Download or read book Transonic and Supersonic Flow Past a 65 Degree Delta Wing with Rounded Leading Edges Analysis of Experimental Data written by Krishnaswami Yegna Narayan and published by . This book was released on 1988 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic and Supersonic Flow Past a 65 Delta Wing with Rounded Leading Edges written by Krishnaswami Yegna Narayan and published by . This book was released on 1988 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic and Supersonic Flow Past a 65 Delta Wing with Rounded Leading Edges written by Krishnaswami Yegna Narayan and published by . This book was released on 1988 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic and supersonic flow past a 65e delta wing with rounded leading edges written by and published by . This book was released on 1988 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic and supersonic flow past a 65 delta wing with rounded leading edges written by Krishnaswami Yegna Narayan and published by . This book was released on 1988 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic Ans Supersonic Flow Past a 65 delta Wing with Rounded Leading Edges written by Krishnaswami Yegna Narayan and published by . This book was released on 1988 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1992 with total page 568 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Cities and Their Vital Systems written by Advisory Committee on Technology and Society and published by National Academies Press. This book was released on 1989 with total page 1298 pages. Available in PDF, EPUB and Kindle. Book excerpt: Cities and Their Vital Systems asks basic questions about the longevity, utility, and nature of urban infrastructures; analyzes how they grow, interact, and change; and asks how, when, and at what cost they should be replaced. Among the topics discussed are problems arising from increasing air travel and airport congestion; the adequacy of water supplies and waste treatment; the impact of new technologies on construction; urban real estate values; and the field of "telematics," the combination of computers and telecommunications that makes money machines and national newspapers possible.
Download or read book NASA SP written by and published by . This book was released on 1990 with total page 700 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Influence of Airfoil Geometry on Delta Wing Leading edge Vortices and Vortex induced Aerodynamics at Supersonic Speeds written by Richard M. Wood and published by . This book was released on 1992 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book On the Hypersonic Flow Over a Delta Wing with Very Supersonic Leading Edges written by Norman D. Malmuth and published by . This book was released on 1965 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: For the case of very supersonic leading edges, the inviscid hypersonic flow over the windward side of a symmetrical flat-plate delta wing at incidence is analyzed. The limit selected is that the incidence is of higher order than the aspect ratio as the incidence tends to zero at infinite Mach number. In this framework, the flow regions consist of a two-dimensional domain adjacent to the leading edges and a central conefield. The flow quantities in the central region represent small linear, rotational perturbations about the zero sweep flow. A Riemann-Poincare boundary value problem for the pressure perturbation is formulated. An additional condition involving the sidewash at the shock is found to be required to resolve the indeterminacy of the foregoing boundary value problem. Series solutions and numerical results are presented for the shock shape and the pressure. The behavior of the latter quantity is found to be similar to that given by the irrotational linear solution for the supersonic leading edge case. Finally, the relationship between the present application and others involving diffraction problems and corner flows is indicated.
Download or read book Transonic Navier Stokes Calculations about a 65 Deg Delta Wing written by and published by . This book was released on 1994 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautical Engineering written by and published by . This book was released on 1993 with total page 712 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Download or read book Surface Pressure and Flow Visualization Data at Mach Number of 1 60 for Three 65 Deg Delta Wings Varying in Leading Edge Radius and Camber written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-04 with total page 268 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the effect of leading-edge radius, camber, Reynolds number, and boundary-layer state on the incipient separation of a delta wing at supersonic speeds was conducted at the Langley Unitary Plan Wind Tunnel at Mach number of 1.60 over a free-stream Reynolds number range of 1 x 106 to 5 x 106 ft-1. The three delta wing models examined had a 65 deg swept leading edge and varied in cross-sectional shape: a sharp wedge, a 20:1 ellipse, and a 20:1 ellipse with a -9.750 circular camber imposed across the span. The wings were tested with and without transition grit applied. Surface-pressure coefficient data and flow-visualization data indicated that by rounding the wing leading edge or cambering the wing in the spanwise direction, the onset of leading-edge separation on a delta wing can be raised to a higher angle of attack than that observed on a sharp-edged delta wing. The data also showed that the onset of leading-edge separation can be raised to a higher angle of attack by forcing boundary-layer transition to occur closer to the wing leading edge by the application of grit or the increase in free-stream Reynolds number. McMillin, S. Naomi and Bryd, James E. and Parmar, Devendra S. and Bezos-OConnor, Gaudy M. and Forrest, Dana K. and Bowen, Susan Langley Research Center NASA-TM-4673, NAS 1.15:4673, L-17443 RTOP 505-59-53-05...
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1998 with total page 920 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Controlled Vortical Flow on Delta Wings Through Unsteady Leading Edge Blowing written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-11-18 with total page 162 pages. Available in PDF, EPUB and Kindle. Book excerpt: The vortical flow over a delta wing contributes an important part of the lift - the so called nonlinear lift. Controlling this vortical flow with its favorable influence would enhance aircraft maneuverability at high angle of attack. Several previous studies have shown that control of the vortical flow field is possible through the use of blowing jets. The present experimental research studies vortical flow control by applying a new blowing scheme to the rounded leading edge of a delta wing; this blowing scheme is called Tangential Leading Edge Blowing (TLEB). Vortical flow response both to steady blowing and to unsteady blowing is investigated. It is found that TLEB can redevelop stable, strong vortices even in the post-stall angle of attack regime. Analysis of the steady data shows that the effect of leading edge blowing can be interpreted as an effective change in angle of attack. The examination of the fundamental time scales for vortical flow re-organization after the application of blowing for different initial states of the flow field is studied. Different time scales for flow re-organization are shown to depend upon the effective angle of attack. A faster response time can be achieved at angles of attack beyond stall by a suitable choice of the initial blowing momentum strength. Consequently, TLEB shows the potential of controlling the vortical flow over a wide range of angles of attack; i.e., in both for pre-stall and post-stall conditions. Lee, K. T. and Roberts, Leonard BLOWING; DELTA WINGS; FLOW DISTRIBUTION; LEADING EDGES; VORTICES; AIRCRAFT MANEUVERS; ANGLE OF ATTACK; MOMENTUM; NONLINEARITY; STABILITY...
