Download or read book Wind Tunnel and Full scale Forces on Rocket Sleds written by Daniel J. Krupovage and published by . This book was released on 1967 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: Vertical quasi-steady state forces on three dual rail rocket sleds, which were predicted using wind tunnel data, are compared with those measured on the Holloman Test Track. A description of the magnitude and character of the oscillatory forces is also presented. This is the first such comparison since the advent of rocket sled testing. Wind tunnel force tests on the three rocket sleds indicated that aerodynamic forces would be of sufficient magnitude to warrant consideration in structural design. The forces measured during the track tests indicated that the aerodynamic contribution was the dominant component to the vertical quasi-steady state force in the supersonic regime. The results of full-scale investigations showed implicitly that when the sleds experienced considerable aerodynamic forces, the wind tunnel data agreed fairly well with the forces measured on the rocket sled. The quasi-steady state vertical forces were predicted, using wind tunnel data, to within 3,000 pounds for loads between 12,000 and 32,000 pounds. (Author).

Download or read book Wind Tunnel and Full scale Forces on Rocket Sleds written by and published by . This book was released on 1967 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Vertical quasi-steady state forces on three dual rail rocket sleds, which were predicted using wind tunnel data, are compared with those measured on the Holloman Test Track. A description of the magnitude and character of the oscillatory forces is also presented. This is the first such comparison since the advent of rocket sled testing. Wind tunnel force tests on the three rocket sleds indicated that aerodynamic forces would be of sufficient magnitude to warrant consideration in structural design. The forces measured during the track tests indicated that the aerodynamic contribution was the dominant component to the vertical quasi-steady state force in the supersonic regime. The results of full-scale investigations showed implicitly that when the sleds experienced considerable aerodynamic forces, the wind tunnel data agreed fairly well with the forces measured on the rocket sled. The quasi-steady state vertical forces were predicted, using wind tunnel data, to within 3,000 pounds for loads between 12,000 and 32,000 pounds. (Author).

Download or read book Static Force and Moment Tests of the Holloman Narrow gage Rocket Sled at Mach Numbers from 1 5 to 4 0 written by R. H. Rhudy and published by . This book was released on 1975 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Static Force and Moment Test of the Holloman Narrow Gage Rocket Sled at Mach Numbers from 3 5 to 5 5 written by and published by . This book was released on 1987 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: A static force and moment test was performed in the Supersonic Wind Tunnel A at Mach numbers from 3.5 to 5.5 to obtain experimental aerodynamic data on the 1/12th scale model of a Narrow-Gage Rocket Sled. The test was performed with the model in close proximity to a ground plane and rail assembly simulating the High Speed Test Track at Holloman Air Force Base. The configuration variables were the mounting of either a 4 or 16-degree wedge above the rocket motors. Final tabulation of test data results are included in this report. Keywords: Aerodynamic loading; Rocket sled scale models; Wedges; Angle of attack; Wind tunnel test; Image Analyzer Data System(IADS).

Download or read book Wind Tunnel Testing of Interactions of High Altitude Rocket Plumes with the Free Stream written by H. K. Smithson and published by . This book was released on 1971 with total page 440 pages. Available in PDF, EPUB and Kindle. Book excerpt: Interactions of model rocket plumes and the free stream at varying simulated altitudes have been investigated in an altitude simulation chamber. Free-stream variables were Mach number, gas, total temperature, and total pressure. Model rocket parameter variables were exhaust gas, area ratio, chamber total pressure and total temperature, and the orientation of the model relative to the free stream. In addition to pitot probe measurements, plume photographs and density measurements were obtained using the electron beam technique. (Author).

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1989 with total page 960 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Government wide Index to Federal Research Development Reports written by and published by . This book was released on 1967 with total page 1234 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book U S Government Research Development Reports written by and published by . This book was released on 1967 with total page 224 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind Tunnel Investigation of a Spike bluff Body Combination for a Monorail Rocket Sled M written by Rudolf Hermann and published by . This book was released on 1962 with total page 226 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of wind tunnel measurements of lift, drag and pitching moment on a circular crosssection monorail sled using a flow separation spike including the influence of ground interference are presented and discussed. Variables investigated were the spike length, spike diameter and location on a series of sled nose shapes. Mach number range was from 2 to 5. The sled configuration having the largest drag (spike retracted) and the lowest drag (spike extended) was that with a flat face sled nose and with the spike mounted on the sled axis. The spike length for minimum drag, in general, became longer at higher speeds. Sled lift was essentially unaffected by variation of the spike length. Diameter of the spike had little effect on the overall lift or drag. Unsteady flow phenomena (buzzing) were observed for some sled configurations at spike lengths on the order of 1 to 1.5 body diameters, but not at spike lengths for minimum drag. When buzzing occurred it could be reduced or eliminated by rounding the sled nose shoulder. Mounting the spike below the sled axis diminished the drag reduction characteristics of the spike, increased the incidence of buzzing, but decreased the sled lift.

Download or read book Technical Abstract Bulletin written by Defense Documentation Center (U.S.) and published by . This book was released on 1967 with total page 784 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Evaluation of Wind Tunnel Tests on Afmdc Monorail Cone and Spike nose Sled Configurations at Mach Numbers from 2 0 to 5 0 written by W. T Strike (Jr) and published by . This book was released on 1968 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: An evaluation was made of the results of wind tunnel tests on 0.4- scale models of two monorail rocket-sled configurations. The sled models consisted of a cylindrical body with forward and aft splitter wedges and slippers and with an interchangeable 15-deg cone nose and spike nose. The wind tunnel tests were conducted at Mach numbers 2, 3, 4, and 5 and over a Reynolds number range (based on the sled body diameter) from 0.22 to 1.92 million. The sled model was sting supported over a scaled replica of the Holloman track rail which was supported on a sharp-leading-edge ground plane (flat plate). The test results consist of static force measurements obtained from a six-component strain-gage balance. Also, pitot pressure flow field surveys were made over the ground plane and model rail in the region occupied by the sled model. The following model parameters were varied during the test: the location of the sled relative to the rail tip and also to the ground plane leading edge, the height of the sled body above the rail surface, the gap between the slipper and rail surface, and the sled roll angle. The results presented include an evaluation of the influence of the sled slippers, the free-stream Reynolds number, and the Mach number on the aerodynamic loading of the sled.

Download or read book Facilities and Techniques for Aerodynamic Testing at Transonic Speeds and High Reynolds Number written by North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Fluid Dynamics Panel and published by . This book was released on 1971 with total page 450 pages. Available in PDF, EPUB and Kindle. Book excerpt: In September 1968, the FDP of AGARD held a specialists' meeting in Paris on transonic aerodynamics, in recognition of the fact that the absence of adequate theoretical methods and wind-tunnels of high enough Reynolds number had already led to costly shortcomings in the transonic performance of certain combat and transport aircraft. Since projected aerospace systems, military, civil and space-oriented, would involve flight at Reynolds number of up to 100 million, the FDP undertook an examination of the requirements of NATO nations for wind tunnel facilities for testing large models at high Reynolds numbers.

Download or read book Airman written by and published by . This book was released on 1973 with total page 628 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book U S Government Research and Development Reports written by and published by . This book was released on 1970 with total page 1416 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Air Corps News Letter written by and published by . This book was released on 1956 with total page 1012 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind Tunnel Investigation of Aerodynamics of Slipper Beams as Mounted on a Typical Supersonic Rocket Sled written by Frederick Moynihan and published by . This book was released on 1962 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of wind tunnel measurements of lift, drag and pitching moment on a circular crosssection monorail sled using a flow separation spike including the influence of ground interference are presented and discussed. Variables investigated were the spike length, spike diameter and location on a series of sled nose shapes. Mach number range was from 2 to 5. The sled configuration having the largest drag (spike retracted) and the lowest drag (spike extended) was that with a flat face sled nose and with the spike mounted on the sled axis. The spike length for minimum drag, in general, became longer at higher speeds. Sled lift was essentially unaffected by variation of the spike length. Diameter of the spike had little effect on the overall lift or drag. Unsteady flow phenomena (buzzing) were observed for some sled configurations at spike lengths on the order of 1 to 1.5 body diameters, but not at spike lengths for minimum drag. When buzzing occurred it could be reduced or eliminated by rounding the sled nose shoulder. Mounting the spike below the sled axis diminished the drag reduction characteristics of the spike, increased the incidence of buzzing, but decreased the sled lift.

Download or read book Bibliography of Scientific and Industrial Reports written by and published by . This book was released on 1970-07 with total page 940 pages. Available in PDF, EPUB and Kindle. Book excerpt: