| Capabilities for Magnus Prediction in Subsonic and Transonic Flight |
Dec-2008 |
9 pages |
| Authors:
J DeSpirito; S I Silton; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD
|
 | The Magnus characteristics of three spin-stabilized projectiles were characterized using steady-state RANS and time-accurate RANS/LES computational fluid dynamic simulations. RANS/LES simulations improved the Magnus moment prediction for projectiles with rounded or chamfered bases. No difference was found between the RANS and RANS/LES simulations for the projectile with a sharp-cornered base?either with or without a boattail. The near-body flow field was similar for RANS and RANS/LES simulations; but the RANS/LES simulations ... |
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| Effect of Rifling Grooves on the Performance of Small-Caliber Ammunition |
Dec-2008 |
9 pages |
| Authors:
Paul Weinacht; Sidra I Silton; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| A combined experimental and computational investigation was performed to examine the effect of rifling grooves on the aerodynamics of projectiles and determine whether the aerodynamics associated with the rifling grooves are a potential mechanism for in-flight trim angles. The experimental program consisted of spark-range firings of bullets from the standard twist barrel spanning the range of velocities typically encountered in flight. Additionally, sabot-launched smooth and pre-engraved bullets were fired from ... |
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| Navier-Stokes Predictions of Dynamic Stability Derivatives: Evaluation of Steady-State Methods |
Sep-2008 |
44 pages |
| Authors:
James DeSpirito; Sidra I Silton; Paul Weinacht; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD WEAPONS AND MATERIALS RESEARCH DIRECTORATE
|
| The prediction of the dynamic stability derivatives-roll-damping, Magnus, and pitch-damping moments-were evaluated for three spin-stabilized projectiles using steady-state computational fluid dynamic (CFD) calculations. Roll-damping CFD predictions were found to be very good across the Mach number range investigated. Magnus moment predictions were very good in the supersonic flight regime; however, the accuracy varied in the subsonic and transonic flight regime. The best Magnus moment prediction in the subsonic flight regime ... |
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| CFD Computation of Magnus Moment and Roll Damping Moment of a Spinning Projectile |
SEP 2006 |
24 pages |
| Authors:
James DeSpirito; Karen R. Heavey; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD WEAPONS AND MATERIALS RESEARCH DIRECTORATE
|
| Computational fluid dynamic simulations (CFD) were used to predict the aerodynamic coefficients and flow field over a spinstabilized, 25-mm, sub-caliber training projectile. The primary objective of the investigation was to determine the CFD parameters necessary for the accurate prediction of the Magnus moment and roll damping of a spin-stabilized projectile. Archival experimental data was used to validate the numerical calculations. The Mach number range investigated was from 0.4 to 4.5. ... |
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| Base Pressure Computations of the DERA Generic Missile Wind Tunnel Model |
SEP 2005 |
29 pages |
| Authors:
James DeSpirito; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD WEAPONS AND MATERIALS RESEARCH DIRECTORATE
|
| Computational fluid dynamic simulations were used to compute the aerodynamic coefficients of a body-alone missile and a planar fin missile in the presence of a wind tunnel sting. The investigation was an extension to a previous investigation in which the computed forebody axial force did not compare well with experimental wind tunnel data, while all other forces and moments showed excellent agreement. The current investigation showed that the computed results ... |
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| Aero-Elastic Motion of a Spin-Stabilized Projectile |
MAR 2005 |
40 pages |
| Authors:
Charles H. Murphy; William H. Mermagen Sr; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| The elastic flight motion of a slowly spinning finned missile has been successfully described by the finite element method (FEM). With the addition of a Magnus force distribution function, this analysis was used to describe the elastic flight motion of a spin-stabilized projectile. Transient frequencies and damping rates for a 10-cal. cone cylinder have been calculated. The elastic frequencies for a rapidly spinning projectile can be substantially different from those ... |
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| New Numerical Integrators Based on Solvability and Splitting |
03 JAN 2005 |
|
| Authors:
Fernando Casas; UNIVERSIDAD JAUME I CASTELLON (SPAIN) DEPARTAMENTO DE INGENIERIA Y CIENCIA DE LOS COMPUTADORES
