Download or read book An Exact Theory of Supersonic Flow Around a Delta Wing written by L. R. Fowell and published by . This book was released on 1955 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Damping in Roll of Cruciform and Some Related Delta Wings at Supersonic Speeds written by Herbert S. Ribner and published by . This book was released on 1951 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: The damping in roll of cruciform delta wings in supersonic flow has been evaluated by means of small-disturbance (linearized) wing theory; both subsonic and supersonic component stream velocities normal to the leading edges have been considered. In addition, some known two-dimensional results for rotating multibladed laminae have been applied to obtain the loading when the number of panels is changed from four to an arbitrary number, under the restriction of low aspect ratio; the damping in roll has been determined explicitly for three panels. Finally, the damping for an inifinite number of panels has been evaluated without restriction as to aspect ratio or Mach number.

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 The Drag of a Delta Wing in Supersonic Flow written by Eugene A. Carpovich and published by . This book was released on 1949 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Calculations by a First Order Theory of Supersonic Flow Around Delta Wings written by and published by . This book was released on 1980 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Supersonic Flow Past a Delta Wing at Angles of Attack and Yaw written by R.C.F. Bartels and published by . This book was released on 1948 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Potential Theory of Unsteady Supersonic Flow written by John W. Miles and published by . This book was released on 1959-01-02 with total page 248 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Calculation of Supersonic Viscous Flow Over Delta Wings with Sharp Subsonic Leading Edges written by Y. C. Vigneron and published by . This book was released on 1978 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Uniform Second order Solution for Supersonic Flow Over Delta Wing Using Reverse flow Integral Method written by Joseph Henry Clarke and published by . This book was released on 1963 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: The problem of supersonic flow over an inclined flatplate delta wing with supersonic edges is solved to second order in incidence. This solution for surface pressure is uniform and fully analytic. The approach utilizes a reverse-flow integral method previously developed for secondorder problems. This method is augmented by a number of techniques appropriate to its framework. The simplification over standard techniques acgieved by using these reverse-flow methods is quite substantial and makes the problem tractible. Reverse-flow procedures give a volume-surface integral relation that connects the second-order forward flow over the body of interest with the linearized reverse-flow over a related body. A singular integral equation is generated from the integral relation by introducing the edge sweep of the reverse-flow wing as a free parameter. An inversion is available which gives the second-order solution on the surface of the wing. The solution is then made uniformly valid using techniques previously developed. (Author).

Download or read book Notes and Tables for Use in the Analysis of Supersonic Flow written by and published by . This book was released on 1947 with total page 594 pages. Available in PDF, EPUB and Kindle. Book excerpt: This document is a compilation of formulas, tables, and curves for use in the analysis of supersonic flow.

Download or read book Computation of Supersonic Flow over Flying Configurations written by Adriana Nastase and published by Elsevier. This book was released on 2010-07-07 with total page 425 pages. Available in PDF, EPUB and Kindle. Book excerpt: Computation of Supersonic Flow over Flying Configurations is a high-level aerospace reference book that will be useful for undergraduate and graduate students of engineering, applied mathematics and physics. The author provides solutions for three-dimensional compressible Navier-Stokes layer subsonic and supersonic flows. Computational work and experimental results show the real-world application of computational results Easy computation and visualization of inviscid and viscous aerodynamic characteristics of flying configurations Includes a fully optimized and integrated design for a proposed supersonic transport aircraft

Download or read book An Integrated Approach to the Analysis and Design of Wings and Wing body Combinations in Supersonic Flow written by Ralph L. Carmichael and published by . This book was released on 1966 with total page 18 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 The Calculation of Downwash Behind Supersonic Wings with an Application to Triangular Plan Forms written by Maxwell Alfred Heaslet and published by . This book was released on 1948 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method is developed, consistent with the assumptions of small perturbation theory, which provides a means of determining for a known load distribution, the downwash behind a wing in supersonic flow. THe analysis is based upon the use of supersonic doublets which are distributed over the plan form and wake of the wing in a manner determined from the wing loading.

Download or read book Supersonic Flow Over Low Aspect ratio Wings written by and published by . This book was released on 1911 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: An attempt has been made, by means of exp": rimental work, to consolidate and augment existing knowledge of high-speed flows over delta wings. Particular emphasis . is placed on the investigation of flows which did not confirm to the 'accepted' pattern. In Part 1 the flow regimes on a caret wing are discussed with particular emphasis placed on the occurrence of 'strong' oblique shocks. Results are presented which demonstrate that when viewed in direction normal to the leading edge, shocks of both the 'weak' and the 'strong' families can be said to exist. An experiment designed to produce a single strong shock by means of a caret wingýof large anhedral, instead gave rise to a complex multiple shock pattern which could not be adequately explained by exact inviscid theory. In Part 2 the unexpected pressure rises reported on the lee surfaces of various delta wings (References 22 and 23) are shown to be, at least in part, the result of interference from the model support and base-mounted instrumentation. The physical reason for the pressure rise is discussed. 'Correct' leeside pressure distributions are pre- sented for one of the models used in Reference 23 for angles of attack up to 50 degrees. In Part 3 the different flow regimes on delta wings are discussed together with the methods of defining the boundaries between them. The conjecture that thin shock-layer theory can be used to predict the on- set of leading-edge separation is carefully investigated by means of tunnel tests on a particular wing with triangular cross-section.

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 Linearized Theory of Conical Supersonic Flow with Application to Triangular Wings written by North American Aviation, inc and published by . This book was released on 1947 with total page 122 pages. Available in PDF, EPUB and Kindle. Book excerpt: