Journal articles: 'High-lift design'

1

Selig, Michael S., and James J. Guglielmo. "High-Lift Low Reynolds Number Airfoil Design." Journal of Aircraft 34, no. 1 (January 1997): 72–79. http://dx.doi.org/10.2514/2.2137.

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van Dam, C. P., S. G. Shaw, J. C. Vander Kam, P. K. C. Rudolph, and D. Kinney. "Aero‐mechanical design of high‐lift systems." Aircraft Engineering and Aerospace Technology 71, no. 5 (October 1999): 436–43. http://dx.doi.org/10.1108/00022669910296873.

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Iannelli, Pierluigi, Frédéric Moens, Mauro Minervino, Rita Ponza, and Ernesto Benini. "Comparison of Optimization Strategies for High-Lift Design." Journal of Aircraft 54, no. 2 (March 2017): 642–58. http://dx.doi.org/10.2514/1.c033648.

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Miller, David S., and Richard M. Wood. "Aerodynamic design considerations for efficient high-lift supersonicwings." Journal of Aircraft 23, no. 10 (October 1986): 783–88. http://dx.doi.org/10.2514/3.45381.

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Eyi, S., K. D. Lee, S. E. Rogers, and D. Kwak. "High-lift design optimization using Navier-Stokes equations." Journal of Aircraft 33, no. 3 (May 1996): 499–504. http://dx.doi.org/10.2514/3.46972.

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6

Cohen, M. J. "Errata: High-Lift Airfoil Design from the Hodograph." Journal of Aircraft 22, no. 5 (May 1985): 447. http://dx.doi.org/10.2514/3.56757.

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Zaccai, David, Francesco Bertels, and Roelof Vos. "Design methodology for trailing-edge high-lift mechanisms." CEAS Aeronautical Journal 7, no. 4 (August 4, 2016): 521–34. http://dx.doi.org/10.1007/s13272-016-0202-7.

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Greenman, Roxana M., and Karlin R. Roth. "High-Lift Optimization Design Using Neural Networks on a Multi-Element Airfoil." Journal of Fluids Engineering 121, no. 2 (June 1, 1999): 434–40. http://dx.doi.org/10.1115/1.2822228.

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The high-lift performance of a multi-element airfoil was optimized by using neural-net predictions that were trained using a computational data set. The numerical data was generated using a two-dimensional, incompressible, Navier-Stokes algorithm with the Spalart-Allmaras turbulence model. Because it is difficult to predict maximum lift for high-lift systems, an empirically-based maximum lift criteria was used in this study to determine both the maximum lift and the angle of attack at which it occurs. Multiple input, single output networks were trained using the NASA Ames variation of the Levenberg-Marquardt algorithm for each of the aerodynamic coefficients (lift, drag, and moment). The artificial neural networks were integrated with a gradient-based optimizer. Using independent numerical simulations and experimental data for this high-lift configuration, it was shown that this design process successfully optimized flap deflection, gap, overlap, and angle of attack to maximize lift. Once the neural networks were trained and integrated with the optimizer, minimal additional computer resources were required to perform optimization runs with different initial conditions and parameters. Applying the neural networks within the high-lift rigging optimization process reduced the amount of computational time and resources by 83% compared with traditional gradient-based optimization procedures for multiple optimization runs.

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Sun, Gang, Kang Le Xu, and Ying Chun Chen. "High-Lift Aerodynamics Design for Large Civil Aircraft in Fudan University." Applied Mechanics and Materials 52-54 (March 2011): 1382–87. http://dx.doi.org/10.4028/www.scientific.net/amm.52-54.1382.

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Part of work on CFD simulations by the high-lift system design team in Fudan university for large civil aircraft is presented. The research on CFD simulation of the high-lift systems and some concepts and experience in three-dimensional geometry modeling are also presented, which are done on the self-developed platform of high-lift device aerodynamic calculation software and programs. For which, the design efficiency is substantially improved.

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DU, YongLiang, and YaKui GAO. "High lift control system design for a transport aircraft." SCIENTIA SINICA Technologica 48, no. 3 (February 9, 2018): 289–98. http://dx.doi.org/10.1360/n092017-00203.

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Yankui, Wang, Yang Shuifeng, Zhang Dongjun, and Deng Xueying. "Design of Waverider Configuration with High Lift-Drag Ratio." Journal of Aircraft 44, no. 1 (January 2007): 144–48. http://dx.doi.org/10.2514/1.22669.

