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Author : Edward J. Marquart
Publisher : Unknown
Page : 44 pages
File Size : 49,7 Mb
Release : 1982
Category : Ballistic missiles
ISBN : UOM:39015104952166
Author : Anonim
Publisher : Unknown
Page : 196 pages
File Size : 49,8 Mb
Release : 1982
Category : Science
ISBN : CORNELL:31924057185104
Author : Bob L. Uselton,Frederick B. Cyran
Publisher : Unknown
Page : 154 pages
File Size : 46,9 Mb
Release : 1980
Category : Hypersonic wind tunnels
ISBN : UOM:39015104952091
Wind tunnel tests were conducted to provide support interference information for planning and directing wind tunnel tests at supersonic and hypersonic Mach numbers. Sting-length and sting-diameter effects on base and surface pressures of a blunt 6-deg cone with a sliced base were investigated at Mach numbers 2, 3, 5, and 8. Dynamic stability tests on a blunt 7-deg cone were also conducted at Mach numbers 2, 5, and 8. The objectives of the 7-deg cone tests were to define critical sting lengths as determined by the measurement of dynamic stability derivatives, static pitching moment, and base pressure. Two frequencies of oscillation were investigated, and data were obtained for laminar, transitional, and turbulent boundary-layer conditions at the model base. The data from the 6- and 7-deg cone tests showed that the critical sting length depended on the interference indicator, Mach number, angle of attack, state of the model boundary layer, and frequency of oscillation. The critical sting length was generally less for models with turbulent boundary layers than for those with laminar boundary layers. A critical sting length of 2.5 model diameters was determined to be suitable for all test conditions that produced a turbulent boundary layer at or ahead of the model base.
Author : Frederick B. Cyran,Bob L. Uselton,Edward J. Marquart
Publisher : Unknown
Page : 58 pages
File Size : 48,9 Mb
Release : 1981
Category : Boundary layer
ISBN : UOM:39015104951804
Wind tunnel tests were conducted to provide sting-support interference information for planning and directing wind tunnel tests at subsonic and transonic Mach numbers. Sting-length effects on dynamic stability derivatives, static pitching moment, and base pressure of a blunt, flat-base 7- deg cone were investigated at Mach numbers 0.2 to 1.3 in the Arnold Engineering Development Center (AEDC) Propulsion Wind Tunnel Facility (PWT). Two frequencies of oscillation, nominally 5.3 and 2.9 Hz, were investigated. The boundary-layer state at the model base was turbulent for all Mach numbers greater than 0.2. The interference effects of two types of model-wake splitter plates were also investigated. The results showed that the critical sting length depended on the Mach number, angle of attack, and type of data used as the interference indicator. A critical sting length of three model diameters was determined to be suitable for all test conditions for the ratio of sting-diameter-to-model-base- diameter (0.22) for this test.
Author : Frederick B. Cyran,J. P. Christopher
Publisher : Unknown
Page : 92 pages
File Size : 54,7 Mb
Release : 1981
Category : Aerodynamics, Transonic
ISBN : UOM:39015104952042
Wind tunnel sting support interference effects on dynamic stability derivatives, static pitching moment and base pressure of a blunt, 7-deg cone were investigated at subsonic and transonic Mach numbers. The cone was tested with sting configurations having a variable effective sting length ranging from 1 to 3.3 model base diameters, at angles of attack ranging from 0 to 30 deg. A forced-oscillation system was utilized to obtain data at a frequency of oscillation of approximately 5.3 Hz, and at an amplitude of 1 deg. The Reynolds number, based on model base diameter, was nominally 1.8 million, which produced a turbulent boundary layer over the aft portion of the model. The nature of the causes of these interference effects is discussed and analyzed with respect to sting length, type of measurement, and Mach number, with emphasis on defining critical sting length and on predicting minimal interference sting configurations for dynamic stability testing. The results showed that the critical sting length depended on the type of measurement used as the interference indicator, Mach number, and angle of attack. A critical sting length of three model diameters was determined to be suitable for all test conditions for the ratio of sting diameter-to-model base diameter (0.22) investigated. (Author).
