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Author: Harold R. Vaughn Publisher: ISBN: Category : Aerodynamics, Supersonic Languages : en Pages : 40
Book Description
The surface flow angle was measured on an ogive cylinder at angles of attack and at supersonic Mach numbers. The results are compared with potential theory which is shown to be inadequate unitl modified.
Author: Harold R. Vaughn Publisher: ISBN: Category : Aerodynamics, Supersonic Languages : en Pages : 40
Book Description
The surface flow angle was measured on an ogive cylinder at angles of attack and at supersonic Mach numbers. The results are compared with potential theory which is shown to be inadequate unitl modified.
Author: D. S. Dolling Publisher: ISBN: Category : Languages : en Pages : 39
Book Description
An experimental investigation was made of flow over a tangent ogive cylinder model at small angle of attack. The model was approximately 10 calibers (50cm, 20in.) long with a 3 caliber nose. Surface pressure distributions have been measured in both the circumferential and axial directions and boundary layer pitot surveys made at four stations along with wind and lee sides of the cylinder. Over the entire angle of attack range tested, 0 through 5 deg, no boundary layer separation was observed. All the measurements were made at a nominal freestream Mach number of 3, a unit Reynolds number of 6.2 x 10 to the 7th power/m (1.6 million/in.) and with near adiabatic wall conditions. At these high Reynolds numbers, natural boundary layer transition occurred, and in all cases was observed close to the nose tip. The measurements were compared with predictions from a boundary layer based computer code developed by Sturek, et al, at the U.S. Army Ballistic Research Laboratories. Pressure distributions agree well with the predictions. The experimental and computed velocity profiles have some common trends but there exist significant discrepancies between them. In a general sense, the computed and measured profiles have fundamentally different shapes and their downstream development is not accurately modelled, particularly on the windside.
Author: H. R. Vaughn Publisher: ISBN: Category : Body of revolution Languages : en Pages : 70
Book Description
An analysis is presented for predicting Magnus force and moment coefficients for spinning ogive cylinder, cone cylinder, and conical bodies with laminar, transitional and turbulent boundary layers. The results compare favorably with experimental data.
Author: Robert P. Reklis Publisher: ISBN: Category : Languages : en Pages : 66
Book Description
Measurements of wall static pressure on the surface of bodies with both secant and tangent ogive noses and with both straight tails and boattails are reported. Data were taken at three supersonic Mach numbers (2, 3, and 4) and at six angles of attack (0, 1, 2, 4, 6, and 10 degs). Pressure data were obtained at ten longitudinal stations along the models. The models were rolled to obtain data at azimuthal positions every 10 degs about the body. Some comparisons of the data with numerical computations based on inviscid theory are given. These comparisons show good agreement at small angles of attack. (Author).
Author: William L. Oberkampf Publisher: ISBN: Category : Aerodynamics, Supersonic Languages : en Pages : 304
Book Description
This report covers an experimental investigation of the symmetric body vortex wake of a circular cylinder in supersonic flow. Flow field measurements were made in the cross-flow plane at various axial body stations for angles of attack from 10 to 25 degrees. Data were obtained for two Reynolds numbers at a freestream Mach number of 2 and for one Reynolds number at a freestream Mach number of 3. A conical pressure probe was used to measure total pressure, Mach number, and three orthogonal velocity components at a large number of grid points in each of the survey planes. The pitch and yaw angles of the probe were manipulated in the wind tunnel in order to minimize any probe interference effects on the body vortex. A new experimental technique was used which involved the interaction of a theoretical predictive technique, a computer driven probe, and real time data quality optimization. Results are presented for the distribution of total pressure, Mach number, cross-flow velocity field, and axial velocity component in the cross-flow plane. These quantities are further processed to infer the position of the primary body vortex in the cross-flow plane, local circulation distribution in the cross-flow plane, vortex core size, wake height, and total circulation in the cross-flow plane. (Author).
Author: Harold R. Vaughn
Author: Harold R. Vaughn
Author: Alain Beck
Author: D. S. Dolling
Author: Johns Hopkins University. Applied Physics Laboratory
Author: Charlie M. Jackson
Author: H. R. Vaughn
Author: Robert P. Reklis
Author: William L. Oberkampf
Author: D. Adamson
Author: