Supersonic Wind Tunnel Measurements Of Static And Magnus Aerodynamic Coefficients For Projectile Shapes With Tangent And Secant Ogive Noses

Author : Charles John Nietubicz
Publisher : Unknown
Page : 0 pages
File Size : 41,7 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 : 758 pages
File Size : 46,5 Mb
Release : 1980
Category : Aeronautics
ISBN : UIUC:30112075601275

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Scientific and Technical Aerospace Reports by Anonim Pdf

Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.

Author : William G. Reinecke
Publisher : CRC Press
Page : 2108 pages
File Size : 45,6 Mb
Release : 1999-11-10
Category : Technology & Engineering
ISBN : 1566769019

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Ballistics 18th International Symposium by William G. Reinecke Pdf

Author : Anonim
Publisher : Unknown
Page : 636 pages
File Size : 50,5 Mb
Release : 1981
Category : Aerodynamics
ISBN : PSU:000011749097

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A Collection of Technical Papers by Anonim Pdf

Author : Anonim
Publisher : Unknown
Page : 614 pages
File Size : 51,7 Mb
Release : 1997
Category : Aeronautics
ISBN : PSU:000031975902

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35th Aerospace Sciences Meeting & Exhibit by Anonim Pdf

Author : Anonim
Publisher : Unknown
Page : 1198 pages
File Size : 41,8 Mb
Release : 1980-07
Category : Science
ISBN : MINN:31951T00242635K

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Government Reports Announcements & Index by Anonim Pdf

Author : Anonim
Publisher : Unknown
Page : 1112 pages
File Size : 41,8 Mb
Release : 1980
Category : Government reports announcements & index
ISBN : MINN:30000008703351

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Government Reports Annual Index by Anonim Pdf

Author : Anonim
Publisher : Unknown
Page : 412 pages
File Size : 54,9 Mb
Release : 1991
Category : Aeronautics
ISBN : PSU:000019401713

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91-0331 - 91-0367 by Anonim Pdf

Author : Antonio Ferri
Publisher : Unknown
Page : 76 pages
File Size : 40,9 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 : Frank J. Regan
Publisher : Unknown
Page : 116 pages
File Size : 45,9 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 : R. J. Volluz
Publisher : Unknown
Page : 512 pages
File Size : 44,8 Mb
Release : 1961
Category : Aerodynamics, Supersonic
ISBN : UOM:39015095339258

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Handbook of Supersonic Aerodynamics by R. J. Volluz Pdf

Author : Frank J. Regan,Mary E. Falusi
Publisher : Unknown
Page : 178 pages
File Size : 45,7 Mb
Release : 1972
Category : Magnus effect
ISBN : UOM:39015095152768

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The Static and Agnus Aerodynamic Characteristics of the M823 Research Store Equipped with Fixed and Freely Spinning Stabilizers by Frank J. Regan,Mary E. Falusi Pdf

The report is the first in a two-part series of technical reports on the dynamics and aerodynamics of free-fall stores using freely spinning stabilizers. Presented are the results of recent wind-tunnel measurements of the normal force, pitching moment and Magnus force and moment on the M823 Research Store in transonic flow. Comparisons are made between configurations equipped with fixed and freely spinning stabilizers, with regard to sign and relative magnitude of the Magnus force and moment. A method is presented and applied whereby the Magnus force and moment are corrected for flow angularity.

Author : Rudolf Hermann
Publisher : Unknown
Page : 90 pages
File Size : 53,5 Mb
Release : 1950
Category : Wind tunnels
ISBN : UCAL:$C23187

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Diffuser Efficiency and Flow Process of Supersonic Wind Tunnels with Free Jet Test Section by Rudolf Hermann Pdf

In the wind tunnel arrangement under consideration, the air leaves the Laval nozzle as a free jet and is recaptured by the diffuser, which is of the convergent-divergent design. A theoretical analysis of the flow process through this type of supersonic wind tunnel is presented and the diffuser efficiency is calculated for the case of equilibrium between test chamber pressure and pressure in the nozzle exit, assuming one-dimensional, in viscous, steady flow. Using the basic equations of continuity, energy and momentum flux through a bounding surface, an exact solution of the problem is obtained, which is applicable up to Mach number infinite. One of the basic results is, that in the recapturing zone of the diffuser a transition occurs from supersonic to subsonic flow, which is followed by an acceleration in the convergent portion up to sonic velocity at the second throat. The transition is not a normal shock and involves a total pressure loss greater than that of a normal shock at the test section Mach number. A mathematical solution with supersonic velocity after the transition process has no physical existence. A comprehensive comparison of the analytical results with available experiments in supersonic wind tunnels up to Mach number 4.4 regarding diffuser efficiency and second throat area shows good agreement.

Author : David S. Shaw
Publisher : Unknown
Page : 46 pages
File Size : 47,9 Mb
Release : 1962
Category : Airplanes
ISBN : UIUC:30112104504912

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Wind-tunnel Investigation at Mach Numbers from 1.60 to 2.86 of the Static Aerodynamic Characteristics of a Supersonic Transport Configuration with Variable-sweep Wings Employing a Double Inboard Pivot by David S. Shaw Pdf

Author : Frankie Gale Moore
Publisher : Unknown
Page : 146 pages
File Size : 47,9 Mb
Release : 1972
Category : Aerodynamics
ISBN : UOM:39015095341866

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Body Alone Aerodynamics of Guided and Unguide Projectiles at Subsonic, Transonic and Supersonic Mach Numbers by Frankie Gale Moore Pdf

Several theoretical and empirical methods are comgined into a single computer program to predict lift, drag, and center of pressure on bodies of revolution at subsonic, transonic, and supersonic Mach numbers. The body geometries can be quite general in that pointed, spherically blunt, or truncated noses are allowed as well as discontinuities in nose shape. Particular emphasis is placed on methods which yield accuracies of ninety percent or better for most configurations but yet are computationally fast. theoretical and experimental results are presented for several projectiles and a computer program listing is included an an appendix.