Relevant bibliographies by topics / High-lift design

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'High-lift design'

Author: Grafiati
Published: 4 June 2021
Last updated: 5 February 2022

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Journal articles on the topic "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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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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Dissertations / Theses on the topic "High-lift design"

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Trapani, Giuseppe. "The design of high lift aircraft configurations through multi-objective optimisation." Thesis, Cranfield University, 2014. http://dspace.lib.cranfield.ac.uk/handle/1826/8831.

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An approach is proposed in this work to support the preliminary design of High-Lift aircraft configurations through the use of Multi-Objective optimisation tech¬niques. For this purpose a framework is developed which collates a Free-Form De¬formation parametrisation technique, a number of Computational Fluid Dynamics suites of different fidelity levels, a rapid aero-structure coupling procedure and two multi-objective optimisation techniques, namely Multi-Objective Tabu Search and Non-dominated Sorting Genetic Algorithm-II. The proposed optimisation framework is used for the execution of several design studies. Firstly, the deployment settings and elements' shape of the 2D multi-element GARTEUR A310 test case are optimised for take-off conditions. Consider¬able performance improvements are achieved using both the optimisation algorithms, though the sensitivity of the optimum designs to changes in operating conditions is highlighted. Therefore, a new optimisation set-up is proposed which successfully identifies operational robust designs. Secondly, the framework is extended to the optimisation of 3D geometries, using a Quasi-three-dimensional approach for the evaluation of the aerodynamic performance. The application to the deployment settings optimisation of the (DLF F11) KH3Y configuration illustrates that the method can be applied to more complicated real-world design cases. In particular, the deployment settings of slat and flaps (inboard and outboard segments) are suc¬cessfully optimised for landing conditions. Finally, a rapid aero-structure coupling procedure is implemented, in order to perform static aero-elastic analysis within the optimisation process. The KH3Y optimisation study is repeated including, this time, the effects of structural deformations. Different optima deployment settings are identified compared to the rigid case, illustrating that, despite being of reduced magnitude, wing deformations influence the optimum high-lift system settings. Furthermore, an industrial development and application of multi-objective opti-misation techniques is also presented. In the proposed approach, a reduced order model based on Proper Orthogonal Decomposition methods is used in an offline-online optimisation strategy. The results of the optimisation process for the RAE2822 single-element aerofoil and for the GARTEUR A310 multi-element aerofoil illustrate the potential of the method, as well as its limitations. The technical analysis is com-pleted with a description of the Agile project management approach used to run the project. Finally, future work directions have been identified and recommended.
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McQuilling, Mark W. "DESIGN AND VALIDATION OF A HIGH-LIFT LOW-PRESSURE TURBINE BLADE." Wright State University / OhioLINK, 2007. http://rave.ohiolink.edu/etdc/view?acc_num=wright1189792837.

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Ammoo, Mohd Shariff. "Development of a design methodology for transport aircraft variable camber flaps suitable for cruise and low-speed operations." Thesis, Cranfield University, 2003. http://dspace.lib.cranfield.ac.uk/handle/1826/11062.

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This thesis describes the development of a generic design methodology for variable camber flap systems for transport aircraft, intended to be used for cruise and low-speed operations. The methodology was structured after several revisions were performed on conventional high-lift device design methodologies for existing transport aircraft. The definition and detail explanations are given at every phase of the methodology. A case study was performed in order to give an example of the implementation of the methodology where a transport aircraft called A TRA, a design study from previous PhD report, was taken as a model. Experimental work could not be performed, due to budget constraints, so the case study was only carried out using computer-based analyses. Software packages such as MSES-code (a Computational Fluid Dynamic software), CATIA and PATRANINASTRAN were used for this case study to analyse aerodynamic characteristics, layout as well as simulation and structure analyses respectively. The results obtained showed that it was practically feasible to deploy such a high-lift device to transport aircraft when the effect from aerodynamic loads gave minimum effect on structural deformation. The deflections of the flap as well as spoilers under critical loads were below the allowable limits, which had a minimal effect due to the additional lift force generated from the movable surfaces.
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Takai, Tomohiro. "Simulation based design for high speed sea lift with waterjets by high fidelity urans approach." Thesis, University of Iowa, 2010. https://ir.uiowa.edu/etd/748.

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Li, Daxin. "Multi-objective design optimization for high-lift aircraft configurations supported by surrogate modeling." Thesis, Cranfield University, 2013. http://dspace.lib.cranfield.ac.uk/handle/1826/8468.

