Relevant bibliographies by topics / Cambered wings

Contents

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

Academic literature on the topic 'Cambered wings'

Author: Grafiati
Published: 4 June 2021
Last updated: 14 February 2022

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the lists of relevant articles, books, theses, conference reports, and other scholarly sources on the topic 'Cambered wings.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Journal articles on the topic "Cambered wings"

1

Harbig, R. R., J. Sheridan, and M. C. Thompson. "Relationship between aerodynamic forces, flow structures and wing camber for rotating insect wing planforms." Journal of Fluid Mechanics 730 (July 30, 2013): 52–75. http://dx.doi.org/10.1017/jfm.2013.335.

Full text
Abstract:
AbstractWing deformation is observed during the flight of some insect species; however, the effect of these distorted wing shapes on the leading edge vortex (LEV) is not well understood. In this study, we investigate the effect of one of these deformation parameters, (rigid) wing camber, on the flow structures and aerodynamic forces for insect-like wings, using a numerical model of an altered fruit fly wing revolving at a constant angular velocity. Both positive and negative camber was investigated at Reynolds numbers of 120 and 1500, along with the chordwise location of maximum camber. It was found that negatively cambered wings produce very similar LEV structures to non-cambered wings at both Reynolds numbers, but high positive camber resulted in the formation of multiple streamwise vortices at the higher Reynolds number, which disrupt the development of the main LEV. Despite this, positively cambered wings were found to produce higher lift to drag ratios than flat or negatively cambered wings. It was determined that a region of low pressure near the wing’s leading edge, combined with the curvature of the wing’s upper surface in this region, resulted in a vertical tilting of the net force vector for positively cambered wings, which explains how insects can benefit from wing camber.
APA, Harvard, Vancouver, ISO, and other styles
2

Walker, Simon M., Adrian L. R. Thomas, and Graham K. Taylor. "Deformable wing kinematics in the desert locust: how and why do camber, twist and topography vary through the stroke?" Journal of The Royal Society Interface 6, no. 38 (December 16, 2008): 735–47. http://dx.doi.org/10.1098/rsif.2008.0435.

Full text
Abstract:
Here, we present a detailed analysis of the wing kinematics and wing deformations of desert locusts ( Schistocerca gregaria , Forskål) flying tethered in a wind tunnel. We filmed them using four high-speed digital video cameras, and used photogrammetry to reconstruct the motion of more than 100 identified points. Whereas the hindwing motions were highly stereotyped, the forewing motions showed considerable variation, consistent with a role in flight control. Both wings were positively cambered on the downstroke. The hindwing was cambered through an ‘umbrella effect’ whereby the trailing edge tension compressed the radial veins during the downstroke. Hindwing camber was reversed on the upstroke as the wing fan corrugated, reducing the projected area by 30 per cent, and releasing the tension in the trailing edge. Both the wings were strongly twisted from the root to the tip. The linear decrease in incidence along the hindwing on the downstroke precisely counteracts the linear increase in the angle of attack that would otherwise occur in root flapping for an untwisted wing. The consequent near-constant angle of attack is reminiscent of the optimum for a propeller of constant aerofoil section, wherein a linear twist distribution allows each section to operate at the unique angle of attack maximizing the lift to drag ratio. This implies tuning of the structural, morphological and kinematic parameters of the hindwing for efficient aerodynamic force production.
APA, Harvard, Vancouver, ISO, and other styles
3

Traub, L. W., R. Waghela, and K. A. Bordignon. "Characterisation of a highly staggered spanwise cambered biplane." Aeronautical Journal 119, no. 1212 (February 2015): 203–28. http://dx.doi.org/10.1017/s0001924000010344.

Full text
Abstract:
AbstractAn investigation is presented to elucidate the performance of a staggered, spanwise cambered biplane. The spanwise camber yielded wings forming a ‘∧’ or ‘∨’ when viewed streamwise. The configuration is examined in terms of its aerodynamic and stability characteristics. The feasibility of negating the requirement for a conventional empennage is explored. Geometric variation encompassed front and back wing anhedral/dihedral angles yielding 49 combinations. Evaluation of the geometry was accomplished using both wind tunnel testing and numerical simulation. The results indicated that front wing dihedral in conjunction with aft wing anhedral was most beneficial, such that the benefit of wake spacing was maximised. Aerodynamic benefit was indicated compared to a conventional empennage geometry. The greatest disparity in behaviour of the fore and aft wing anhedral/dihedral distribution was in the high lift regime, where the nature of the stall varied. Simulations to establish the viability of the geometry in terms of controllability were also conducted and indicated that the configuration is viable.
APA, Harvard, Vancouver, ISO, and other styles
4

Traub, Lance W. "Lift Prediction of Spanwise Cambered Delta Wings." Journal of Aircraft 36, no. 3 (May 1999): 515–22. http://dx.doi.org/10.2514/2.2486.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

Traub, Lance W. "Aerodynamic Characteristics of Spanwise Cambered Delta Wings." Journal of Aircraft 37, no. 4 (July 2000): 714–24. http://dx.doi.org/10.2514/2.2657.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

Wootton, R. J., K. E. Evans, R. Herbert, and C. W. Smith. "The hind wing of the desert locust (Schistocerca gregaria Forskal). I. Functional morphology and mode of operation." Journal of Experimental Biology 203, no. 19 (October 1, 2000): 2921–31. http://dx.doi.org/10.1242/jeb.203.19.2921.

Full text
Abstract:
Detailed morphological investigation, mechanical testing and high-speed cinematography and stroboscopic examination of desert locusts, Schistocerca gregaria, in flight show that their hind wings are adapted to deform cyclically and automatically through the wing stroke and that the deformations are subtly dependent on the wings' structure: their shape, venation and vein design and the local properties of the membrane. The insects predominantly fly fast forwards, generating most force on the downstroke, and the hind wings generate extra lift by peeling apart at the beginning of the downstroke and by developing a cambered section during the stroke's translation phase through the ‘umbrella effect’ - an automatic consequence of the active extension of the wings' expanded posterior fan. Bending experiments indicate that most of the hind wing is more rigid to forces from below than from above and demonstrate that the membrane acts as a stressed skin to stiffen the structure.
APA, Harvard, Vancouver, ISO, and other styles
7

Forster, K. J., and T. R. White. "Numerical Investigation into Vortex Generators on Heavily Cambered Wings." AIAA Journal 52, no. 5 (May 2014): 1059–71. http://dx.doi.org/10.2514/1.j052529.

Full text
APA, Harvard, Vancouver, ISO, and other styles
8

Wrist, Andrew H., and James P. Hubner. "Aerodynamic comparisons of flexible membrane micro air vehicle wings with cambered and flat frames." International Journal of Micro Air Vehicles 10, no. 1 (May 29, 2017): 12–30. http://dx.doi.org/10.1177/1756829317705327.

Full text
Abstract:
Flexible membrane wings at the micro air vehicle scale can experience improved lift/drag ratios, delays in stall, and decreased time-averaged flow separation when compared to rigid wings. This research examines the effect of frame camber on the aerodynamic characteristics of membrane wings. The frames for the wings were 3D printed using a polymer-based material. The membranes are silicone rubber. Tests were conducted at Re ∼50,000. Aerodynamic force and moment measurements were acquired at angles-of-attack varying from −4 to 24°. Additionally, digital image correlation data were acquired to assess time-averaged shapes of the membrane wings during wind tunnel tests. An in-house program was developed to average the deflection plots from the digital image correlation images and produce time-averaged shapes. Lifting-line theory based on the time-averaged shapes was then used to calculate theoretical lift and induced drag coefficients, showing that the time-average shape of the membrane under load contributes extensively to the aerodynamic performance. The results show that introducing camber to the frames of membrane wings increases aerodynamic efficiency.
APA, Harvard, Vancouver, ISO, and other styles
9

ENNOS, A. ROLAND, and ROBIN J. WOOTTON. "FUNCTIONAL WING MORPHOLOGY AND AERODYNAMICS OF PANORPA GERMANICA (INSECTA: MECOPTERA)." Journal of Experimental Biology 143, no. 1 (May 1, 1989): 267–84. http://dx.doi.org/10.1242/jeb.143.1.267.

