Download or read book Some Preliminary Data on Vortex Height Over a Slender Delta Wing at Supersonic Speeds written by A. W. Sharp and published by . This book was released on 1960 with total page 10 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Some Preliminary Data on Vortex Position Over a Slender Delta Wing at Supersonic Speeds written by A. W. Sharp and published by . This book was released on 1959 with total page 11 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 Lee side Flow Over Delta Wings at Supersonic Speeds written by David S. Miller and published by . This book was released on 1985 with total page 160 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Leeward Flow Over Delta Wings at Supersonic Speeds written by and published by . This book was released on 1980 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Vortex Flows at Supersonic Speeds written by Richard M. Wood and published by . This book was released on 2003 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Vortex Flows at Supersonic Speeds written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-15 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt: A review of research conducted at the National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC) into high-speed vortex flows during the 1970s, 1980s, and 1990s is presented. The data are for flat plates, cavities, bodies, missiles, wings, and aircraft with Mach numbers of 1.5 to 4.6. Data are presented to show the types of vortex structures that occur at supersonic speeds and the impact of these flow structures on vehicle performance and control. The data show the presence of both small- and large-scale vortex structures for a variety of vehicles, from missiles to transports. For cavities, the data show very complex multiple vortex structures exist at all combinations of cavity depth to length ratios and Mach number. The data for missiles show the existence of very strong interference effects between body and/or fin vortices. Data are shown that highlight the effect of leading-edge sweep, leading-edge bluntness, wing thickness, location of maximum thickness, and camber on the aerodynamics of and flow over delta wings. Finally, a discussion of a design approach for wings that use vortex flows for improved aerodynamic performance at supersonic speeds is presented. Wood, Richard M. and Wilcox, Floyd J., Jr. and Bauer, Steven X. S. and Allen, Jerry M. Langley Research Center WU 706-51-21-10
Download or read book Flow Studies on Flat plate Delta Wings at Supersonic Speed written by William H. Michael and published by . This book was released on 1955 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results show that theoretical aerodynamic calculations, such as those in NACA TN 3430, utilizing a single, separated vortex pair above wing upper surface to represent the separated vorticity can be applied at supersonic speeds for very slender wings.
Download or read book Theoretical and Experimental Longitudinal Aerodynamic Characteristics of an Aspect Ratio 0 25 Sharp edge Delta Wing at Subsonic Supersonic and Hypersonic Speeds written by Charles H. Fox and published by . This book was released on 1974 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: The suction analogy concept of Polhamus for predicting vortex lift in conjunction with an appropriate potential-flow solution is called the present method. This method is applied herein to an aspect ratio of 0.25 sharp-edge delta wing from a Mach number of 0.143 to 10.4 in free air and at 0.074 in ground effect, and also to an aspect ratio of 0.35 triangular cross-sectional body at Mach number of 6.9. The models had subsonic leading edges at the test Mach numbers. Vortex-flow effects could be neither confirmed nor denied to exist at high speeds because of the lack of flow visualization above a Mach number of 0.143. The data, however, could be better predicted by including a vortex-flow effect, although not always to the extent predicted from the present method because of the presence of actual and hypothesized unmodeled flow situations.
Download or read book Some Preliminary Results on a Conically Cambered Delta Wing at Supersonic Speeds written by and published by . This book was released on 1960 with total page 13 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of Methods for Computing Flutter Characteristics of Supersonic Delta Wings and Comparison with Experimental Data written by Charles Harold Wilts and published by . This book was released on 1959 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Some Data on the Flow Field in Depth Around a Slender Delta Wing at Supersonic Speed written by A. W. Sharp and published by . This book was released on 1960 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Paper written by and published by . This book was released on 1987 with total page 244 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Study of Lee side Flows Over Conically Cambered Delta Wings at Supersonic Speeds Part 1 written by and published by . This book was released on 1987 with total page 222 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Study of Lee side Flows Over Conically Cambered Delta Wings at Supersonic Speeds written by Richard M. Wood and published by . This book was released on 1987 with total page 220 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Vortex Formation Over Delta Double Delta and Wave Rider Configurations at Supersonic Speeds written by Uwe Ganzer and published by . This book was released on 1987 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: The flow field of the thick delta wing at high subsonic and at supersonic speeds has been the subject of quite a variety of investigations at the Technical University of Berlin. The research work started as early as in the late 60s and is still going on today. It was triggered off by the initiatives of the late 'Dietrich Kuechemann-aiming' at a hypersonic transport and it was taken as a contribution to the Eurohyp activities. The wing configurations investigated at the Technical University of Berlin were of simple shape: Delta wings with straight leading edges and triangular cross sections of different thickness. The interest was focussed on the development of the leeside flow with changes in angle of incidence and main stream Mach number. In addition to that similar delta wings with curved leading edges and also with a jump in leading edge sweep were investigated, as well as two types of wave riders. Besides some theoretical work mainly wind tunnel test were made applying available test techniques: Surface pressure measurements, Pitot measurements in the flow field, flow visualization by Schlieren, vapour and oilfilm technique, skin friction determination using oilfilm interferrogramm and, finally, laser velocimetry (laser-two-focus-system). The experimental investigations were particularly challenging, because of the small models of generally not more than 6 cm span. This limitation arose from the small size of the transonic and supersonic wind tunnel (15 x 15 cm). The paper will give a review on the activities and a brief report on some of the findings.
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1991 with total page 256 pages. Available in PDF, EPUB and Kindle. Book excerpt:
