.…”

Section: Introductionmentioning

confidence: 99%

Investigation of the flowfield induced by simulated battle damage

et al. 2017

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Particle Image Velocimetry (PIV) has been used to study the complex flowfield created by simulated battle damage to a two-dimensional wing. Computational Fluid Dynamics (CFD) predictions have also been used for validation of internal cavity flow. Two damage cases were selected for the study; both cases were simulated using a single hole with diameters equal to 20% and 40% of the chord, located at the wing half-chord. Wind-tunnel tests were conducted at a Reynolds number of 500,000 over a range of incidences from 0 to 10° with two-component PIV measurements made on three chordwise and three spanwise planes. The PIV data were analysed and compared to CFD data of the same damage cases. The PIV data have shown lower velocity ratios and lower vorticity in the jet compared to past Jet in Cross-Flow experiments and CFD was used to describe the flow features inside the cavity of the wing. It was seen that the wing cavity has large effects on the external flow features, particularly for the 20% damage case. Finally, the flow field data have been related to force balance data. At higher incidence angles, the larger force coefficient increments in both lift and drag can be attributed to the larger wakes and higher jet strengths.

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“…Asymmetric aerodynamic characteristics were the first to be of concern, and wing bending and impact damage were studied by the use of wind tunnel experiments (Render et al 2007;Djellal and Ouibrahim 2008;Render et al 2009). The dynamic problems were also the focus of the study.…”

Section: Introductionmentioning

confidence: 99%

The Control of Asymmetric Rolling Missiles Based on Improved Trajectory Linearization Control Method

Sun¹,

Yu²,

Zhang³

2016

J.Aerosp. Technol. Manag.

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According to motion characteristic of an asymmetric rolling missile with damage fin, a three-channel controlled model is established. The controller which is used to realize non-linear tracking and decoupling control of the roll and angle motion is introduced based on an improved trajector y linearization control method. The improved method is composed of the classic trajectory linearization control method and a compensation control law. The classic trajectory linearization control method is implemented in the time-scale separation principle. The Lipschitz non-linear state observer systematically obtained by solving the linear matrix inequality approach is provided to estimate state variables and unknown parameters, and then the compensation control law utilizing the estimated unknown parameters improves the TLC method. Simulation experiments show that the adaptive decoupling control ensure tracking performance, and the robustness and accuracy of missile attitude control are ensured under the condition of the system parameters uncertainty, random observation noise and external disturbance caused by damage fin.

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Aerodynamic Performances of Battle-Damaged and Repaired Wings of an Aircraft Model

Cited by 11 publications

References 14 publications

Numerical study of battle damaged two-dimensional wings

Numerical study of battle damaged two-dimensional wings

Investigation of the flowfield induced by simulated battle damage

The Control of Asymmetric Rolling Missiles Based on Improved Trajectory Linearization Control Method

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