Full text
Abstract:
The functional wing morphology of the wings of the scorpion fly Panorpa germanica L. was investigated using a combination of light microscopy, high-speed cinematography, wing manipulation and mechanical testing In rising forward flight the wings are flapped 40° out of phase along a shallow stroke plane, the forewings leading. Aerodynamic analysis suggests that unsteady effects are important in flight During the downstroke, both wings are straight and cambered, the chord being parallel to the body axis, which is angled 45° upwards from horizontal. Both wings are supinated at lower stroke reversal, the hindwing to a much greater extent, and flex ventrally halfway along their length for the first half of the upstroke. Flexion is parallel to the chord in the hindwing, but is oblique in the forewing, so distal forewing areas are supinated relative to proximal areas The behaviour of the wings is related to their structure. Spars at the leading and trailing edges of both wings support the wing during the downstroke, and flexion during the upstroke is facilitated by buckling of the weak ventral thyridium region. The oblique flexion seen in the forewing is due to its relatively longer leading edge spar The differences between the wings are, in turn, related to their pitch control mechanisms. The forewing has a well-developed clavus, like that of the forewing of a locust, and pitch is altered by relative movement of this and the leading edge, but only within a narrow range. Oblique flexion is necessary to invert the aerofoil. The weaker and less well-developed clavus of the hindwing, more similar to that of the Diptera, allows a greater degree of supination, effected largely by wing inertia. No oblique flexion is necessary
APA, Harvard, Vancouver, ISO, and other styles
10

Traub, Lance W. "Analytic Drag Prediction for Cambered Wings with Partial Leading Edge Suction." Journal of Aircraft 46, no. 1 (January 2009): 312–19. http://dx.doi.org/10.2514/1.38558.

Full text
APA, Harvard, Vancouver, ISO, and other styles
More sources

Dissertations / Theses on the topic "Cambered wings"

1

Rao, A. J. "Variable camber wings for transport aircraft." Thesis, Cranfield University, 1989. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.237551.

Full text
APA, Harvard, Vancouver, ISO, and other styles
2

Wiggins, Leonard D. III. "Structural Design and Analysis of a Kinematic Mechanism for a Morphing Hyper-Elliptic Cambered Span (HECS) Wing." Thesis, Virginia Tech, 2003. http://hdl.handle.net/10919/9668.

Full text
Abstract:
The HECS wing was developed by NASA Langley Research Center and has a nonplanar, hyper-elliptically swept leading and trailing edge as well as spanwise camber. For this wing, the leading and trailing edges are swept back according to a hyper-elliptical equation. The span of the wing is also defined with hyper-elliptical anhedral giving it nonplanar spanwise camber. A single-degree-of-freedom mechanism is developed to provide a means for the wing to continuously change shape from its nonplanar to planar configuration. The mechanism uses a repeating quaternary-binary link configuration to translate motion from one segment to the next. A synthesis of the mechanism is performed, such that with one input to the first segment of the chain, the other wing segments move into their desired positions. Linear aerodynamic theory is applied to the HECS wing configuration at certain morphed positions in order to predict the aerodynamic loads. This work performs a linear static analysis of the mechanism at different morphed positions. A finite element representation of the mechanism as a structure is developed. Using the predicted aerodynamic loads, a structural analysis is performed. The analysis investigates different materials and cross sections of the members to determine a need for redesign due to failure from buckling and bending stress. From the analysis of the mechanism, a design is finalized which lightens the structure as well as increases the strength. These results are beneficial for the next phase of model development of the mechanism.
Master of Science
APA, Harvard, Vancouver, ISO, and other styles
3

Sakarya, Evren. "Structural Design And Evaluation Of An Adaptive Camber Wing." Master's thesis, METU, 2010. http://etd.lib.metu.edu.tr/upload/12611514/index.pdf.

Full text
Abstract:
This study presents a camber morphing concept as an alternative to existing plain flap or aileron type hinged control surfaces used in wings. Structural aspects of the concept are investigated with static nonlinear finite element analyses by using MSC Nastran. In order to assess the aerodynamic characteristics
CFD based 2D solutions are obtained using ANSYS Fluent. The camber morphing concept is applied to the full scale hingeless control surface and implemented in the adaptive camber wing. Hingeless control surfaces and adaptive camber wing are manufactured and changes made in manufacture stages are incorporated into finite element models. Finite element analyses of the wing are conducted with static and dynamic loading and comparison with experimental dynamic analyses are performed.
APA, Harvard, Vancouver, ISO, and other styles
4

MacKinnon, A. V. "An experimental study of a variable camber wing (VCW)." Thesis, Cranfield University, 1993. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.359503.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

Miller, Samuel C. "Fluid-Structure Interaction of a Variable Camber Compliant Wing." University of Dayton / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1428575972.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

Poonsong, Prasobchok. "Design and analysis of a multi-section variable camber wing." College Park, Md. : University of Maryland, 2004. http://hdl.handle.net/1903/221.

Full text
Abstract:
Thesis (M.S.) -- University of Maryland, College Park, 2004.
Thesis research directed by: Dept. of Aerospace Engineering. Title from t.p. of PDF. Includes bibliographical references. Published by UMI Dissertation Services, Ann Arbor, Mich. Also available in paper.
APA, Harvard, Vancouver, ISO, and other styles
7

Balasubramanian, Karthik. "Novel, Unified, Curvature-Based Airfoil Parameterization Model for Turbomachinery Blades and Wings." University of Cincinnati / OhioLINK, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1535459266289742.

Full text
APA, Harvard, Vancouver, ISO, and other styles
8

Macci, S. H. M. "Structural and mechanical feasibility study of a variable camber wing (VCW) for a transport aircraft." Thesis, Cranfield University, 1992. http://hdl.handle.net/1826/4168.

Full text
Abstract:
Aerodynamic investigations have shown' that variable camber wings (VCW) for transport aircraft have considerable potential in terms of improving aircraft performance and enhancing their operational flexibility. In order to justify these benefits it is essential that the camber varying system is structurally and mechanically feasible. This research examined the feasibility of providing variable camber to two supercritical aerofoil sections of different'characteristics. The unique method of camber vaTiation was applied by rotating the forward and aft regions of the aerofoil on a circular arc and keeping the surface continuous and matching at their attachment to the main wing box. The change in camber thus increased the chord due to translational motion of the aforementioned regions. The geometries required for varying the forward camber by this method presented formidable design difficulties and no immediate solutions could be found. As a result, an alternative geometry was devised which accepts camber by simply drooping the nose region. A novel idea was developed for aft camber variation, which is considered to be universal for all supercritical aerofoil sections. The system utilises a tracking mechanism which guides a trailing edge element on a continuous arc. Surface continuity is provided by a flexible skin on the upper side and a spring loaded hinged panel on the under side. The flexible skin remains attached to the trailing edge element through a series of roller link arrangement which locate the skin in a separate guide rail. The large moment arm and therefore the increased torsional loads created due to the translational motion of the trailing edge element necessitated investigation of alternative deployment geometries. As a result two additional geometries were schemed. One had reduced radius of rotation and therefore reduced extension, while the other changed camber by drooping the aft region without any chordal extension. Since there was no aerodynamic evidence on the possible benefits offered by these geometries it was decide to postpone them until such information was available. Some detailed aspects of the proposed concept for aft camber variation were considered by applying the system to a modem transport aircraft wing. This resulted in a design which is practically feasible. Justification of this concept was made by designing and testing a half scale structural model of one trailing edge segment. Three dimensional (3-D) geometric investigation showed that the camber-varying elements ride on a frustum of a cone and therefore their deployment is skewed to the line of flight. The 3-D geometric implications of variable camber clearly suggested that the camber variation by rotation on a circular arc, on a tapered wing can be possible if the rotating element is made to flex and twist or it utilises a pin jointed arrangement. To provide the necessary flexibility to the trailing edge element, its structural box best be made from fibre reinforced plastic material. The deployment of the trailing edge element on the structural m(; del was made possible by designing it in laminated wood. Comparison of the proposed variable camber system with a conventional single slotted flap arrangement suggests that the two systems could be equally complex but the variable camber could be slightly heavier., Further systems investigations are required to quantify overall aerodynamic, mass, and cost implications of the use of VCW on transport aircraft.
APA, Harvard, Vancouver, ISO, and other styles
9

Martins, Pires Rui Miguel. "Design methodology for wing trailing edge device mechanisms." Thesis, Cranfield University, 2007. http://hdl.handle.net/1826/3393.

Full text
Abstract:
Over the last few decades the design of high lift devices has become a very important part of the total aircraft design process. Reviews of the design process are performed on a regular basis, with the intent to improve and optimize the design process. This thesis describes a new and innovative methodology for the design and evaluation of mechanisms for Trailing Edge High-Lift devices. The initial research reviewed existing High-Lift device design methodologies and current flap systems used on existing commercial transport aircraft. This revealed the need for a design methodology that could improve the design process of High-Lift devices, moving away from the conventional "trial and error" design approach, and cover a wider range of design attributes. This new methodology includes the use of the innovative design tool called SYNAMEC. This is a state-of-the-art engineering design tool for the synthesis and optimizations of aeronautical mechanisms. The new multidisciplinary design methodology also looks into issues not usually associated with the initial stages of the design process, such as Maintainability, Reliability, Weight and Cost. The availability of the SYNAMEC design tool and its ability to perform Synthesis and Optimization of mechanisms led to it being used as an important module in the development of the new design methodology. The SYNAMEC tool allows designers to assess more mechanisms in a given time than the traditional design methodologies. A validation of the new methodology was performed and showed that creditable results were achieved. A case study was performed on the ATRA - Advance Transport Regional Aircraft, a Cranfield University design project, to apply the design methodology and select from within a group of viable solutions the most suitable type of mechanism for the Variable Camber Wing concept initially defined for the aircraft. The results show that the most appropriate mechanism type for the ATRA Variable Camber Wing is the Link /Track Mechanism. It also demonstrated how a wide range of design attributes can now be considered at a much earlier stage of the design.
APA, Harvard, Vancouver, ISO, and other styles
10

Zientarski, Lauren Ann. "Wind Tunnel Testing of a Variable Camber Compliant Wing with a Unique Dual Load Cell Test Fixture." University of Dayton / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1448893315.

Full text
APA, Harvard, Vancouver, ISO, and other styles

Books on the topic "Cambered wings"

1

Bolonkin, Alexander. Estimated benefits of variable-geometry wing camber control for transport aircraft. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1999.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
2

MacKinnon, A. Wind tunnel tests on a variable camber wing. Cranfield, Bedford, England: College of Aeronautics, Cranfield University, 1993.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
3

Wood, Richard M. Study of lee-side flows over conically cambered delta wings at supersonic speeds. Hampton, Va: Langley Research Center, 1987.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
4

Chu, Julio. Pressure meaurements on a thick cambered and twisted 58 [degree] delta wing at high subsonic speeds. Hampton, Va: Langley Research Center, 1987.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
5

Wood, Richard M. Study of lee-side flows over conically cambered delta wings at supersonic speeds. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
6

Gilyard, Glenn B. In-flight transport performance optimization: An experimental flight research program and an operational scenario. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1997.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
7

Gilyard, Glenn B. In-flight transport performance optimization: An experimental flight research program and an operational scenario. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1997.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
8

Ashill, P. R. Control of leading-edge separation on a cambered delta wing. Farnborough: Defence Research Agency, 1993.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
9

Smith, John W. Variable-camber systems integration and operational performance of the AFTI/F-111 mission adaptive wing. Edwards, California: NASA Dryden Flight Research Facility, 1992.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
10

W, Smith John. Variable-camber systems integration and operational performance of the AFTI/F-111 mission adaptive wing. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Office, 1992.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
More sources

Book chapters on the topic "Cambered wings"

1

Giraud, Alexandre, Martin Cronel, Ioav Ramos, and Bertrand Nogarede. "Camber Actuation of an Articulated Wing with Electromechanical Actuators." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 441–53. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-55594-8_36.

Full text
APA, Harvard, Vancouver, ISO, and other styles
2

Jodin, G., J. F. Rouchon, J. Schller, N. Simiriotis, M. Triantafyllou, S. Cazin, P. Elyakime, M. Marchal, and M. Braza. "Electroactive Morphing Vibrating Trailing Edge of a Cambered Wing: PIV, Turbulence Manipulation and Velocity Effects." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 427–39. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-55594-8_35.

Full text
APA, Harvard, Vancouver, ISO, and other styles
3

Giraud, A., Cédric Raibaudo, Martin Cronel, Philippe Mouyon, Ioav Ramos, and Carsten Doll. "Camber Setting of a Morphing Wing with Macro-acuator Feedback Control." In Fluid-Structure-Sound Interactions and Control, 229–36. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-33-4960-5_36.

Full text
APA, Harvard, Vancouver, ISO, and other styles
4

Carvalho, Mateus, Cédric Raibaudo, Sébastien Cazin, Moïse Marchal, G. Harran, Clément Nadal, J. F. Rouchon, and M. Braza. "Dynamics of a Cambered A320 Wing by Means of SMA Morphing and Time-Resolved PIV at High Reynolds Number." In Fluid-Structure-Sound Interactions and Control, 283–93. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-33-4960-5_44.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

Liu, Yi, Shaoxiu Ouyang, and Xiaoxia Zhao. "Drag Reduction Effect of a Variable Camber Wing of a Transport Aircraft Based on Trailing Edge Flap Deflection of Small Angles." In Lecture Notes in Electrical Engineering, 1508–14. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_120.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

ESPAÑA, MARTÍN, and GLENN GILYARD. "ADAPTIVE WING CAMBER OPTIMIZATION: A PERIODIC PERTURBATION APPROACH." In Automatic Control in Aerospace 1994 (Aerospace Control '94), 35–40. Elsevier, 1995. http://dx.doi.org/10.1016/b978-0-08-042238-1.50009-4.

Full text
APA, Harvard, Vancouver, ISO, and other styles

Conference papers on the topic "Cambered wings"

1

Shkarayev, Sergey, Dmitro Silin, Gregg Abate, and Roberto Albertani. "Aerodynamics of Cambered Membrane Flapping Wings." In 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-58.

Full text
APA, Harvard, Vancouver, ISO, and other styles
2

Pomeroy, Brent, and Kenneth Visser. "A Computational Study of Induced Drag Behavior for Spanwise Cambered Wings." In 28th AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-4227.

Full text
APA, Harvard, Vancouver, ISO, and other styles
3

Wrist, Andrew H., Zheng Zhang, David Pepley, and James P. Hubner. "Aerodynamic Comparison of Flat and Cambered Frames for Flexible MAV Wings." In 53rd AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-1299.

Full text
APA, Harvard, Vancouver, ISO, and other styles
4

Peel, Larry D., James Mejia, Ben Narvaez, Kyle Thompson, and Madhuri Lingala. "Development of a Simple Morphing Wing Using Elastomeric Composites as Skins and Actuators." In ASME 2008 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. ASMEDC, 2008. http://dx.doi.org/10.1115/smasis2008-544.