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Nowadays, the competition among airlines seriously depend upon the saving operating costs, with the premise that not to degrade its services quality. Especially in the face of increasingly scarce oil resources, reducing fleets operational fuel consumption, is an important means to improve profits. Aircraft fuel economy is determined by operational management strategies and application technologies. The application of technologies mainly refers to airplane’s engine performance, Weight efficiency and aerodynamic characteristics. A market competitive aircraft should thoroughly consider to all of these aspects. Transport aircraft aerodynamic performance mainly is determined by wing’s properties. Wings that are optimized for efficient flight in cruise conditions need to be fitted with powerful high-lift devices to meet lift requirements for safe takeoff and landing. These high-lift devices have a significant impact on the total airplane performance. The aerodynamic characteristics of the wing airfoil will have a direct impact on the aerodynamic characteristics of the wing, and the wing’s effective cruise hand high-lift configuration design has a significant impact on the performance of transport aircraft. Therefore, optimizing the design is a necessary airfoil design process. Nowadays engineering analysis relies heavily on computer-based solution algorithms to investigate the performance of an engineering system. Computational fluid dynamics (CFD) is one of the computer-based solution methods which are more widely employed in aerospace engineering. The computational power and time required to carry out the analysis increases as the fidelity of the analysis increases. Aerodynamic shape optimization has become a vital part of aircraft design in the recent years. Since the aerodynamic shape optimization (ASO) process with CFD solution algorithms requires a huge amount of computational power, there is always some reluctance among the aircraft researchers in employing the ASO approach at the initial stages of the aircraft design. In order to alleviate this problem, statistical approximation models are constructed for actual CFD algorithms. The fidelity of these approximation models are merely based on the fidelity of data used to construct these models. Hence it becomes indispensable to spend more computational power in order to convene more data which are further used for constructing the approximation models. The goal of this thesis is to present a design approach for assumed wing airfoils; it includes the design process, multi-objective design optimization based on surrogate modelling. The optimization design stared from a transonic single-element single-objective optimization design, and then high-lift configurations were two low-speed conditions of multi-objective optimization design, on this basis, further completed a variable camber airfoil at low speed to high-lift configuration to improve aerodynamic performance. Through this study, prove a surrogate based model could be used in the wing airfoil optimization design.
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Burnazzi, Marco [Verfasser], and Rolf [Akademischer Betreuer] Radespiel. "Design of Efficient High-Lift Configurations with Coanda Flaps / Marco Burnazzi ; Betreuer: Rolf Radespiel." Braunschweig : Technische Universität Braunschweig, 2017. http://d-nb.info/1175817937/34.

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Melin, Tomas. "Multidisciplinary Design in Aeronautics, Enhanced by Simulation-Experiment Synergy." Doctoral thesis, Stockholm : Kungliga Tekniska högskolan, 2006. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3996.

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Atkins, D. W. "The CFD assisted design and experimental testing of a wing-sail with high lift devices." Thesis, University of Salford, 1996. http://usir.salford.ac.uk/14811/.

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A wingsail is a solid symmetrical aerofoil section which creates thrust in the same manner as a conventional sail. Wingsails may either be used as a sole power unit, e. g. for a yacht or catamaran, or as an auxiliary power unit on a larger craft, e. g. fishing vessels, cargo ships or passenger liners. To augment the thrust created by the wingsail, high lift devices are employed to increase both the maximum lift and the stall incidence of the aerofoil. A wingsail must be symmetrical and capable of creating an equal lift force with the flow approaching the leading edge from either side of the wing centreline, i. e. the wingsail surface must act as either the upper, or lower pressure surface. Initial experimental work proved that using a symmetrical slat as a leading edge high lift device both delayed the separation of flow over the wingsail upper surface and increased the effective camber of the aerofoil. To increase the thrust created still further, this leading edge high lift device was combined with a trailing edge high lift device, a symmetrical single slotted flap. Due to the large number of possible model configurations, a commercially available CFD package was introduced to assist with the design. A series of validation tests comparing the CFD with published and experimental results showed a qualitative agreement with these results. However, the CFD predictions were not sufficiently accurate to be used quantitatively. The computationally designed triple element model was tested experimentally. Lift, drag, pitching moment and pressure distribution measurements were taken from the model. The results of this testing showed that the triple element wingsail increased the plain wing Coax by 68% and the stall incidence by between 4* and 6'. The final triple element wingsail design also increased the thrust of a plain wingsail over the whole operating region. Thrust was increased by up to 83% at the wind angles where a wingsail is most efficient. The results also proved that a commercially available CFD package can be used as an effective and time saving tool for wingsail design.
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Dickel, Jacob Allen. "Design Optimization of a Non-Axisymmetric Endwall Contour for a High-Lift Low Pressure Turbine Blade." Wright State University / OhioLINK, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=wright1534980581177159.

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Teichel, Sönke [Verfasser], and Jörg [Akademischer Betreuer] Seume. "Optimized design of mixed flow compressors for an active high-lift system / Sönke Teichel ; Betreuer: Jörg Seume." Hannover : Gottfried Wilhelm Leibniz Universität Hannover, 2018. http://d-nb.info/1168379946/34.

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Books on the topic "High-lift design"

1

Rudolph, Peter K. C. High-lift systems on commercial subsonic airliners. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1996.

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Pittman, Jimmy L. Supersonic, nonlinear, attached-flow wing design for high lift with experimental validation. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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Gatlin, Gregory M. Low-speed, high-lift aerodynamic characteristics of slender, hypersonic accelerator-type configurations. Hampton, Va: Langley Research Center, 1989.

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Hardy, B. C. The aerodynamic design of a model for the RAE 5m wind tunnel to investigate scale effects at low speed and high lift. London: HMSO, 1991.

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Mechanical design of high lift systems for high aspect ratio swept wings. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1998.

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Mechanical design of high lift systems for high aspect ratio swept wings. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1998.

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Center, Ames Research, ed. High-lift systems on commercial subsonic airliners. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1996.

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High-lift systems on commercial subsonic airliners. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1996.

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Center, Ames Research, ed. High-lift systems on commercial subsonic airliners. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1996.

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Center, Ames Research, ed. High-lift systems on commercial subsonic airliners. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1996.

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Book chapters on the topic "High-lift design"

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van der Burg, J. W., and M. Luehmann. "Simulation of Maximum Lift Using URANS for a High-Lift Transport Configuration." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 75–88. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-38877-4_6.

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Reckzeh, D. "Design Work for the A3XX High-Lift-Wing." In New Results in Numerical and Experimental Fluid Mechanics III, 3–10. Berlin, Heidelberg: Springer Berlin Heidelberg, 2002. http://dx.doi.org/10.1007/978-3-540-45466-3_1.

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Fischer, M., H. Bieler, and R. Emunds. "The Noise Criteria within Multidisciplinary High-Lift Design." In New Results in Numerical and Experimental Fluid Mechanics V, 348–56. Berlin, Heidelberg: Springer Berlin Heidelberg, 2006. http://dx.doi.org/10.1007/978-3-540-33287-9_43.

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Brezillon, Joël, Richard P. Dwight, and Markus Widhalm. "Aerodynamic Optimization for Cruise and High-Lift Configurations." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 249–62. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-04093-1_18.

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Landa, Tim, Jochen Wild, and Rolf Radespiel. "Simulation of Longitudinal Vortices on a High-Lift Wing." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 351–66. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-21127-5_21.

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Semaan, Richard, Yosef El Sayed, Stefan Loges, Bernd R. Noack, and Rolf Radespiel. "Active Flow Control Experiments on a High-Lift Configuration." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 77–90. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-52429-6_5.

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Franke, Dirk M. "Aerodynamic Optimization of a High-Lift System with Kinematic Constraints." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 9–16. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-35680-3_2.

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Mouriaux, S., and K. Puri. "High-Lift Low Pressure Turbines T106-A and T106-C." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 465–77. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-62048-6_17.

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Reckzeh, D. "CFD-Methods for the Design Process of High-Lift-Configurations." In Notes on Numerical Fluid Mechanics (NNFM), 347–54. Wiesbaden: Vieweg+Teubner Verlag, 1999. http://dx.doi.org/10.1007/978-3-663-10901-3_45.

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Reckzeh, Daniel, and Heinz Hansen. "High Reynolds-Number Windtunnel Testing for the Design of Airbus High-Lift Wings." In New Results in Numerical and Experimental Fluid Mechanics V, 1–8. Berlin, Heidelberg: Springer Berlin Heidelberg, 2006. http://dx.doi.org/10.1007/978-3-540-33287-9_1.

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Conference papers on the topic "High-lift design"

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Angle, Gerald M., Wade W. Huebsch, Zenovy S. Wowczuk, Jacky C. Prucz, and James E. Smith. "High Lift Circulation Controlled Helicopter Blade." In ASME 8th Biennial Conference on Engineering Systems Design and Analysis. ASMEDC, 2006. http://dx.doi.org/10.1115/esda2006-95602.

