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Author : Brad M Epstein
Publisher : Unknown
Page : 128 pages
File Size : 53,9 Mb
Release : 2024-06-30
Category : Electronic
ISBN : 1607300702
Author : Anonim
Publisher : Unknown
Page : 548 pages
File Size : 53,6 Mb
Release : 1970
Category : Education, Higher
ISBN : WISC:89109745364
Author : Anonim
Publisher : Unknown
Page : 690 pages
File Size : 52,9 Mb
Release : 1894
Category : American periodicals
ISBN : NYPL:33433100957707
Author : Anonim
Publisher : Unknown
Page : 686 pages
File Size : 49,9 Mb
Release : 1894
Category : Electronic
ISBN : BSB:BSB11520277
Author : National Center for Education Statistics
Publisher : Unknown
Page : 324 pages
File Size : 48,5 Mb
Release : 2024-06-30
Category : Electronic
ISBN : UOM:39015013979557
Lists institutions in the United States and its outlying areas that offer at least a 2-year program of college-level studies in residence or, if nonresident in nature, that are accredited or pre-accredited by an accrediting agency recognized for such purpose by the U.S. Commissioner of Education.
Author : Alfred Merle Morrison,Solomon, J. M.,Ciment, M.,Ferguson, R. E.
Publisher : Unknown
Page : 260 pages
File Size : 46,7 Mb
Release : 1975
Category : Aerodynamic load
ISBN : UOM:39015095246990
This report contains numerical tables of aerodynamic coefficients and surface pressure distributions for sphere cone configurations as a function of angle of attack and Mach number. These results were generated by an NSWC/WOL computer code based on a finite difference solution of the steady inviscide three-dimensional compressible flow equation for a perfect gas [upsilon]= 1.4. Cone half angles of 50, 60, 80, 90, 100, 150 and 200 are considered. Truncated values are obtained at axial stations to a length of 200 times the sphere radius, over a Mach number range of 3.5, 5, 10, 20, 25 and 30, for an angle-of-attack span of 10, 30, 50, and 100. Center-of-pressure location, and axial- and normal-force coefficients are tabularly presented at each axial-length increment station. Surface pressure distributions are also presented at each axial-length increment station, including seven meridian plane angles over the half plane from windward to leeward ray. The techniques utilized in generating the tables are described, and comparisons between computed values and values measured in some wind-tunnel experiments are presented. The presentation format is discussed to establish the mechanics necessary to use the tables. The tables are divided into two volumes; the first containing pressure information, and the second, aerodynamic information.
Author : Wardlaw, Jr. (Andrew B.),Alfred Merle Morrison
Publisher : Unknown
Page : 52 pages
File Size : 43,6 Mb
Release : 1975
Category : Aerodynamic load
ISBN : UOM:39015095247162
Linear regression techniques are used to establish a quantitative description of side forces on bodies at high incidence. A data base is assembled concerning the key side force characteristics of maximum observed side force, angle of occurrence, and minimum angle of attack at which a side force is observed. This information is examined to determine the important trends and a predictive model for side force based on the crossflow analogy is developed to suggest other important variables. A linear regression model for these quantities is developed to include only those variables which are statistically significant. Results indicate that peak side force coefficients are a function of Mach number and only weakly of Reynolds number. Nose fineness is the critical model dimension which suggests that peak side force is a product of the nose flow field. The angle at which peak side forces occur is found to be dependent on model length and Mach number, while the onset angle of attack is a function of model length only.
Author : R. E. Phinney,F. P. Baltakis
Publisher : Unknown
Page : 36 pages
File Size : 40,8 Mb
Release : 1973
Category : Heat
ISBN : UOM:39015095247089
In order to assess the direct influence of surface roughtness upon heat transfer andits indirect effect through the shift in transition location, a series of wind tunnel tests were carried out. A fixed body shape (with one exception) with varying roughness was tested at a series of tunnel conditions and the heat transfer measured by the thin wall calorimenter method. The wind tunnel conditions and the heat transfer distribution around the models are presented in tabular form.
