Download or read book Supersonic Flow Past Finite Double Wedge Wings of Variable Thickness written by Maurice Holt and published by . This book was released on 1960 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Supersonic Flow Past Finite Double Wedge Wings of Variable Thickness written by Maurice Holt and published by . This book was released on 1960 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Supersonic Flow Past Finite Double Wedge Wings of Variable Thickness written by Maurice Holt and published by . This book was released on 1960 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt: In this case the whole disturbed flow field also varies sinusoidally with span. In region (i) the pressure satisfies the telegraph equation and the problem of calculating the disturbed flow field reduces to an integro-differential-difference equation for the distorted shock shape function. The solution of this equation, the existence and uniqueness of which is established, is obtained in the form of series expansions in chordwise distance on the shock ... In region (ii) the surface pressure satisfies a Volterra integral equation which can be solved by a simple numerical procedure. The present paper takes no account of edge effects, which must be treated separately as a conefield problem.

Download or read book Supersonic Flow Past Finite Double Wedge Wings of Variable Thickness Part I Linear Variation written by Maurice Holt and published by . This book was released on 1960 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Supersonic Flow Past Finite Double Wedge Wings of Variable Thickness written by Bohyun Yim and published by . This book was released on 1960 with total page 134 pages. Available in PDF, EPUB and Kindle. Book excerpt: In this case the whole disturbed flow field also varies sinusoidally with span. In region (i) the pressure satisfies the telegraph equation and the problem of calculating the disturbed flow field reduces to an integro-differential-difference equation for the distorted shock shape function. The solution of this equation, the existence and uniqueness of which is established, is obtained in the form of series expansions in chordwise distance on the shock... In region (ii) the surface pressure satisfies a Volterra integral equation which can be solved by a simple numerical procedure. The present paper takes no account of edge effects, which must be treated separately as a conefield problem.

Download or read book AFOSR written by United States. Air Force. Office of Scientific Research and published by . This book was released on 1960 with total page 940 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Dissertation Abstracts written by and published by . This book was released on 1963-05 with total page 1756 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstracts of dissertations and monographs in microform.

Download or read book OAR Cumulative Index of Research Results written by and published by . This book was released on with total page 788 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Index to American Doctoral Dissertations written by and published by . This book was released on 1959 with total page 252 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Annual Report written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1953 with total page 534 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Report written by and published by . This book was released on 1945 with total page 620 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Report National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1952 with total page 1208 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Annual Report of the National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1954 with total page 1200 pages. Available in PDF, EPUB and Kindle. Book excerpt: Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.

Download or read book U S Government Research Reports written by and published by . This book was released on 1960 with total page 950 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Analysis Of Supersonic Flow Over Finite Width Wedges Using The Panel Method written by Poprawa Stefan Andreas Helmut and published by . This book was released on 1987 with total page 194 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book OAR Cumulative Index of Research Results written by United States. Air Force. Office of Aerospace Research and published by . This book was released on 1959 with total page 794 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book On the Calculation of Unsteady Nonlinear Three dimensional Supersonic Flow Past Wings written by Stanford University. Department of Aeronautics and Astronautics and published by . This book was released on 1968 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt: A comprehensive study is made of factors influencing the accuracy of predicted thickness effects on the flow due to oscillatory motion of a sweptback wing in supersonic flight. For a delta planform with its leading edge swept at or near the Mach angle, the streamlines and velocity pattern due to thickness are found to be highly three-dimensional. Based on this observation, improvements are suggested to previous approximate second-order theories for the unsteady loading. Numerical examples are presented for 45 degree delta wings of 5% and 10% thicknesses, which indicate a substantial difference between the linearized and nonlinear lifting potential distributions. Although a greater volume of computation is needed to guarantee adequate accuracy, practical means are described for the complete numerical solution of problems of this type. (Author).