Full text
Abstract:
Morphing wings are desired for their ability to reduce drag, change flight characteristics, and perhaps reduce weight by eliminating flap / aileron mechanisms. Development of two generations of a student morphing wing project is documented. The second wing was further developed by Peel. The work shows how a relatively low cost but realistic morphing wing test-bed can be fabricated. Wing skin, actuator, and actuator attachment development are discussed, as well as possible auxetic skin behavior. Aerodynamic characterization of the wing will be discussed in another paper. A very simple morphing wing was fabricated in phase one. The nose was able to elastically camber down ∼ 25° and the tail 20°. Actuation was provided by three pneumatic “Rubber Muscle Actuators” (RMA) that produce high contractive forces. Upper and lower wing skins were fabricated from carbon fiber / polyurethane elastomer laminates. Lower skin buckling, actuator air leaks and actuator attachment problems were resolved in the second phase. A finite element model of the generation II wing was developed and is being used to refine/ explore the morphing wing test-bed. The second generation wing fabrication methodology shows smooth elastic cambering and no buckling or waviness in the skins. The nose cambered down 23° and the tail cambered down to 15°. Improved leak-free biomimetic actuators and attach points now include no metal parts, have higher actuation forces due to new braided sheaths and functionally gradient matrix properties.
APA, Harvard, Vancouver, ISO, and other styles
5

Blake, Doug, and Bruce P. Selberg. "Non Linear Induced Drag Study of Generically Cambered Closely Coupled Dual Wings." In Aerospace Technology Conference and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1991. http://dx.doi.org/10.4271/912126.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

Lazos, Barry, and Kenneth Visser. "Aerodynamic Comparison of Hyper-Elliptic Cambered Span (HECS) Wings with Conventional Configurations." In 24th AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-3469.

Full text
APA, Harvard, Vancouver, ISO, and other styles
7

Wrist, Andrew H., and James P. Hubner. "Theoretical Investigation of the Aerodynamics of Membrane MAV Wings with Cambered Frames." In 54th AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-0831.

Full text
APA, Harvard, Vancouver, ISO, and other styles
8

Stubbs, Matthew D., William B. Whittier, and Charles F. Reinholtz. "Single Degree-of-Freedom Morphing Wing (Design and Synthesis)." In ASME 2004 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2004. http://dx.doi.org/10.1115/detc2004-57019.

Full text
Abstract:
Recent research in morphing wing technology has focused on complex multiple-degree-of-freedom (MDOF) mechanisms and smart structures to provide a specified shape change; single degree-of-freedom actuation concepts have generally been ignored or overlooked. In this research, the authors propose a novel design for a single degree-of-freedom (SDOF) mechanism for mission morphing of aircraft wings. A general design methodology has been developed, and this has been applied to a Hyper-Elliptic Cambered Span (HECS) wing developed by engineers at NASA Langley Research Center. The design tools developed include a synthesis procedure for determining the dimensions of the single-degree-of-freedom morphing mechanism, and a sensitivity analysis to determine the effects of manufacturing errors.
APA, Harvard, Vancouver, ISO, and other styles
9

WOOD, RICHARD, and PETER COVELL. "Flow visualization model of the leeside flows over conically cambered delta wings at supersonic speeds." In 5th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2477.

Full text
APA, Harvard, Vancouver, ISO, and other styles
10

Colpitts, Robert R., Alexi Levert-Beaulieu, and Ruben E. Perez. "Effect of Various Cambered Airfoil Profiles to Wings with Leading Edge Tubercles in Transonic Flow." In AIAA Scitech 2021 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-0468.

Full text
APA, Harvard, Vancouver, ISO, and other styles

Reports on the topic "Cambered wings"

1

Rade, Domingos A., and Francisco J. de Souza. Variable Camber Morphing Wings. Fort Belvoir, VA: Defense Technical Information Center, February 2016. http://dx.doi.org/10.21236/ad1009258.

Full text
APA, Harvard, Vancouver, ISO, and other styles
You might also be interested in the extended bibliographies on the topic 'Cambered wings' for particular source types:
Journal articles Books
We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!

To the bibliography