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Wang, Xinyu, Shuyue Wang, Jun Tao, Gang Sun, and Jun Mao. "A PCA–ANN-based inverse design model of stall lift robustness for high-lift device." Aerospace Science and Technology 81 (October 2018): 272–83. http://dx.doi.org/10.1016/j.ast.2018.08.019.

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Fuglsang, Peter, Christian Bak, Mac Gaunaa, and Ioannis Antoniou. "Design and Verification of the Risø-B1 Airfoil Family for Wind Turbines." Journal of Solar Energy Engineering 126, no. 4 (November 1, 2004): 1002–10. http://dx.doi.org/10.1115/1.1766024.

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This paper presents the design and experimental verification of the Risø-B1 airfoil family for MW-size wind turbines with variable speed and pitch control. Seven airfoils were designed with thickness-to-chord ratios between 15% and 53% to cover the entire span of a wind turbine blade. The airfoils were designed to have high maximum lift and high design lift to allow a slender flexible blade while maintaining high aerodynamic efficiency. The design was carried out with a Risø in-house multi disciplinary optimization tool. Wind tunnel testing was done for Risø-B1-18 and Risø-B1-24 in the VELUX wind tunnel, Denmark, at a Reynolds number of 1.6×106. For both airfoils the predicted target characteristics were met. Results for Risø-B1-18 showed a maximum lift coefficient of 1.64. A standard case of zigzag tape leading edge roughness caused a drop in maximum lift of only 3.7%. Cases of more severe roughness caused reductions in maximum lift between 12% and 27%. Results for the Risø-B1-24 airfoil showed a maximum lift coefficient of 1.62. The standard case leading edge roughness caused a drop in maximum lift of 7.4%. Vortex generators and Gurney flaps in combination could increase maximum lift up to 2.2 (32%).

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14

Herrmann, U. "EPISTLE: High lift system design for low-noise applied to a supersonic aircraft." Aeronautical Journal 110, no. 1107 (May 2006): 327–31. http://dx.doi.org/10.1017/s0001924000013191.

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Abstract A new approach for low-drag high-lift system design based on the application of viscous flow solvers was developed in the EC research project EPISTLE. Two high-lift systems for a supersonic commercial transport aircraft (SCT) wing were designed, manufactured and wind-tunnel tested. The predicted large drag reductions were fully confirmed by tests at high Reynolds numbers. These drag reductions significantly reduce the low-speed noise of future SCT configurations. This was estimated by preliminary aircraft design tools. Low-speed noise reduction by aerodynamic means is obtained, as effective high-lift systems enable these aircraft to climb faster.

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Huy, Do Quang, Nguyen Viet Bac, Le Dang Thang, Pham Van Hung, and Vu Toan Thang. "Low Cost Design of High Performance Lift Assist Pneumatic Manipulator." International Journal of Emerging Technology and Advanced Engineering 10, no. 8 (August 21, 2020): 1–5. http://dx.doi.org/10.46338/ijetae0820_01.

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Komarov, V. A., E. A. Kishov, and R. V. Charkviani. "Structural design and testing of composite wing high-lift device." Journal of Machinery Manufacture and Reliability 45, no. 5 (July 2016): 476–83. http://dx.doi.org/10.3103/s1052618816050101.

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17

Jirásek, Adam, and Olivier Amoignon. "Design of a High-Lift System with Droop Nose Device." Journal of Aircraft 46, no. 2 (March 2009): 731–35. http://dx.doi.org/10.2514/1.41520.

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18

Mahgoub, Abdelrahman Ibrahim, Hashim El-Zaabalawy, Walid Aboelsoud, and Mohamed Abdelaziz. "Design of High-Lift Airfoil for Formula Student Race Car." SAE International Journal of Commercial Vehicles 12, no. 1 (December 5, 2018): 19–30. http://dx.doi.org/10.4271/02-12-01-0002.

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19

OGAKI, Masanobu, Takeshi WATANABE, and Kanichi AMANO. "High lift device design and low speed wind-tunnel test." Journal of the Japan Society for Aeronautical and Space Sciences 34, no. 394 (1986): 592–99. http://dx.doi.org/10.2322/jjsass1969.34.592.

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20

Howell, R. J., H. P. Hodson, V. Schulte, R. D. Stieger, Heinz-Peter Schiffer, F. Haselbach, and N. W. Harvey. "Boundary Layer Development in the BR710 and BR715 LP Turbines—The Implementation of High-Lift and Ultra-High-Lift Concepts." Journal of Turbomachinery 124, no. 3 (July 1, 2002): 385–92. http://dx.doi.org/10.1115/1.1457455.

