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 Study of Lee side Flows Over Conically Cambered Delta Wings at Supersonic Speeds Part 2 written by and published by . This book was released on 1987 with total page 412 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Professional Measurements Obtained in Flight at Transonic Speeds for a Conically Cambered Delta Wing written by Earl R. Keener and published by . This book was released on 1959 with total page 76 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 412 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Preliminary Investigation at Supersonic Speeds of Triangular and Sweptback Wings written by Macon C. Ellis and published by . This book was released on 1949 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results from a supersonic wind-tunnel investigation of a series of thin triangular and sweptback wings are presented. The triangular wing series consisted of eight triangular wings of vertex angles such that a range of leading-edge postions both inside and outside the Mach cone at the test Mach numbers of 1.43 and 1.71 was obtained. The three swept wings had angles of sweep at 45, 55, and 63 degrees and were tested at a Mach number of 1.43.

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 Pressure Measurements Obtained in Flight at Transonic Speeds for a Conically Cambered Delta Wing written by Earl R. Keener and published by . This book was released on 1959 with total page 80 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 Effect of Leading and Trailing edge Flaps on Clipped Delta Wings with and Without Wing Camber at Supersonic Speeds written by Gloria Hernandez and published by . This book was released on 1994 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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 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 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 Pressure Measurements at Transonic and Low Supersonic Speeds on a Thin Conical Cambered Low aspect ratio Delta Wing in Combination with Basic and Indented Bodies written by John P. Mugler and published by . This book was released on 1957 with total page 79 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure distributions on a thin conical cambered low-aspect-ratio delta wing have been obtained in the Langley 8-foot transonic tunnel over a Mach number range from 0.60 to 1.12 and at a Mach number of 1.43. Data were obtained for the wing in combination with a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2. The angle-of-attack range was from -4 to 20 degrees in most instances.

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 66 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 Gap Effects of a Sharp Edged Delta Wing at Supersonic Speeds written by Bernard Mazelsky and published by . This book was released on 1969 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: Sonic boom measurements were conducted to evaluate the effects of a leading slat with various degrees of camber and gap size between the slat and the main wing on a 70 deg swept delta wing at supersonic speeds. The model was sized for sonic boom measurements in a wind tunnel. In addition to these measurements, the model was instrumented with several pressure taps for indicating the flow through the gap. As a separate wind tunnel entry, force measurements were also taken to indicate the effect of the cambered slat on the pitch stability and lift-drag ratio. Due to the small size of the model required to measure the sonic boom, the gap configuration was such that the airflow was normal to the wing surface. For optimum lift and drag performance, the gap should be designed such that the flow from the upper surface should be tangential to the upper surface. A second model has been constructed to evaluate the lift-drag problem separately by increasing the size of the model such that the proper gap configurations can be fabricated. Regardless of the non-optimization of the gaps, the following results were established by this phase of the program. (1) The effect of camber results in an increase in (L/D)max. (2) The effect of Reynolds Number on (L/D)max is negligible when the gap is closed. However, for a very small gap, a slight increase in (L/D)max occurs with increasing Reynolds Number. (3) For the case of zero and 11 deg camber, the reduction of overpressure due to the gap is approximately 5%. For the case of the 7 deg camber, no reduction was apparent. (Author).

Download or read book A Wing Concept for Supersonic Maneuvering written by William Henry Mason and published by . This book was released on 1983 with total page 88 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 1994 with total page 892 pages. Available in PDF, EPUB and Kindle. Book excerpt: