V/STOL Wind-tunnel Testing PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download V/STOL Wind-tunnel Testing PDF full book. Access full book title V/STOL Wind-tunnel Testing by . Download full books in PDF and EPUB format.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 78
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 78
Get Book Here
Book Description
Author: Harry H. Heyson
Publisher:
ISBN:
Category : Short take-off and landing aircraft
Languages : en
Pages : 340
Get Book Here
Book Description
Under sufficiently large wake deflections, the forward portion of the wake is found to flow forward along the floor leading to a vortex pattern which results in Rae's limits (Journal of Aircraft, May-June 1967). Although wind-tunnel data cannot normally be corrected successfully beyond these limits, it may be possible to obtain ground-effect data for conditions more severe than those implied by Rae.
Author: A. Krothapalli
Publisher: Springer Science & Business Media
ISBN: 146124840X
Category : Science
Languages : en
Pages : 511
Get Book Here
Book Description
The Joint Institute for Aeronautics and Acoustics at Stanford University was established in October 1973 to provide an academic environment for long-term cooperative research between Stanford and NASA Ames Research Center. Since its establishment, the Institute has conducted theoretical and experimental work in the areas of aerodynamics, acoustics, fluid mechanics, flight dynamics, guidance and control, and human factors. This research has involved Stanford faculty, research associates, graduate students, and many distinguished visitors in collaborative efforts with the research staff of NASA Ames Research Center. The occasion of the Institute's tenth anniversary was used to reflect back on where that research has brought us, and to consider where our endeavors should be directed next. Thus, an International Symposium was held to review recent advances in the fields relevant to the activities of the Institute and to discuss the areas of research to be undertaken in the future. This anniversary was also chosen as an opportunity to honor one of the Institute's founders and its director, Professor Krishnamurty Karamcheti. It has been his crea tive inspiration that has provided the ideal research environment at the Joint Institute.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 42
Get Book Here
Book Description
Author: Ray H. Wright
Publisher:
ISBN:
Category : Interference (Aerodynamics)
Languages : en
Pages : 92
Get Book Here
Book Description
A wind-tunnel test section with closed upper wall, slotted side walls, and open lower boundary was found theoretically to produce zero tunnel-boundary lift interference on a small wing with horizontal wake mounted at the center of the test section. For this test section the variation of the interference with angle of the vortex wake behind a high-lift-coefficient model was not large. Because of the small slot widths required for zero interference and of the effects of boundary layer, the theory is regarded as unreliable for predicting the slot widths required; however, the variation of the interference with the slot width for widths somewhat greater than those needed for zero interference was found to be small. The interference in the region likely to be occupied by the tall of a model was investigated in some detail and was found to change with slot width and with wake angle more strongly than did the interference at the lifting element. A limited investigation of the lift interference in a test section with closed upper wall and slotted side and lower boundaries was made to obtain the theoretically indicated slot width required for zero lift interference at a center-mounted wing with the wake horizontal.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 86
Get Book Here
Book Description
Author: Jewel B. Barlow
Publisher: John Wiley & Sons
ISBN: 0471557749
Category : Technology & Engineering
Languages : en
Pages : 738
Get Book Here
Book Description
A brand-new edition of the classic guide on low-speed wind tunnel testing While great advances in theoretical and computational methods have been made in recent years, low-speed wind tunnel testing remains essential for obtaining the full range of data needed to guide detailed design decisions for many practical engineering problems. This long-awaited Third Edition of William H. Rae, Jr.'s landmark reference brings together essential information on all aspects of low-speed wind tunnel design, analysis, testing, and instrumentation in one easy-to-use resource. Written by authors who are among the most respected wind tunnel engineers in the world, this edition has been updated to address current topics and applications, and includes coverage of digital electronics, new instrumentation, video and photographic methods, pressure-sensitive paint, and liquid crystal-based measurement methods. The book is organized for quick access to topics of interest, and examines basic test techniques and objectives of modeling and testing aircraft designs in low-speed wind tunnels, as well as applications to fluid motion analysis, automobiles, marine vessels, buildings, bridges, and other structures subject to wind loading. Supplemented with real-world examples throughout, Low-Speed Wind Tunnel Testing, Third Edition is an indispensable resource for aerospace engineering students and professionals, engineers and researchers in the automotive industries, wind tunnel designers, architects, and others who need to get the most from low-speed wind tunnel technology and experiments in their work.
Author: M. F. Platzer
Publisher:
ISBN:
Category : Short take-off and landing aircraft
Languages : en
Pages : 552
Get Book Here
Book Description
Author: Harry H. Heyson
Publisher:
ISBN:
Category : Numerical analysis
Languages : en
Pages : 44
Get Book Here
Book Description
An approximate treatment of V/STOL wall interference in a circular tunnel indicates that the interference factors at the model for this tunnel should be of the same order of magnitude as those presently available for a square tunnel of equal cross-sectional area. There is a greater degree of uncertainty with respect to the lateral and longitudinal distributions of interference; however, the available results for the square tunnel should be reasonably close to those of the circular tunnel provided that the model is relatively small in comparison with the test section.
Author:
Publisher:
ISBN:
Category : Short take-off and landing aircraft
Languages : en
Pages : 486
Get Book Here
Book Description
