Supersonic Wind Tunnel Magnus Measurements Of The 7 8 9 And 10 Caliber Army Navy Spinner Projectile

Author : John E. Holmes,Frank J. Regan,Mary Ellen Falusi
Publisher : Unknown
Page : 68 pages
File Size : 52,8 Mb
Release : 1968
Category : Magnus effect
ISBN : UOM:39015095150374

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Supersonic Wind Tunnel Magnus Measurements of the 7-, 8-, 9- and 10-caliber Army-Navy Spinner Projectile by John E. Holmes,Frank J. Regan,Mary Ellen Falusi Pdf

The Army-Navy Spinner Projectile is a research shape that has been used as the foundation of many spin stabilized weapon designs. The purpose of the wind tunnel tests was to make supersonic wind tunnel Magnus measurements on AN Spinner configurations of 7-, 8-, 9- and 10-caliber lengths. Such an experimental study indicates the effect of length on the Magnus force and moment for a basic spin stabilized shape. (Author).

Author : Frank J. Regan
Publisher : Unknown
Page : 116 pages
File Size : 50,8 Mb
Release : 1970
Category : Aerodynamics, Supersonic
ISBN : UOM:39015095150697

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Supersonic Magnus Measurements of the 10-Caliber Army-Navy Spinner Projectile with Wrap-around Fins by Frank J. Regan Pdf

A research configuration was formed by attaching wraparound fins in a cruciform arrangement to a 10-caliber Army-Navy spinner projectile. This configuration was tested in a supersonic tunnel to get the Magnus force and moment, as well as the normal force and pitching moment. Model spin rate was generated by means of fin cant.

Author : Anonim
Publisher : Unknown
Page : 0 pages
File Size : 43,6 Mb
Release : 1968
Category : Electronic
ISBN : OCLC:227648007

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Supersonic Wind Tunnel Magnus Measurements of the 7-, 8-, 9- and 10-Caliber Army-Navy Spinner Projectile by Anonim Pdf

The Army-Navy Spinner Projectile is a research shape that has been used as the foundation of many spin stabilized weapon designs. The purpose of the wind tunnel tests was to make supersonic wind tunnel Magnus measurements on AN Spinner configurations of 7-, 8-, 9- and 10-caliber lengths. Such an experimental study indicates the effect of length on the Magnus force and moment for a basic spin stabilized shape. (Author).

Author : H. R. Vaughn,G. E. Reis
Publisher : Unknown
Page : 70 pages
File Size : 46,9 Mb
Release : 1973
Category : Body of revolution
ISBN : UOM:39015095224302

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A Magnus Theory for Bodies of Revolution by H. R. Vaughn,G. E. Reis Pdf

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 : Frank J. Regan
Publisher : Unknown
Page : 126 pages
File Size : 55,9 Mb
Release : 1972
Category : Body of revolution
ISBN : UOM:39015095152735

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The Effect of Base Bleed on the Drag and Magnus Characteristics of a Rotating Body of Revolution by Frank J. Regan Pdf

Base bleed is a technique whereby all or part of the boundary layer is 'bled' from the rear portion of a projectile to the base region. Passage from the model's surface to the base region is by means of concentric cylindrical passageways. The purpose of base bleed is to reduce the Magnus moment on overlong spinning bodies of revolution and to reduce the base drag. Both analytic and experimental results are presented. The boundary layer is represented by means of the momentum thickness.

Author : Anonim
Publisher : Unknown
Page : 992 pages
File Size : 41,9 Mb
Release : 2024-05-06
Category : Science
ISBN : CORNELL:31924057184735

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Technical Abstract Bulletin by Anonim Pdf

Author : I. D. Jacobson
Publisher : Unknown
Page : 72 pages
File Size : 55,5 Mb
Release : 1973
Category : Ballistics
ISBN : MINN:31951000526587E

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Magnus Characteristics of Arbitrary Rotating Bodies by I. D. Jacobson Pdf

The report reviews both theoretical and experimental investigations of the Magnus effect on arbitrary bodies of revolution. The main emphasis is on spinning projectiles at angle of attack, both with and without fins. Flow visualization measurements are used to assess the accuracy of the existing theories. Laminar, turbulent, and mixed boundary layers are considered. (Author).

Author : John E. Holmes
Publisher : Unknown
Page : 130 pages
File Size : 49,5 Mb
Release : 1973
Category : Guided missiles
ISBN : UOM:39015095152792

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Wrap-around-fin (WAF) Pressure Distribution by John E. Holmes Pdf

The principal difference between a wrap around fin and a planar fin is that the WAF exhibits an induced rolling moment at zero degree angle of attack, while a straight fin has none. The Naval Ordnance Laboratory, along with other members of The Technical Cooperation Program, initiated a joint investigation into the causes of the induced roll moment. Measurements of the pressure distribution over both the convex and concave sides of a WAF showed that the primary difference in pressure across the fin occurred immediately behind the leading edge with the pressure on the convex side apparently being affected more by the curvature than that on the concave side. In general, for a WAF with fixed curvature, it appeared that the physical characteristic which would have the most effect on changing the roll moment would be the fin cross-sectional profile, especially the leading-edge profile. (Author).