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This paper describes a detailed study into the unsteady boundary layer behavior in two high-lift and one ultra-high-lift Rolls-Royce Deutschland LP turbines. The objectives of the paper are to show that high-lift and ultra-high-lift concepts have been successfully incorporated into the design of these new LP turbine profiles. Measurements from surface mounted hot film sensors were made in full size, cold flow test rigs at the altitude test facility at Stuttgart University. The LP turbine blade profiles are thought to be state of the art in terms of their lift and design philosophy. The two high-lift profiles represent slightly different styles of velocity distribution. The first high-lift profile comes from a two-stage LP turbine (the BR710 cold-flow, high-lift demonstrator rig). The second high-lift profile tested is from a three-stage machine (the BR715 LPT rig). The ultra-high-lift profile measurements come from a redesign of the BR715 LP turbine: this is designated the BR715UHL LP turbine. This ultra-high-lift profile represents a 12 percent reduction in blade numbers compared to the original BR715 turbine. The results from NGV2 on all of the turbines show “classical” unsteady boundary layer behavior. The measurements from NGV3 (of both the BR715 and BR715UHL turbines) are more complicated, but can still be broken down into classical regions of wake-induced transition, natural transition and calming. The wakes from both upstream rotors and NGVs interact in a complicated manner, affecting the suction surface boundary layer of NGV3. This has important implications for the prediction of the flows on blade rows in multistage environments.

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Wang, Fang, and Shuang Lin Gao. "Numerical Study on Aerodynamic Design of Hypersonic Vehicle Forebody." Advanced Materials Research 756-759 (September 2013): 4626–29. http://dx.doi.org/10.4028/www.scientific.net/amr.756-759.4626.

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The lift forebody configuration of a small hypersonic vehicle is designed by using the wedge angle method in this paper. The lift forebody created has been optimized by the simplex method with a penalty function. The aerodynamic characteristics of the forebody optimized are investigated by numerical method. The research results show that the wedge angle method is a high efficient way to generate the lift forebody of the hypersonic vehicle; On the design mach number, there is pressure leaking between the upper and lower surface of lift forebody, which leads to lateral flow in the spanwise on the precompression plane, and which create the unhomogeneity of inlet flow field; Adding side skirts on the both sides, which can reduce the lateral flow on the forebody's precompression plane, it can raise the forebody lift.

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22

Themistokleous, Charalampos, Nikolaos-Grigorios Markatos, John Prospathopoulos, Vasilis Riziotis, Giorgos Sieros, and George Papadakis. "A High-Lift Optimization Methodology for the Design of Leading and Trailing Edges on Morphing Wings." Applied Sciences 11, no. 6 (March 22, 2021): 2822. http://dx.doi.org/10.3390/app11062822.

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Morphing offers an attractive alternative compared to conventional hinged, multi-element high lift devices. In the present work, morphed shapes of a NACA 64A010 airfoil are optimized for maximum lift characteristics. Deformed shapes of the leading and trailing edge are represented through Bezier curves derived from locally defined control points. The optimization process employs the fast Foil2w in-house viscous-inviscid interaction solver for the calculation of aerodynamic characteristics. Transitional flow results indicate that combined leading and trailing edge morphing may increase maximum lift in the order of 100%. A 60–80% increase is achieved when morphing is applied to leading edge only—the so-called droop nose—while a 45% increase is obtained with trailing edge morphing. Out of the stochastic optimization algorithms tested, the Genetic Algorithm, the Evolution Strategies, and the Particle Swarm Optimizer, the latter performs best. It produces the designs of maximum lift increase with the lowest computational cost. For the optimum morphed designs, verification simulations using the high fidelity MaPFlow CFD solver ensure that the high lift requirements set by the optimization process are met. Although the deformed droop nose increases drag, the aerodynamic performance is improved ensuring the overall effectiveness of the airfoil design during take-off and landing.

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23

Ge, Chang Jiang, and Mei Chen Ge. "High-Lift Mechanism of a Bionic Slat." Applied Mechanics and Materials 461 (November 2013): 220–29. http://dx.doi.org/10.4028/www.scientific.net/amm.461.220.

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To avoid broadband noise from a slat cove, the deployed slat contour is usually modified by filling cove, but the design is sensitive to aerodynamic performance. In the paper, a bionic slat without a cove is built on the basis of a bionic airfoil (i.e. stowed bionic multi-element airfoil), which is extracted from a long-eared owl wing. The quasi-two-dimensional models with a deployed bionic slat and a stowed bionic slat are manufactured by rapid manufacturing and prototyping system, respectively, and measured in a low-turbulence wind tunnel. The results are used to characterize high-lift effect: the lift coefficients of the model with a stowed slat are larger at less than 4°angle of attack, but the model with a deployed slat has the larger lift coefficients at greater than 4°angle of attack. Furthermore, the deployed bionic slat can increase stall angle and maximum lift coefficient, but also delay the decline of the lift coefficient curve slope meaning that the leading-edge separation is postponed within a certain range of angle of attack. At the same time, the flow field around the models is visualized by smoke wire method. The leading-edge separation of the model with a stowed slat is shown at low Reynolds number and angle of attack. However, the finding does not occur in the flow field of the model with a deployed slat at the same conditions, probably because the gap between the bionic slat and the main wing results in favorable pressure gradient, the deployed bionic slat decreases the peak of adverse pressure gradient by increasing the chord of the bionic multi-element model, and the bionic slat wake excites transition to the boundary layer on upper surface of the main wing. This superiority may be used as reference in the design of the leading-edge slat without a cove.

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Mikhailov, Yu S. "Increase in high-lift devices efficiency of swept wing." Civil Aviation High Technologies 23, no. 6 (December 31, 2020): 101–20. http://dx.doi.org/10.26467/2079-0619-2020-23-6-101-120.

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The use of Fowler flaps and slotted slats in sweptwing aircraft is the standard solution to increase wing lift at take off and landing. In the literature this solution is known as a classical option of high-lift system of commercial subsonic aircraft. The results of numerical and experimental studies of some solutions intended to increase the efficiency of classical high-lift devices are presented. The concept of the trailing-edge devices called "the adaptive flap" is considered as a way to improve flap efficiency. The adaptive concept is characterized by the integration of spoiler downward deflection to the Fowler flap function. Integration of the spoiler with a movable flap provided an increase of lift in the linear region due to flaps deflected to a higher angle. The steeper upwash angle at a leading-edge device may be the reason of an early stall of the main wing. To protect the leading edge a slotted Kruger flap with streamline form has been used. Preliminary design of classical and improved high-lift systems included the determination of aerodynamic shapes and the optimized position for the high-lift devices. Aerodynamic analysis and design were carried out using 2D RANS Navier-Stokes method. A comparison of computed results has shown visible aerodynamic advantages of an improved high-lift system for maximum lift coefficient and refining the behavior of stall characteristics at high angles of attack. The results of wind tunnel tests of aircraft model with adaptive flap showed its effectiveness.

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Chabphet, Santichatsak, Thalang, Sleesongsom, and Bureerat. "High-Lift Mechanism Motion Generation Synthesis Using a Metaheuristic." Proceedings 39, no. 1 (December 30, 2019): 5. http://dx.doi.org/10.3390/proceedings2019039005.

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This paper proposes an approach to synthesize a high-lift mechanism (HLM) of a transportation aircraft. Such a mechanism is very important for generation of additional lift to an aircraft wing during take-off and landing. The design problem is minimization of error between the motions of a four-bar mechanism for controlling a flap to the target points. The optimum target points are positions and angles of flap at the take-off and landing conditions, which are designed based on maximizing the lift to drag ratio. Design constraints include the conditions of four-bar mechanism to work properly, limiting positions and workplace of the mechanism. A optimizer used in this study, is in a group of metaheuristics (MHs). The results show the optimum mechanism can generate flap motion fulfilling the design targets, thus, the proposed technique can be used to increase the performance of HLM.

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Wu, Peng, Xue Ying Deng, and Yan Kui Wang. "Application of Pulsed Blowing Technique in High-Lift Control Surface Design." Advanced Materials Research 482-484 (February 2012): 121–25. http://dx.doi.org/10.4028/www.scientific.net/amr.482-484.121.

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Because the flight performance of aircraft is so dependent on aerodynamic efficiency of control surfaces, it is very important to eliminate the flow separation over the control surfaces at high deflection angle in order to keep the aircraft having good flight capability, especially for the modern aircraft with tailless aerodynamic configuration. A novel flow control technique to eliminate flow separation of control surface at high deflection angle and creat high lift increment by pulsed blowing at leading edge of control surface is discussed in this paper. The performance of lift enhancment of control surface which used this technique is investigated, and based on the zonal analysis of pulsed frequency, the control characteristic of this technique is also discussed.

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Reckzeh, Daniel. "Aerodynamic design of the high-lift-wing for a Megaliner aircraft." Aerospace Science and Technology 7, no. 2 (March 2003): 107–19. http://dx.doi.org/10.1016/s1270-9638(02)00002-0.