Author : Arnold Polak
Publisher : Unknown
Page : 38 pages
File Size : 44,7 Mb
Release : 1974
Category : Aerodynamic heating
ISBN : UOM:39015095246941
The report presents a numerical study of attached interacting supersonic turbulent boundary layers over a two-dimensional protuberance. Results are presented in terms of surface pressure, heat transfer and skin-friction distributions. These results indicate a strong effect of the size of the protuberance, Mach number, but a weak effect of Reynolds number and the ratio of wall-to-recovery temperature. The peak heating rates from a set of test cases compare well to a semi-empirical prediction method. In contradistinction to the laminar case, the turbulent recovery zone downstream of the protuberance is very short. (Author).
Author : Andrew B. Wardlaw (Jr.),W. J. Glowacki
Publisher : Unknown
Page : 100 pages
File Size : 52,6 Mb
Release : 1973
Category : Angle of attack (Aerodynamics)
ISBN : UOM:39015095152867
A method initially proposed by Bryson is extended to include asymmetric shedding. This method employs the impulsive flow analogy, and models each wake vortex using a single-point vortex. Free parameters inherent in the problem formulation are determined empirically. Normal force, pitching moment and yawing force coefficients are predicted for slender bodies with a nose fineness ratio greater than four and at a Mach number less than 0.9. (Modified author abstract).
Author : National Center for Educational Statistics
Publisher : Unknown
Page : 32 pages
File Size : 40,5 Mb
Release : 1965
Category : Degrees, Academic
ISBN : UOM:39015027652943
Author : American Society for Horticultural Science. North Central Region
Publisher : Unknown
Page : 46 pages
File Size : 47,7 Mb
Release : 1982
Category : Horticulture
ISBN : WISC:89031405178
Author : Robert H. Feldhuhn,Allen Edward Winkelmann
Publisher : Unknown
Page : 82 pages
File Size : 54,5 Mb
Release : 1969
Category : Cone
ISBN : UOM:39015095150424
An experimental investigation illustrating some separated flow phenomena associated with highly inclined circular cones was conducted at a nominal Mach number of 5 and at nominal free stream Reynolds numbers per foot of 4,800,000. Surface static pressure measurements, Pitot pressure surveys, schlieren photographs, vapor screen photographs, and surface sublimation measurements were obtained on a sharp 5 degree semi-vertex angle cone at angles of attack up to 40 degrees. The static pressure distribution along the most leeward meridian generator was found to be dependent upon the Reynolds number based upon the distance from the vertex of the cone. The vapor screen photographs at 40 degrees angle of attack indicate the existence of imbedded shock waves in the flow field on the leeward side of the cone. The Pitot tube surveys and the surface sublimation photographs indicate the existence of a region of attached flow near the leeward meridian plane. The surface sublimation photographs also indicate the possible existence of a secondary vortex. (Author).
Author : Arnold Polak
Publisher : Unknown
Page : 58 pages
File Size : 55,9 Mb
Release : 1971
Category : Boundary layer control
ISBN : UOM:39015095150838
The report presents an analysis predicting separation of a turbulent boundary layer over a cone-flare configuration with gas injected into the boundary layer ahead of separation point. Separation location and separation lengths are compared with experimental data obtained at Mach number of 6 and a range of Reynolds numbers. At the highest Reynolds numbers the extent of separation decreases with increasing Reynolds number. When compared to separation over cylinder-flare body it is found that the extent of separation is lower for the cone-flare configuration. (Author).
Author : James R. Bruno,Donald B. Risher
Publisher : Unknown
Page : 46 pages
File Size : 50,9 Mb
Release : 1968
Category : Ablation (Aerothermodynamics)
ISBN : UOM:39015095150366
This report describes a skin-friction balance that is presently being used to measure shear stresses acting on the wall of an ablative duct. Tests have been conducted in the 3 Megawatt Arc Tunnel with a Mach number of 3, a stagnation enthalpy of 3000 BTU/lb, and a stagnation pressure of 20 atmospheres. The balance is a direct deflection measuring device in that balance arm rotation is measured with a linear variable differential transformer as the balance arm deflects due to shear loads acting on the end of the balance arm. (Author).