Author : Anonim
Publisher : Unknown
Page : 0 pages
File Size : 55,9 Mb
Release : 1970
Category : Electronic
ISBN : OCLC:227673130

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Supersonic Magnus Measurements of the 10-Caliber Army-Navy Spinner Projectile with Wrap-Around Fins by Anonim Pdf

A research configuration was formed by attaching wraparound fins in a cruciform arrangement to a 10-caliber Army-Navy spinner projectile. This configuration was tested in a supersonic tunnel to get the Magnus force and moment, as well as the normal force and pitching moment. Model spin rate was generated by means of fin cant.

Author : Anonim
Publisher : Unknown
Page : 330 pages
File Size : 41,9 Mb
Release : 1974
Category : Aerodynamics
ISBN : UCSD:31822011976735

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Collection of Technical Papers on Atmospheric Flight Mechanics by Anonim Pdf

Author : Clarence John Schueler,Linley K. Ward,A. E. Hodapp
Publisher : Unknown
Page : 242 pages
File Size : 54,5 Mb
Release : 1967
Category : Aerodynamic measurements
ISBN : UCSD:31822015409758

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Techniques for Measurement of Dynamic Stability Derivatives in Ground Test Facilities by Clarence John Schueler,Linley K. Ward,A. E. Hodapp Pdf

Some of the techniques in current use for measuring dynamic stability derivatives in wind tunnels are described, with emphasis given to the important features of balance system design, data reduction methods, instrumentation and typical balance systems. The use of gas bearings for dynamic stability and roll damping balances is treated and a three-degree-of-freedom balance system employing a spherical gas bearing is described. (Author).

Author : Charles John Nietubicz
Publisher : Unknown
Page : 0 pages
File Size : 54,9 Mb
Release : 1980
Category : Aerodynamics
ISBN : OCLC:227444741

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Supersonic Wind Tunnel Measurements of Static and Magnus Aerodynamic Coefficients for Projectile Shapes with Tangent and Secant Ogive Noses by Charles John Nietubicz Pdf

Wind tunnel tests have been conducted for a series of projectile configurations. The shapes tested include a three caliber secant ogive nose and three caliber tangent ogive nose configuration. The overall model length was fixed at 6 calibers for all configurations tested. Static and Magnus aerodynamic coefficient data were obtained at Mach numbers 2.0, 3.0 and 4.0 for angles of attack up to 10.0 deg. The data are presented in graphical form along with tabulations of the summary data. The tangent ogive nose produced a slight increase in the Magnus moment coefficient when compared to similar secant ogive configurations. The boattail configuration, when compared to the cylinder shapes, was found to increase the Magnus moment; however, this effect was shown to decrease with increasing Mach number.

Author : Anonim
Publisher : Unknown
Page : 1060 pages
File Size : 48,5 Mb
Release : 1970
Category : Aeronautics
ISBN : STANFORD:36105007163798

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International Aerospace Abstracts by Anonim Pdf

Author : Antonio Ferri
Publisher : Unknown
Page : 76 pages
File Size : 40,6 Mb
Release : 1945
Category : Aerodynamic load
ISBN : UFL:31262081032673

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Supersonic-tunnel Tests of Projectiles in Germany and Italy by Antonio Ferri Pdf

Summary: Tests were performed in the Göttingen (Germany) and Guidonia (Italy) supersonic tunnels in order to determine the aerodynamic characteristics of projectiles of various shapes. The Mach numbers ranged from about 1.3 to 3.2 for the Göttingen tests and from 1.44 to 2.66 for the Guidonia tests. The results show that increasing the relative length of the nose causes the drag coefficient to decrease and the center of pressure to move forward. For a given length, the nose having minimum drag has a curved profile; the curvature is greatest at the tip and decreases to a very small value toward the rear of the nose, where the shape becomes approximately conical. As the Mach number increases, the drag coefficient decreases and the center of pressure moves toward the tail. For the higher Mach numbers the variation of the drag coefficient and the movement of the center of pressure are small. Existing aerodynamic theory gives values of the aerodynamic characteristics close to those determined experimentally for small flow deviations.

Author : R. J. Volluz
Publisher : Unknown
Page : 512 pages
File Size : 49,8 Mb
Release : 1961
Category : Aerodynamics, Supersonic
ISBN : UOM:39015095339258

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Handbook of Supersonic Aerodynamics by R. J. Volluz Pdf