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Wild, Jochen. "Multi-objective constrained optimisation in aerodynamic design of high-lift systems." International Journal of Computational Fluid Dynamics 22, no. 3 (March 2008): 153–68. http://dx.doi.org/10.1080/10618560701868420.

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29

Werner-Spatz, Christian, Wolfgang Heinze, Peter Horst, and Rolf Radespiel. "Multidisciplinary conceptual design for aircraft with circulation control high-lift systems." CEAS Aeronautical Journal 3, no. 2-4 (November 11, 2012): 145–64. http://dx.doi.org/10.1007/s13272-012-0049-5.

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Keller, D. "High-lift design for a forward swept natural laminar flow wing." CEAS Aeronautical Journal 11, no. 1 (May 11, 2019): 81–92. http://dx.doi.org/10.1007/s13272-019-00396-z.

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31

Zhao, Yan, Xiao Meng Liu, and Wen Jie Li. "Mathematical Model Design on Online Virtual Processing Platform of Machinery Manufacturing." Applied Mechanics and Materials 539 (July 2014): 25–28. http://dx.doi.org/10.4028/www.scientific.net/amm.539.25.

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This paper designs the virtual online platform of high precision machinery processing. And we use it to forecast the safety coefficient k and lift coefficient of auto machining process, and based on the safety coefficient and the lift coefficient we improve the automobile working procedure real-time, and obtain a reasonable body safety structure and external driving performance of the structure, which achieves good comprehensive design effect. At the end of this paper, we apply the system in the online virtual platform of computer higher occupation education. According to the cycle mechanism of the lift coefficient, we design the teaching task of cultivating innovative talents, and arrange the teaching tasks of applied science. It provides the theory reference for research on the higher occupation school personnel training.

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32

Liu, Pei Qing, Shuo Yang, and Yun Tian. "An Investigation of Drag Reduction on Gurney Flaps by an Three-Element Airfoil." Applied Mechanics and Materials 138-139 (November 2011): 229–33. http://dx.doi.org/10.4028/www.scientific.net/amm.138-139.229.

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During airplane’s take-off, higher lift force should be provided by wing used high lift devices, and the drag should be lower. The design basis of high lift devices with good aerodynamic characteristic is the design of the multi-element airfoil. When a multi-element airfoil is used Gurney flap, lift coefficient can be improved while drag coefficient is also increased, but the lift-to-drag ratio is reduced. In this paper, the numerical simulation method is used to study the aerodynamic characteristic of the multi-element airfoil used Gurney flap with slat in the configuration of take-off. Lift coefficient and drag coefficient of the multi-element airfoil with Gurney flap can be reduced by slat while lift-to-drag ratio of airfoil is increased. Through the comparisons of the multi-element airfoils with Gurney flap with different types of slats, the optimized multi-element airfoil with higher lift coefficient and lower drag coefficient is obtained ultimately.

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Varaprasad, Veenam. "Design and Analysis of Foreward Step Automotive." International Journal for Research in Applied Science and Engineering Technology 9, no. VII (July 25, 2021): 2357–63. http://dx.doi.org/10.22214/ijraset.2021.36879.

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Nowadays with increase in competition in automobile sector, vehicle aerodynamics plays an important role. Aerodynamics affect the performance of vehicle due to change in parameters such as lift and drag force which plays a significant role at high speeds. With improvement in computer technology, manufacturers are looking toward computational fluid dynamics instead of wind tunnel testing to reduce the testing time and keeps the cost of R&D low. In this paper, lift and drag of production vehicle are determined by the analysis of flow of air around it using Ansys 18.0. After that, analysis was done on the car with different engine hood angles. Based on Cl and Cd values, optimal model was selected. To validate steady state results, transient state analysis was done on this optimal model. By introducing this considerably reduce the drag and increase lift hence improves the performance of vehicle.

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Liu, Xiao Bo, Xiao Feng Wei, Xiao Dong Yuan, and Wei Ni. "A Novel Vertical Lift Machine and its Precise Pose Control." Advanced Materials Research 989-994 (July 2014): 3105–9. http://dx.doi.org/10.4028/www.scientific.net/amr.989-994.3105.

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This paper deals with the design and theoretical analysis on a novel vertical lift machine which can vertically lift above 700 kg load up to 3.2 meters above the floor and located the load with high accuracy of position and orientation. Firstly the design model based on the installment demands of line-replaceable units (LRUs) is constructed. Then theoretical analysis including the number of degree of freedom of the lift machine, the inverse kinematic, the control principle, the lift platform pose error and the precise pose control method are conducted in the article. The validity of the design model and the effectiveness of the precise pose control system are confirmed by experiments using a prototype lift machine.

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Haselbach, Frank, Heinz-Peter Schiffer, Manfred Horsman, Stefan Dressen, Neil Harvey, and Simon Read. "The Application of Ultra High Lift Blading in the BR715 LP Turbine." Journal of Turbomachinery 124, no. 1 (February 1, 2001): 45–51. http://dx.doi.org/10.1115/1.1415737.

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The original LP turbine of the BR715 engine featured “High Lift” blading, which achieved a 20-percent reduction in aerofoil numbers compared to blading with conventional levels of lift, reported in Cobley et al. (1997). This paper describes the design and test of a re-bladed LP turbine with new “Ultra High Lift” aerofoils, achieving a further reduction of approximately 11 percent in aerofoil count and significant reductions in turbine weight. The design is based on the successful cascade experiments of Howell et al. (2000) and Brunner et al. (2000). Unsteady wake-boundary layer interaction on these low-Reynolds-number aerofoils is of particular importance in their successful application. Test results show the LP turbine performance to be in line with expectation. Measured aerofoil pressure distributions are presented and compared with the design intent. Changes in the turbine characteristics relative to the original design are interpreted by making reference to the detailed differences in the two aerofoil design styles.

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Faisal Abdul Hamid, Mohd, Azmin Shakrine Mohd Rafie, Ezanee Gires, and Abd Rahim Abu Talib. "Lift force for cylindrical and elliptical Coandă aircraft design." International Journal of Engineering & Technology 7, no. 4.13 (October 9, 2018): 137. http://dx.doi.org/10.14419/ijet.v7i4.13.21345.

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Small aerial vehicles possess advantages in terms of size and accessibility in performing a variety of tasks. Presently, their design and performance is dependent on variations of conventional aerodynamic configurations (fixed- and rotary-wing). A disadvantage for these configurations is the aerodynamic potential between the mainstream airflow and the body surfaces are not fully utilized. To solve this issue, the Coandă effect is proposed whereby a high-velocity jet is blown tangentially over a curved surface to increase circulation and lift. Prior to the costly approach (experimental and numerical), an analytical formulation (via control volume analysis) to predict the aerodynamic Coandă lift force of the design concept is developed. This is an extended version of the existing mathematical formulations, capturing viscous flow effects. It is also pertinent for circular and elliptical-shaped designs. The results obtained show that the total lift force is dependent on the jet velocity, outflow angle, dimensions of the jet slot, the projected surface area, and the viscous effect. The approach has demonstrated how this modelling technique is effective in calculating the lift force for cylindrical and elliptical Coandă aircraft design.

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Jiang, Zhengrong, and Weijun Gao. "Impact of Enclosure Boundary Patterns and Lift-Up Design on Optimization of Summer Pedestrian Wind Environment in High-Density Residential Districts." Energies 14, no. 11 (May 30, 2021): 3199. http://dx.doi.org/10.3390/en14113199.

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A comfortable wind environment favors the sustainable development of urban residential districts and public health. However, the rapid growth of high-rise urban residential districts leads to low wind velocity environments in summer. This study examines the influence of enclosure boundary patterns and lift-up design on the wind environment and proposes an optimization strategy to improve the low wind velocity environment in residential districts in summer. A typical residential district in Hangzhou was selected; the average wind velocity, calm wind zone ratio and comfortable wind zone ratio were selected as the evaluation indexes. The wind environment for different enclosure boundary patterns and lift-up designs were obtained via computational fluid dynamics (CFD) simulations. The results indicate that the pedestrian wind environment is greatly improved in residential districts by reducing the height/width of the enclosure boundary, increasing the permeability rate and adopting a lift-up design in all buildings within residential districts. A combination of permeable railings and lift-up design is recommended; this can increase the average wind velocity and the ratio of comfortable wind zones by 70% and 200%, respectively. This study provides practical guidelines for the optimization of a low wind velocity environment in Chinese high-density residential districts in summer.

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van Dam, C. P., J. C. Vander Kam, and J. K. Paris. "Design-Oriented High-Lift Methodology for General Aviation and Civil Transport Aircraft." Journal of Aircraft 38, no. 6 (November 2001): 1076–84. http://dx.doi.org/10.2514/2.2875.