|
 | Outline of the Talk: 1. Some (well known) Lie group methods for linear problems (Fer and Magnus expansions); 2. Schemes based on triangular matrices (splitting + solvability); 3. Some methods and practical issues in their construction. |
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| Investigation of Combined Low-Angled Jets and Variable Wall Geometry for Hypersonic Aerodynamic Control |
05 MAY 2004 |
84 pages |
| Authors:
Rodney D. Bowersox; Charles L. Karr; Muhammad Sharif; ALABAMA UNIV TUSCALOOSA DEPT OF AEROSPACE ENGINEERING AND MECHANICS
|
| The principal objective of the present research proposal was to investigate, experimentally and numerically, the use of jets to actively control the aerodynamic forces for high-speed flight vehicles. As a test bed, single port injection into a Mach 5.0 crossflow through diamond and circular orifices, at various incidence angles and momentum ratios were examined. To meet the objective, a research program was performed to characterize and control the secondary flow ... |
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| Experimental Investigation of Transverse Supersonic Gaseous Injection Enhancement Into Supersonic Flow |
DEC 96 |
159 pages |
| Authors:
Mark P. Wilson; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH
|
| In pursuit of more efficient and effective fuel-air mixing for a SCRAMJET combustor, this study was conducted to investigate relative near field enhancements of penetration and mixing of a discrete low-angled (25 deg) injected air jet into a supersonic (M=2.9) cross flow. The enhancements were achieved by injecting the transverse air jet parallel to the compression face of eight different ramp geometries. The jet-ramp interactions created collinear shock structures, baroclinic ... |
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| Directed Energy Effects on the Flight Path of a Spinning Ballistic Projectile |
JUN 95 |
95 pages |
| Authors:
George S. Capen; NAVAL POSTGRADUATE SCHOOL MONTEREY CA
|
| This thesis will examine the equations of motion for a spinning ballistic projectile. The goal of such an examination is to determine the possible mechanisms by which a directed energy weapon may induce sufficient instability as to significantly alter the projectile's flight path. A ballistic projectile is generally launched with a "fire and forget" philosophy. The desired impact point is determined before firing. It may be possible to alter the ... |
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| Experimental Investigation of the Aerodynamics of Independently Rotating Cylindrical Shells |
DEC 92 |
91 pages |
| Authors:
Walter C. Howerton; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
|
| The purpose of this thesis was to investigate experimentally the aerodynamic forces on two adjacent, independently rotating cylinders in a cross- flow. This investigation involved a force measurement setup which had the two cylinders mounted on a common support shaft, extending beyond the span of the wind tunnel test section, and supported by spoke rings with strain gages in the vertical and horizontal directions. This setup proved capable of measuring ... |
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| Transonic Navier-Stokes Computations for a Spinning Body of Revolution |
SEP 91 |
43 pages |
| Authors:
Jubaraj Sahu; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| A zonal, implicit, time-marching Navier-Stokes computational technique has been used to compute three dimensional transonic flow fields over a projectile. Flow field computations have been performed at M = 0.94 for spin rates of 0 and 4900 rpm and at angles of attack, alpha = 0,4, and 10 degrees. All the computations have been performed on the Cray-2 supercomputer. Details of the flow field such as Mach number contours and ... |
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| Aerodynamic Coefficients of the M483A1 Determined from Spark Range Tests |
APR 91 |
43 pages |
| Authors:
Robert H. Whyte; ARROW TECH ASSOCIATES SOUTH BURLINGTON VT
|
| The aerodynamic coefficients of the M483A1 have been refined based on analysis of 65 BRL Transonic Range tests. Both the original M483A1 tests (1975) and the latest tests from 1987-1989 were analyzed utilizing a six degree-of- freedom technique during September-October 1990. The Magnus moment was found to be extremely nonlinear with angle of attack and Mach number. The size of the slow arm limit cycle was computed along the region ... |
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| The Aerodynamic Characteristics of .50 Ball, M33, API, M8, and APIT, M20 Ammunition |
JAN 90 |
79 pages |
| Authors:
