Tailoring Wing Structures for Reduced Drag Penalty in Off-Design Flight Conditions

Papila, Melih; Haftka, Raphael T.; Mason, William H.; Alves, Rafael

doi:10.2514/6.2004-4637

Cited by 3 publications

(3 citation statements)

References 7 publications

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“…The development and use of automated wing design in a multidisciplinary environment were discussed by Neill et al [14], who implemented a directional algorithm using sensitivity analysis and constraint approximations. Papila et al [46] performed an optimization by investigating the induced drag penalty associated with flight under lower lift coefficient conditions. Their wing structural model consisted of a main box section and 15 equally spaced ribs.…”

Section: Discussionmentioning

confidence: 99%

Wind Tunnel Experiments on an Aircraft Model Fabricated Using a 3D Printing Technique

Szwedziak

Bąbel²,

Winiarski³

et al. 2022

JMMP

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Experimental tests regarding the M-346 aircraft model made via 3D printing were carried out in order to obtain numerical data and characteristics in the form of graphs of basic aerodynamic forces and coefficients. The tests were carried out for the left side of the airframe model in a clean configuration, without additional suspension equipment; the flight control surfaces and the aerodynamic brake were in neutral positions. Based on the scan of the base model in 1:48 scale using a Nikon Model Maker MMDx laser scanning head, followed by the generation and optimization of some of the airframe elements in SolidWorks software, a test model ready for printing was prepared. Using the MakerBot Print program, the printing parameters were set, and the process itself was completed using a MakerBot Replicator Z18 3D printer. The next step was manual treatment in order to remove the material excess from the melted thermoplastic material, join the elements and appropriately polish the surface of the tested model in order to obtain the desired quality. The test was carried out using a Gunt HM 170 wind tunnel for fixed airflow velocities at variable angles of attack. On this basis, the numerical values of lift force, Pz, and drag force, Px, were obtained; then, the lift force indices, Cz, and drag force indices, Cx, were computed for the steady states, which were for angle α from −12 to 16°. The use of 3D printing contributed to the generation of geometry, which, for research purposes, was scaled down in order to fully use the available measurement space of the wind tunnel. The final stage of the work was to compare the obtained curves of particular characteristics with the literature data.

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Section: Discussionmentioning

confidence: 99%

Wind Tunnel Experiments on an Aircraft Model Fabricated Using a 3D Printing Technique

Szwedziak

Bąbel²,

Winiarski³

et al. 2022

JMMP

View full text Add to dashboard Cite

show abstract

“…The development and use of the Automated Structural Optimization System (ASTROS) with wing structural design in multidisciplinary environment were discussed by Neill et al [8], who implemented the feasible directions algorithm with sensitivity analysis and constraint approximations. Papila et al [9] considered different optimization strategies by investigating the induced drag penalty associated with flight conditions having lower lift coefficient than the one associated with the design flight conditions. Their wing structural model consisted of main box section and fifteen equally spaced ribs.…”

Section: /16mentioning

confidence: 99%

Aerodynamic/Structural Optimization of a Training Aircraft Wing

Maalawi

Negm

Sheikh³

2009

International Conference on Aerospace Sciences and Aviation Tec

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This paper presents a coupled aerodynamic/structural optimization model for a light training, low subsonic aircraft wing. Four optimization strategies have been developed and tested. The first was based on minimization of the total weight of the main wing structure subject to strength, stiffness and aeroelastic constraints. The second strategy considered maximization of the critical flight speed at which divergence occurs, while the third one focused on minimization of the wing drag/lift ratio as a measure of improving aerodynamic efficiency without violating structural weight requirements. The last strategy was based on minimization of the power consumption, which has worked very well and shown balanced improvements in both the aerodynamic and structural efficiencies of the wing under the imposed design constraints. The aerodynamic variables are chosen to be the wing aspect and chord taper ratios, while the structural variables encompassed spar locations, spar flange cross-sectional areas, shear webs and covering skin thicknesses of the main wing box section. The optimization problem has been formulated as a nonlinear mathematical programming problem solved by invoking the MATLab optimization Toolbox routines, which implements the method of feasible directions. Structural, aerodynamic and aeroelastic analyses assumed slender one-dimensional configuration. It makes use of the quasi-steady strip theory in evaluating aerodynamic loads and the classical engineering theories of bending and torsion in calculating stresses and deformations. Results have shown that the approach implemented in this study can be efficient in producing improved designs in a reasonable computer time. The proposed model has succeeded in arriving at the optimum solutions showing significant improvements in the needed design goals as compared with a baseline wing design.

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“…However, the shape of the lift distribution for a twisted wing changes with lift coefficient [8][9][10], and induced drag can increase significantly at off-design lift coefficients [11]. Although it is generally desirable to achieve minimum induced drag at or near a representative cruise lift coefficient, the structural limits of the wing must be designed to a high lift coefficient corresponding to a maneuver or gust load.…”

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confidence: 99%

Lift Distributions for Minimum Induced Drag with Generalized Bending Moment Constraints

Pate

German

2013

Journal of Aircraft

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The previous works of Prandtl, Jones, and Klein and Viswanathan addressed the problem of determining the lift distribution that minimizes induced drag for a given lift and specified bending moment. In these formulations, bending moment is considered to be a surrogate for wing weight. These classical methods require the bending constraints to be imposed at the same lift coefficient at which drag is minimized. In practice, however, it is commonly desired to minimize drag at a representative cruise lift coefficient while imposing the bending constraints at a limiting structural load condition, such as a maneuver lift coefficient. This paper presents an approach to extend the classical methods by allowing the bending constraints to be imposed at different lift coefficients than that at which induced drag is minimized. An example for a wing planform similar to that of a Boeing 737 shows that the penalty for optimizing induced drag at the maneuver lift coefficient as implied in the classical methods results in between a 1-10% increase in drag at cruise compared to the results from this new approach. It is expected that the new approach will enable the classical methods to be extended to practical applications in multidisciplinary wing design.

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Tailoring Wing Structures for Reduced Drag Penalty in Off-Design Flight Conditions

Cited by 3 publications

References 7 publications

Wind Tunnel Experiments on an Aircraft Model Fabricated Using a 3D Printing Technique

Wind Tunnel Experiments on an Aircraft Model Fabricated Using a 3D Printing Technique

Aerodynamic/Structural Optimization of a Training Aircraft Wing

Lift Distributions for Minimum Induced Drag with Generalized Bending Moment Constraints

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