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39

Cerra, David F., and Joseph Katz. "Design of a High-Lift, Thick Airfoil for Unmanned Aerial Vehicle Applications." Journal of Aircraft 45, no. 5 (September 2008): 1789–93. http://dx.doi.org/10.2514/1.36924.

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van Dam, C. P. "The aerodynamic design of multi-element high-lift systems for transport airplanes." Progress in Aerospace Sciences 38, no. 2 (February 2002): 101–44. http://dx.doi.org/10.1016/s0376-0421(02)00002-7.

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41

Beutel, T., S. Sattler, Y. El Sayed, M. Schwerter, M. Zander, S. Büttgenbach, M. Leester-Schädel, R. Radespiel, M. Sinapius, and P. Wierach. "Design of a high-lift experiment in water including active flow control." Smart Materials and Structures 23, no. 7 (May 21, 2014): 077004. http://dx.doi.org/10.1088/0964-1726/23/7/077004.

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Mahmood, S., P. Scholz, and R. Radespiel. "Numerical Design of Leading Edge Flow Control over Swept High-Lift Airfoil." Aerotecnica Missili & Spazio 92, no. 1-2 (January 2013): 3–16. http://dx.doi.org/10.1007/bf03404659.

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Zhao, Huan, Zhenghong Gao, Yuan Gao, and Chao Wang. "Effective robust design of high lift NLF airfoil under multi-parameter uncertainty." Aerospace Science and Technology 68 (September 2017): 530–42. http://dx.doi.org/10.1016/j.ast.2017.06.009.

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Kim, Sangho, Juan J. Alonso, and Antony Jameson. "Multi-Element High-Lift Configuration Design Optimization Using Viscous Continuous Adjoint Method." Journal of Aircraft 41, no. 5 (September 2004): 1082–97. http://dx.doi.org/10.2514/1.17.

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Hua, Xin, Wei Shao, Chun Hua Zhang, and Zhi Qiang Zhang. "Based on Imitation Seagull Airfoil UVA Wing Numerical Simulation." Applied Mechanics and Materials 271-272 (December 2012): 791–96. http://dx.doi.org/10.4028/www.scientific.net/amm.271-272.791.

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Wing aircraft is one of the major components to generate lift, in today's energy shortage, design the high lift-to-drag ratio wing is the goal pursued by, The author in the exploration of bionic airfoil aerodynamic characteristics on the basis of, which will be applied to straight wing design so as to improve the aerodynamic performance of aircraft.Our research mainly includes two aspects: first, the use of imitation seagull airfoil and NACA4412 airfoil are designed into the straight wing. The use of FLUENT software in Re=300000condition carries on the numerical simulation results show that the ratio of gull wing airfoil than NACA4412 lift coefficient increased by 13%, while the lift to drag ratio,is improved by 46.83%. Then, using the similarity principle, the wing scale, was tested in a wind tunnel test, the results obtained with the simulation are consistent. Airfoil design for the design of high performance wing opened a new way.

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Steiner, Julia, Axelle Viré, Francesco Benetti, Nando Timmer, and Richard Dwight. "Parametric slat design study for thick-base airfoils at high Reynolds numbers." Wind Energy Science 5, no. 3 (August 24, 2020): 1075–95. http://dx.doi.org/10.5194/wes-5-1075-2020.

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Abstract. Standard passive aerodynamic flow control devices such as vortex generators and gurney flaps have a working principle that is well understood. They increase the stall angle and the lift below stall and are mainly applied at the inboard part of wind turbine blades. However, the potential of applying a rigidly fixed leading-edge slat element at inboard blade stations is less well understood but has received some attention in the past decade. This solution may offer advantages not only under steady conditions but also under unsteady inflow conditions such as yaw. This article aims at further clarifying what an optimal two-element configuration with a thick main element would look like and what kind of performance characteristics can be expected from a purely aerodynamic point of view. To accomplish this an aerodynamic shape optimization procedure is used to derive optimal profile designs for different optimization boundary conditions including the optimization of both the slat and the main element. The performance of the optimized designs shows several positive characteristics compared to single-element airfoils, such as a high stall angle, high lift below stall, low roughness sensitivity, and higher aerodynamic efficiency. Furthermore, the results highlight the benefits of an integral design procedure, where both slat and main element are optimized, over an auxiliary one. Nevertheless, the designs also have two caveats, namely a steep drop in lift post-stall and high positive pitching moments.

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Shen, Xiao Song, Jie Zhang, and You Wei Zeng. "Design of Decanter System Floating Tank Lifting Type." Advanced Materials Research 805-806 (September 2013): 1775–79. http://dx.doi.org/10.4028/www.scientific.net/amr.805-806.1775.