Robert L. McCoy; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| The caliber .50 Ball, M33, API, M8, and APIT, M20 munitions were recently fired in the BRL spark photography ranges, to determine the complete aeroballistic characteristics required for a fire control study. Aerodynamic drag, gyroscopic stability, dynamic stability and yaw damping rates were determined at supersonic, transonic and subsonic speeds. The observed non-linear behavior of the Magnus moment coefficient predicts a slow arm limit cycle yaw at transonic and subsonic ... |
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| Nonaxisymmetric Body, Supersonic, Inviscid Dynamic Derivative Prediction |
JUN 89 |
46 pages |
| Authors:
Leroy Devan; NAVAL SURFACE WARFARE CENTER DAHLGREN VA
|
| A supersonic, aerodynamic computational model, which is the basis of the NANC code, has been extended to compute dynamic derivatives. The extension is to the inviscid contribution of constant angular rates and axial accelerations. The body geometry limitations are the same as for the steady- state model. Here, a pointed body or equivalent pointed body is assumed for low Mach numbers; at higher Mach numbers, the effect of axial acceleration ... |
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| Study of Three Dimensional Transonic Flow Separations |
APR 88 |
|
| Authors:
F. K. Owen; G. M. Orngard; T. K. McDevitt; T. A. Ambur; AMF INC WHITE PLAINS NY*
|
| An extensive wind tunnel study of flows with transonic swept separation zones and shock-boundary layer interactions on realistic stationary and spinning projectile test models was conducted in the NASA Ames 6- by- 6-ft. supersonic wind tunnel. These studies provide a detailed data base to assess the potential effects of symmetric and asymmetric three-dimensional transonic flow separations on projectile performance. A three-component laser velocimeter system, laser vapor screen, model balance and ... |
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| Aerodynamic Coefficient Predictions for a Projectile Configuration at Transonic Speeds |
DEC 87 |
34 pages |
| Authors:
Charles J. Nietubicz; Jubaraj Sahu; Robert Lafarge; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| This report describes a computational study applied to a M549 projectile configuration. The objective was to apply previously developed Navier-Stokes computational techniques to the M549 shape, compare the results with available experimental data and evaluate the current computational capability. All computations and comparisons are for the transonic flight regime. The projectile flow fields, including the recirculatory base flow regions, were computed using thin-layer Navier-Stokes codes. Increased grid resolution and reduced ... |
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| PNS (Parabolized Navier-Stokes) for Spinning Shell at Moderate Angles of Attack and for Long L/D Finned Projectiles |
JUN 86 |
|
| Authors:
Paul Weinacht; Bernard J. Guidos; Walter B. Sturek; Betty A. Hodes; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| The thin-layer Parabolized Navier Stokes (PNS) computational technique is applied to calculate the three-dimensional viscous flow about two types of projectiles: (1) a standard shell configuration at moderate angle of attack with a region of lee side crossflow separation and (2) long L/D finned projectiles. Results for the shell configuration are obtained using the algebraic turbulence model for Baldwin and Lomax with and without modifications that more properly account for ... |
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| Numerical Investigation of the Aerodynamics and Stability of a Flared Afterbody for Axisymmetric Projectiles at Supersonic Speeds |
DEC 1983 |
56 pages |
| Authors:
M. J. Nuscua; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| A parametric study has been conducted for eight similar axisymmetric, spin stabilized projectile shapes. The aerodynamic and stability parameters of flared projectile afterbodies at freestream Mach numbers of 2,3 and 4 and at an angle of attack of 2 deg have been determined. The projectiles under investigation has an ogive nose, a cylindrical midsection and one of three afterbodies: an extended cylinder, a boattail (conical frustum), and a boattail- flare ... |
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| Streamwise Vorticity Decay Downstream of a Three-Dimensional Protuberance |
OCT 1981 |
|
| Authors:
C. W. Kitchens Jr.; N. Gerber; R. Sedney; J. M. Bartos; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| Streamwise vortices generated in bounary layers are known to persist for hundreds of boundary-layer thicknesses. This remarkable property is the main topic of this report. The particular case of the flow field generated by a three-dimensional protuberance immersed in a flat plate boundary layer is studied using numerical modeling. Experimental measurements in a downstream crossflow plane are used to construct initial data for a marching calculation using the boundary-layer and ... |
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| Computational Parametric Study of the Aerodynamics of Spinning Slender Bodies at supersonic Speeds |
AUG 1981 |
|
| Authors:
Walter B. Sturek; Donald C. Mylin; Clarence C. Bush; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| Three dimensional finite-difference flow field computation techniques have been employed to generate a parametric aerodynamic study at supersonic speeds. Computations for viscous turbulent and inviscid flow have been performed for cone-cylinder, secant-ogive-cylinder, and tangent-ogive-cylinder bodies for a Mach number range of 1.75 < or = M < or = 5. The aerodynamic coefficients computed are pitching moment, normal force, center of pressure, Magnus moment, Magnus force, Magnus center of pressure, ... |
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| Aerodynamic Design Manual for Tactical Weapons |
JUL 1981 |
179 pages |
| Authors:
Lawrence A. Mason; Leroy Devan; Frank G. Moore; Donald McMillan; NAVAL SURFACE WEAPONS CENTER DAHLGREN VA
|
| The Naval Surface Weapons Center Aeroprediction Code has been extensively applied to the prediction of static and dynamic aerodynamics of missile configurations. Major extensions have recently been made to the Code, extending its capability to 0 less than or equal to M (infinity) less than or equal to 8 and 0 degrees less than or equal to alpha less than or equal to 180 degrees and improving the transonic and ... |
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| Computation of Hypersonic Laminar Viscous Flow over a Body with Mass Transfer and/or Spin at Angle of Attack |
14 MAY 1981 |
|
| Authors:
M. D. Kim; C. H. Lewis; VIRGINIA POLYTECHNIC INST AND STATE UNIV BLACKSBURG DEPT OF AEROSPACE AND OCEAN ENGINEERING
|
| Computational results of hypersonic laminar viscous flow over blunt- nosed bodies with mass transfer and/or spin are presented. An implicit-iterative numerical scheme at each marching step is used to solve the parabolized Navier- Stokes equations. The code takes into account the mass-transfer and spin effects in the boundary condition at the body surface and the periodic effect in the boundary condition around the body. To facilitate convergence, the v-momentum equation ... |
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| Trajectory Simulation Input Data for the 20mm, M56A3 Projectile Fired from a Helicopter |
MAY 1981 |
|
| Authors:
Joseph W. Kochenderfer; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| Aerodynamic and trajectory simulation input data for the 20mm, M56A3 projectile suitable for use in six degree of freedom and modified point mass models are presented. Comparison is made between models, and the added complexity introduced by firing from a helicopter is discussed. Limitations on use of the ballistic parameters to various flight conditions are outlined. (Author) |
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| An Experimental Investigation of TIP Bluntness Effects on the Turbulent Compressible Boundary Layer on an Axisymmetric Body |
MAY 1981 |
|
| Authors:
William K. Gray; David S. Dolling; Seymour M. Bogdonoff; PRINCETON UNIV NJ DEPT OF MECHANICAL AND AEROSPACE ENGINEERING
|
| An experimental study has been carried out in which the effect of tip bluntness on the turbulent boundary layer over an axisymmetric body was examined. It was performed at a Mach number of 2.94 with a unit Reynolds number of roughly 6.34 x 10 to the 7th power per meter and a nearly adiabatic wall condition. A tangent ogive-cylinder was used with a noise fineness ratio of approximately 3. Six ... |
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| Free Flight Range Tests of the Copperhead Projectile |
MAR 1981 |
67 pages |
| Authors:
Robert L. McCoy; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| Free flight spark range tests of the Copperhead projectile were conducted in the BRL Transonic Range, to obtain free flight aerodynamic data for the full-scale, tactical configuration. The free flight data show good general agreement with previously obtained wind tunnel results. The tactical Copperhead projectile is statically stable at all Mach numbers tested. A weak slow-arm dynamic instability was observed at transonic and high subsonic speeds, for small angles of ... |
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| Computational Parametric Study of the Aerodynamics of Spinning Slender Bodies at Supersonic Speeds, |
JUN 1980 |
|
| Authors:
Walter B. Sturek; Donald C. Mylin; Clarence C. Bush; BALLISTIC RESEARCH LABS ABERDEEN PROVING GROUND MD
|
| Recent trends in projectile design have led to shapes with greater length and more slender ogives. Unexpected flight stability problems have been encountered due to decreased aerodynamic stability of these new shapes. Clearly, conventional aerodynamic predictive capabilities were not adequate. In an effort to avoid these problems in the future, the Ballistic Research Laboratory has been developing advanced numerical computational techniques for computing projectile aerodynamic characteristics to improve shell design ... |
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| A Comparison of Navier-Stokes Computations with Experimental Data for a Projectile Shape at Transonic Velocities, |
JUN 1980 |
|
| Authors:
Charles J. Nietubicz; Lyle D. Kayser; BALLISTIC RESEARCH LABS ABERDEEN PROVING GROUND MD
|
| A concentrated theoretical and experimental research program has been ongoing at BRL in order to develop the predictive capabilities required for determining projectile aerodynamics. Supersonic computations using combined inviscid flow field and boundary layer techniques have been developed for cone-cylinder and ogive-cylinder configurations. Recent results have been obtained in supersonic flow over a typical boattailed projectile using modern computational techniques for solving the thinlayer Navier-Stokes equations. |
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| Symmetric Missile Dynamic Instabilities - A Review |
MAR 1980 |
42 pages |
| Authors:
Charles H. Murphy; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| Dynamic instabilities observed for symmetric missiles and projectiles arise from a large variety of causes. These include unstable linear damping moments, and different nonlinear in-plane and out-of-plane damping moments for non spinning re-entry vehicles, nonlinear Magnus moments for spinning missiles, and internal resonance with moving payload components. If aerodynamic trim is present, linear spin-yaw resonance can occur as well as nonlinear subharmonic motions and a number of other limit motions. ... |
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| Computation of Three-Dimensional Aerodynamic Flow. |
JAN 1980 |
|
| Authors:
K. C. Wang; MARTIN MARIETTA LABS BALTIMORE MD
|
| The present contract continues an earlier one which extended from 1970-1976, F44620-70-C-0085. The purpose of this continued action was to make pioneering calculations of genuine three-dimensional laminar boundary layers. During the current contract period, efforts were first focused on investigations of: (1) the general characteristics of three-dimensional flow separation, especially for aerospace applications and (2) the boundary layer features and the magnus forces on spinning bodies such as spinning projectiles ... |
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| Boundary Layer and Side Force Characteristics of a Spinning Axisymmetric Body, |
1980 |
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| Authors:
J. T. Kegelman; R. C. Nelson; T. J. Mueller; NOTRE DAME UNIV IND
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| Magnus Effect on Spinning Bodies of Revolution. |
MAY 1979 |
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| Authors:
D. S. Joshi; I. D. Jacobson; J. B. Morton; P. A. Torpey; VIRGINIA UNIV CHARLOTTESVILLE DEPT OF MECHANICAL AND AEROSPACE ENGINEERING
|
| A numerical finite difference method is developed to solve the three dimensional laminar/turbulent boundary layer equations on a spinning body of revolution at an angle of attack in supersonic flow. Influence of asymmetric transition and the presence of mixed boundary layers is considered to predict Magnus forces and moments. Several contributions to the Magnus effects are considered. These include asymmetric boundary layer displacement thickness, centrifugal pressure, and primary and cross ... |
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| Aerodynamic Analysis of the Rifleman's Assault Weapon. |
MAR 1979 |
173 pages |
| Authors:
Jimmie N. Derrick; ARMY MISSILE RESEARCH AND DEVELOPMENT COMMAND REDSTONE ARSENAL AL TECHNOLOGY LAB
|
| A wind tunnel test was conducted for seven different shell configurations. The basic configuration was a spherical shell with modification to the base section. A spherical aft shell, a truncated aft shell, and various artifical boundary layer trip devices on the base section was used. The test was conducted for Mach numbers up to 0.3 to determine the aerodynamic forces at angles-of-attack from -2 to 15 deg and various spin ... |
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| Verification Test of the AEDC High Alpha Roll Dynamics System |
NOV 1978 |
36 pages |
| Authors:
J. A. Collins; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN
|
| A test was conducted to evaluate the new AEDC High Alpha Roll Dynamics System for large models and obtain scaling parameter information. Data were obtained at Mach numbers 0.22 thru 1.15 for a Reynolds number per ft range of 690,000 through 2,500,000, at angles of attack -5 to 25 deg, and spin rates up to approximately ten thousand RPM. The model configurations (L/D of 10, D = 4.5 in.) included ... |