Author : Anonim
Publisher : Unknown
Page : 24 pages
File Size : 43,5 Mb
Release : 1960
Category : Electronic
ISBN : NASA:31769000458730
Author : United States. Army Materiel Command
Publisher : Unknown
Page : 290 pages
File Size : 40,9 Mb
Release : 1966
Category : Projectiles, Aerial
ISBN : UOM:39015095328509
This handbook presents a general survey of the principal factors affecting the flight of projectiles, and describes the methods commonly used for predicting and influencing the flight performance. The coefficients which characterize the aerodynamic forces and moments of a moving body are identified, methods for determining the coefficients applicable to a projectile having a given shape and center of gravity location are described, and the coefficients of a number of projectiles and projectile shapes are given. The use of aerodynamic coefficients in predicting stability, range and accuracy is described. The effects of variations in projectile shape and center of gravity location on range, accuracy and lethality are discussed. Some material on prototype testing and the effects of round-to-round variations in production lots is presented.
Author : Anonim
Publisher : Unknown
Page : 416 pages
File Size : 50,8 Mb
Release : 1982
Category : Aerodynamics
ISBN : 9283503228
Author : B. H. Goethert
Publisher : Unknown
Page : 420 pages
File Size : 53,6 Mb
Release : 2007
Category : Science
ISBN : UVA:X030260513
Numerous aspects of transonic aerodynamics include wall interference corrections in conventional wind tunnels, subsonic flow in a variety of wind tunnels, and test results from transonic wind tunnels. 1961 edition.
Author : Jack Norman Nielsen
Publisher : AIAA (American Institute of Aeronautics & Astronautics)
Page : 450 pages
File Size : 50,8 Mb
Release : 1988-01-01
Category : Guided missiles
ISBN : 0962062901
The similarities between the airplane and the missile extend beyond their flying capabilities, and at higher operational speeds, the configuration distinctions become even less apparent. " Missile Aerodynamics," a classic now available from AIAA and Nielsen Engineering and Research, Inc., combines the best of missile and airplane aerodynamics, drawing extensively from numerous technical papers to present a rational and unified account of the principles behind missile projection. Evaluate the missile versus the airplane in a multitude of areas, from longitudinal acceleration, wing loading, roll and dynamic stability, guidance and navigation, and more. J.N. Nielsen covers every aspect of missile aerodynamics, from the classification of missiles and basic formulas to innovative aerodynamic controls. In one reliable reference, readers will find hundreds of schematics, equations, and tables with practical applications in missile design and engineering. Originally published by Nielsen Engineering and Research, Inc.
Author : Alvin Seiff
Publisher : Unknown
Page : 28 pages
File Size : 46,7 Mb
Release : 1962
Category : Aerodynamics, Hypersonic
ISBN : UIUC:30112106637439
Author : Anonim
Publisher : Unknown
Page : 360 pages
File Size : 51,7 Mb
Release : 1965
Category : Aeronautics
ISBN : MINN:31951P00397089Z
Author : United States Sentencing Commission
Publisher : Unknown
Page : 68 pages
File Size : 55,5 Mb
Release : 1988-10
Category : Sentences (Criminal procedure)
ISBN : MINN:31951D01984795V
Author : Robert A. Wasko
Publisher : Unknown
Page : 28 pages
File Size : 55,7 Mb
Release : 1961
Category : Launch vehicles (Astronautics)
ISBN : UIUC:30112106872887
Author : William David Compton,Charles D. Benson
Publisher : Courier Corporation
Page : 466 pages
File Size : 52,5 Mb
Release : 2013-05-13
Category : Science
ISBN : 9780486264349
The official record of America's first space station, this book from the NASA History Series chronicles the Skylab program from its planning during the 1960s through its 1973 launch and 1979 conclusion. Definitive accounts examine the project's achievements as well as its use of discoveries and technology developed during the Apollo program. 1983 edition.