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A new unpowered decanter system was designed to lift the decanting sink only by the dynamic provided by liquid level difference. The system arranged the float tank pools symmetrically in both ends of the decanting sink. The system was run by the difference of liquid level between float tank pool and reaction pool. When the level difference got small, the float tank would rise and hence lift up the decanting sink in the reaction pool to up above the liquid level; when the level difference got large, the float tank no longer received the buoyance so the decanting sink would float in the reaction pool and decant. The testing results of the experiment device showed that by means of difference of liquid level to lift the decanting sink was feasible. The new system is simple in structure, so that the construction and maintenance cost is not high. It also does not consume electricity. It provides a new decanter model.

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Tao, Jun, Xinyu Wang, and Gang Sun. "Stall characteristics analyses and stall lift robustness inverse design for high-lift devices of a wide-body commercial aircraft." Aerospace Science and Technology 111 (April 2021): 106570. http://dx.doi.org/10.1016/j.ast.2021.106570.

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Gonza´lez, P., I. Ulizar, R. Va´zquez, and H. P. Hodson. "Pressure and Suction Surfaces Redesign for High-Lift Low-Pressure Turbines." Journal of Turbomachinery 124, no. 2 (April 1, 2002): 161–66. http://dx.doi.org/10.1115/1.1452747.

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Nowadays there is a big effort toward improving the low-pressure turbine efficiency even to the extent of penalizing other relevant design parameters. LP turbine efficiency influences SFC more than other modules in the engine. Most of the research has been oriented to reduce profile losses, modifying the suction surface, the pressure surface, or the three-dimensional regions of the flow. To date, the pressure surface has received very little attention. The dependence of the profile losses on the behavior of both pressure and suction surfaces has been investigated for the case of a high-lift design that is representative of a modern civil engine LP turbine. The experimental work described in this paper consists of two different sets of experiments: the first one concluded an improved pressure surface definition, and the second set was oriented to achieve further improvement in losses modifying the profile suction surface. Three profiles were designed and tested over a range of conditions. The first profile is a thin-solid design. This profile has a large pressure side separation bubble extending from near the leading edge to midchord. The second profile is a hollow design with the same suction surface as the first one, but avoiding pressure surface separation. The third one is also a hollow design with the same pressure surface as the second profile, but more aft loaded suction surface. The study is part of a wider ongoing research program covering the effects of the different design parameters on losses. The paper describes the experiments conducted in a low-speed linear cascade facility. It gathers together steady and unsteady loss measurements by wake traverse and surface pressure distributions for all the profiles. It is shown that thick profiles generate only around 90 percent of the losses of a thin-solid profile with the same suction surface. The results support the idea of an optimum axial position for the peak Mach number. Caution is recommended, as profile aft loading would not be a completely secure method for reducing losses.

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Somers, D. M., and J. L. Tangler. "Wind Tunnel Test of the S814 Thick Root Airfoil." Journal of Solar Energy Engineering 118, no. 4 (November 1, 1996): 217–21. http://dx.doi.org/10.1115/1.2871781.

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The objective of this wind-tunnel test was to verify the predictions of the Eppler Airfoil Design and Analysis Code for a very thick airfoil having a high maximum lift coefficient designed to be largely insensitive to leading-edge roughness effects. The 24 percent thick S814 airfoil was designed with these characteristics to accommodate aerodynamic and structural considerations for the root region of a wind-turbine blade. In addition, the airfoil’s maximum lift-to-drag ratio was designed to occur at a high lift coefficient. To accomplish the objective, a two-dimensional wind tunnel test of the S814 thick root airfoil was conducted in January 1994 in the low-turbulence wind tunnel of the Delft University of Technology Low Speed Laboratory, The Netherlands. Data were obtained with transition free and transition fixed for Reynolds numbers of 0.7, 1.0, 1.5, 2.0, and 3.0 × 106. For the design Reynolds number of 1.5 × 106, the maximum lift coefficient with transition free is 1.32, which satisfies the design specification. However, this value is significantly lower than the predicted maximum lift coefficient of almost 1.6. With transition fixed at the leading edge, the maximum lift coefficient is 1.22. The small difference in maximum lift coefficient between the transition-free and transition-fixed conditions demonstrates the airfoil’s minimal sensitivity to roughness effects. The S814 root airfoil was designed to complement existing NREL low maximum-lift-coefficient tip-region airfoils for rotor blades 10 to 15 meters in length.

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Journal articles on the topic 'High-lift design'

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