Naca 0015 Wing Pressure And Trailing Vortex Measurements

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Naca 0015 Wing Pressure And Trailing Vortex Measurements

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Author :
language : en
Publisher: DIANE Publishing
Release Date :

Naca 0015 Wing Pressure And Trailing Vortex Measurements written by and has been published by DIANE Publishing this book supported file pdf, txt, epub, kindle and other format this book has been release on with categories.

Naca 0015 Wing Pressure And Trailing Vortex Measurements

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Author : Kenneth W. McAlister
language : en
Publisher:
Release Date : 1991

Naca 0015 Wing Pressure And Trailing Vortex Measurements written by Kenneth W. McAlister and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1991 with Aerodynamic load categories.

Naca 0015 Wing Pressure And Trailing Vortex Measurements

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Author : National Aeronautics and Space Adm Nasa
language : en
Publisher:
Release Date : 2018-11-19

Naca 0015 Wing Pressure And Trailing Vortex Measurements written by National Aeronautics and Space Adm Nasa and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-11-19 with categories.

A NACA 0015 semispan wing was placed in a low-speed wind tunnel, and measurements were made of the pressure on the upper and lower surface of the wing and of velocity across the vortex trailing downstream from the tip of the wing. Pressure data were obtained for both 2-D and 3-D configurations. These data feature a detailed comparison between wing tips with square and round lateral edges. A two-component laser velocimeter was used to measure velocity profiles across the vortex at numerous stations behind the wing and for various combinations of conditions. These conditions include three aspect ratios, three chord lengths, a square- and a round lateral-tip, presence or absence of a boundary-layer trip, and three image plane positions located opposite the wing tip. Both pressure and velocity measurements were made for the angles of attack 4 deg less than or equal to alpha less than or equal to 12 deg and for Reynolds numbers 1 x 10(exp 6) less than or equal to Re less than or equal to 3 x 10(exp 6). Mcalister, K. W. and Takahashi, R. K. Ames Research Center LOW SPEED; PRESSURE MEASUREMENT; SEMISPAN MODELS; TRAILING EDGES; VELOCITY MEASUREMENT; VORTICES; WING TIPS; WINGS; ANGLE OF ATTACK; ASPECT RATIO; BOUNDARY LAYERS; LASER DOPPLER VELOCIMETERS; PRESSURE DISTRIBUTION; REYNOLDS NUMBER; VELOCITY DISTRIBUTION; WIND TUNNEL TESTS; WING PROFILES...

Naca 0015 Wing Pressure And Trailing Vortex Measurements

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Author : Kenneth W. McAlister
language : en
Publisher:
Release Date : 1991

Naca 0015 Wing Pressure And Trailing Vortex Measurements written by Kenneth W. McAlister and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1991 with Aerodynamic load categories.

A NACA 0015 semispan wing was placed in a low-speed wind tunnel, and measurements were made of the pressure on the upper and lower surface of the wing and of the velocity across the vortex trailing downstream from the tip of the wing. Pressure data were obtained for both 2D and 3D configurations. These data feature a detailed comparison between wing tips with square and round lateral edges. A two-component laser velocimeter was used to measure velocity profiles across the vortex at numerous stations behind the wing and for various combinations of conditions. These conditions include three aspect ratios, three chord lengths, a square- and a round-lateral tip, presence or absence of a boundary-layer trip, and three image plane positions located opposite the wing tip. Both pressure and velocity measurements were made for angles of attack of 4 deg less then or equal to alpha less then or equal to 12 deg and for Reynolds. numbers of 1 x 10 deg less then or equal to Re less then or equal to 3 x 10 deg. The addition of a round-lateral edge to the wing Up was found to eliminate the secondary vortex near the wing Up, but had little effect on the downs characteristics of the trailing vortex. The increase in wing lift near the Lip because of the presence of the trailing vortex was evident in the surface pressure, but was not captured by circulation-box measurements. The circumferential velocity within the vortex was found to reach free-stream values and produce core rotational speeds as high as 44,000 rpm. The streamwise velocity within the viscous wake that is shed from the wing was observed to form islands of peak velocity in the spiraling sheet that feeds into the trailing vortex.

Scientific And Technical Aerospace Reports

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Author :
language : en
Publisher:
Release Date : 1980

Scientific And Technical Aerospace Reports written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1980 with Aeronautics categories.

Flow Modulation And Fluid Structure Interaction At Airplane Wings

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Author : Josef Ballmann
language : en
Publisher: Springer Science & Business Media
Release Date : 2012-12-06

Flow Modulation And Fluid Structure Interaction At Airplane Wings written by Josef Ballmann and has been published by Springer Science & Business Media this book supported file pdf, txt, epub, kindle and other format this book has been release on 2012-12-06 with Technology & Engineering categories.

The research work of the collaborative research center SFB401 Flow Modulation and Fluid-Structure Interaction at Airplane Wings at the Rheinisch-Westfälische Technische Hochschule (RWTH) Aachen, which is reported in this book, was pos sible due to the financial support of the Deutsche Forschungsgemeinschaft (DFG). The proposal has been approved after evaluation by the referees of DFG selected from other universities and industry, which is gratefully acknowledged. The work is still in progress and now approved to continue until the end of year 2005. More than 50 scientists from universities of the United States, Russia, France, Italy, Japan, Great Britain, Sweden, Netherlands, Switzerland, Austria and research orga nizations NASA, ONERA, NLR, DLR could be invited and have visited the research center, gave seminars on their research on related topics and some of them stayed longer for joined work. Besides its scientific value, also the importance of the pro gram for scientific educa tion becomes evident by looking at the numbers of completed theses, which are up to now about 15 doctoral theses, 40 diploma theses and 70 study theses. The authors of this book acknowledge the valuable support coming from all these persons and institutions. They are especially grateful to the referees having reviewed this work, A. Cohen (Universite Pierre et Marie Curie), J. Cooper (Manchester School of Engineering), W. Devenport (Virginia Tech.), M. Drela (MIT), F. Gern (Avionics Specialties Inc.), A. Griewank (TU Dresden), H. Hönlinger (DLR), P.

Mechanics Of Flight

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Author : Warren F. Phillips
language : en
Publisher: John Wiley & Sons
Release Date : 2004-01-29

Mechanics Of Flight written by Warren F. Phillips and has been published by John Wiley & Sons this book supported file pdf, txt, epub, kindle and other format this book has been release on 2004-01-29 with Science categories.

This comprehensive volume addresses the mechanics of flight through a combination of theory and applications. Topics are presented in a logical order and coverage within each is extensive, including a detailed discussion on the quaterion formulation for six-degree-of-freedom flight.

Mesh Adaption Strategies For Vortex Dominated Flows

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Author : Sean Javad Kamkar
language : en
Publisher: Stanford University
Release Date : 2011

Mesh Adaption Strategies For Vortex Dominated Flows written by Sean Javad Kamkar and has been published by Stanford University this book supported file pdf, txt, epub, kindle and other format this book has been release on 2011 with categories.

A new adaptive mesh refinement strategy that is based on a coupled feature-detection and error-estimation approach is developed. The overall goal is to apply the proper degree of refinement to key vortical features in aircraft and rotorcraft wakes. The refinement paradigm is based on a two-stage process wherein the vortical regions are initially identified for refinement using feature-detection, and then the appropriate resolution is determined by the local solution error. The feature-detection scheme uses a local normalization procedure that allows it to automatically identify regions for refinement with threshold values that are not dependent upon the convective scales of the problem. An error estimator, based on the Richardson Extrapolation method, then supplies the identified features with appropriate levels of refinement. The estimator is shown to be well-behaved for steady-state and time-accurate aerodynamic flows. The above strategy is implemented within the Helios code, which features a dual-mesh paradigm of unstructured grids in the near-body domain, and adaptive Cartesian grids in the off-body domain. A main objective of this work is to control the adaption process so that high fidelity wake resolution is obtained in the off-body domain. The approach is tested on several theoretical and practical vortex-dominated flow-fields in an attempt to resolve wingtip vortices and rotor wakes. Accuracy improvements to rotorcraft performance metrics and increased wake resolution are simultaneously documented.

Computational Fluid Dynamics Review 1998

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Author : M. M. Hafez
language : en
Publisher: World Scientific
Release Date : 1998

Computational Fluid Dynamics Review 1998 written by M. M. Hafez and has been published by World Scientific this book supported file pdf, txt, epub, kindle and other format this book has been release on 1998 with Science categories.

Nasa Scientific And Technical Publications

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Author :
language : en
Publisher:
Release Date : 1993

Nasa Scientific And Technical Publications written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1993 with Aeronautics categories.