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Circulation control techniques have a long history of applications to fixed wing aircraft. General aviation has used circulation control to delay flow separation and increase the maximum lift coefficient achievable with a given airfoil. These techniques have been gradually expanded to other applications, such as ground vehicles, to reduce drag. Circulation control technology can, potentially, be applied also to each blade of the main rotor in a helicopter, in order to increase the lift capacity of the rotor. Applications of circulation control technologies to fixed wing aircraft have demonstrated the potential of a three-fold increase in the lift coefficient, as compared to a conventional airfoil. This finding would suggest that a rotorcraft equipped with circulation control of the main rotor blades could, conceivably, lift up a payload that is approximately three times heavier than the maximum lift capacity of the same helicopter without circulation control. Alternatively, circulation control could reduce the required rotor diameter by up to 48%, if the maximum lift capacity remains unaltered. A High Lift, Circulation Controlled Helicopter Blade will be undergoing initial testing in the subsonic wind tunnel facility at West Virginia University. Two-dimensional elliptic airfoil models with air blowing slots for circulation control will be used as specimens in these tests in order to determine the aerodynamic changes, especially in lift and drag forces, achievable with various blowing slot configurations. Based on the results of the wind tunnel testing, an improved, detailed design will be developed for the entire main rotor of a helicopter with circulation control.
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LOTH, J., and M. FUNK. "Thrust savings limitations with blown high lift wings." In Aircraft Design, Systems and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2884.

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MILLER, D., and R. WOOD. "Aerodynamic design considerations for efficient high-lift supersonicwings." In 3rd Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-4076.

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Katz, Joseph. "High Lift Wing Design for Race-Car Applications." In Aerospace Technology Conference and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1995. http://dx.doi.org/10.4271/951976.

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Antunes, Alexandre, Ricardo da Silva, and Joao Luiz Azevedo. "A Study of Transport Aircraft High-Lift Design Approaches." In 45th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-38.

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Besnard, Eric, Adeline Schmitz, Edwan Boscher, Nicolas Garcia, and Tuncer Cebeci. "Two-dimensional aircraft high lift system design and optimization." In 36th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-123.

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Patterson, Michael D., Nicholas K. Borer, and Brian German. "A Simple Method for High-Lift Propeller Conceptual Design." In 54th AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-0770.

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Eyi, S., K. Lee, S. Rogers, and D. Kwak. "High-lift design optimization using the Navier-Stokes equations." In 33rd Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-477.

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Zhao, Huan, Zhenghong Gao, Chao Wang, and Gao Yuan. "Robust Design of High Speed Natural-Laminar-Flow Airfoil for High Lift." In 55th AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-1414.

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Greenman, Roxana M., and Karlin R. Roth. "High-Lift Optimization Design Using Neural Networks on a Multi-Element Airfoil." In ASME 1998 Design Engineering Technical Conferences. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/detc98/cie-6006.

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Abstract 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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Reports on the topic "High-lift design"

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Allen, Luke, Joon Lim, Robert Haehnel, and Ian Dettwiller. Helicopter rotor blade multiple-section optimization with performance. Engineer Research and Development Center (U.S.), June 2021. http://dx.doi.org/10.21079/11681/41031.

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Abstract:
This paper presents advancements in a surrogate-based, rotor blade design optimization framework for improved helicopter performance. The framework builds on previous successes by allowing multiple airfoil sections to designed simultaneously to minimize required rotor power in multiple flight conditions. Rotor power in hover and forward flight, at advance ratio 𝜇 = 0.3, are used as objective functions in a multi-objective genetic algorithm. The framework is constructed using Galaxy Simulation Builder with optimization provided through integration with Dakota. Three independent airfoil sections are morphed using ParFoil and aerodynamic coefficients for the updated airfoil shapes (i.e., lift, drag, moment) are calculated using linear interpolation from a database generated using C81Gen/ARC2D. Final rotor performance is then calculated using RCAS. Several demonstrative optimization case studies were conducted using the UH-60A main rotor. The degrees of freedom for this case are limited to the airfoil camber, camber crest position, thickness, and thickness crest position for each of the sections. The results of the three-segment case study show improvements in rotor power of 4.3% and 0.8% in forward flight and hover, respectively. This configuration also yields greater reductions in rotor power for high advance ratios, e.g., 6.0% reduction at 𝜇 = 0.35, and 8.8% reduction at 𝜇 = 0.4.
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