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| Turbulent Boundary Layer Measurements on the Boattail Section of a Yawed, Spinning Projectile Shape at Mach 3.0. |
NOV 1978 |
|
| Authors:
Lyle D. Kayser; Walter B. Sturek; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| Total pressure measurements were obtained in the turbulent boundary layer of a spinning body of revolution in support of the BRL Magnus Research Program. Data were obtained on the boattail section of a slender projectile shape at a Mach number of 3.0 and angles of attack up to 6.3 degrees. This report presents a tabulation of the boundary layer profile characteristics in a format that facilitates comparison with theoretical computations. ... |
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| Autorotation of Plates. |
AUG 1978 |
|
| Authors:
Hans J. Lugt; DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD
|
| The autorotation of plates normal to a uniform parallel flow is explained in detail for low Reynolds numbers by means of numerical solutions of the Navier-Stokes equations. The incompressible fluid flow is assumed to be laminar and two-dimensional. Comparisons are made with high Reynolds number and three-dimensional flows. The article defines autorotation, gives an historical account of investigations into autorotation, and shows that autorotation is caused by a complicated interplay ... |
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| Dynamic Force Measurements and Boundary-Layer Transition Mapping on a Spinning 9-Deg Cone with and without Mass Addition at Mach Numbers 5 and 8 |
AUG 1978 |
107 pages |
| Authors:
T. D. Buchanan; L. M. Jenke; M. J. Chaney; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN
|
| A wind tunnel test program was conducted to determine the effect of spin on the aerodynamic forces and moments and the shape and movement of the boundary-layer transition zone on 9-deg (half-angle) cone configurations. The effects of nose geometry, mass addition, angle of attack, Mach number, and Reynolds number were investigated at various spin rates. Results were obtained using a spin mechanism (1-DOF) developed for this test and a three ... |
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| Aeroballistics of Corkscrew Projectiles |
JUN 1978 |
12 pages |
| Authors:
Anders S. Platou; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| During the development and exploitation of the BRL Non-Conical Boattail Projectile, it became evident that a new projectile shape which combines a triangular nose with a triangular boattail would have low drag and a long wheel base for low balloting in the gun barrel. No aerodynamic data were available on the configuration (nicknamed the corkscrew) at the beginning of this program, so it was deemed advisable to conduct wind tunnel ... |
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| Aeroballistics of Corkscrew Projectiles. |
APR 1978 |
|
| Authors:
Anders S. Platou; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| Preliminary wind tunnel and aeroballistic range tests on a new and novel exterior projectile shape have shown that this 5-caliber to 8-caliber long shape has extremely good aerodynamic characteristics. It not only has very low drag, but also low pitching and Magnus moments which in turn yield good gyroscopic and good dynamic stability. Extrapolation of the data to longer lengths indicates that 10-caliber to 12-caliber long projectiles having this shape ... |
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| Theoretical and Experimental Methods in the Solution of Missile Nonlinear Roll Problems, |
MAR 1978 |
56 pages |
| Authors:
Peter Daniels; Samuel R. Hardy; NAVAL SURFACE WEAPONS CENTER DAHLGREN LAB VA
|
| This report is a comprehensive documentation of recently developed experimental and theoretical methods dealing with the solution of free flight missile nonlinear roll problems. A unified approach to the development of a nonlinear rolling motion theory for finned missiles as well as a passive roll rate stabilization technique are described. (Author) |
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| Experimental Measurements in the Turbulent Boundary Layer of a Yawed, Spinning Ogive-Cylinder Body of Revolution at Mach 3.0. Part I. Description of the Experiment and Data Analysis. |
JAN 1978 |
|
| Authors:
Lyle D. Kayser; Walter B. Sturek; ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| Many projectiles used by the Army are slender, spin stabilized bodies of revolution. The distorted boundary layer, which results from a spinning body at angle of yaw, generates Magnus forces and moments. The BRL is conducting and supporting theoretical and experimental magnus research efforts. Experimental results of surveys of the turbulent boundary layer on a secant-ogive-cylinder at angles of attack up to 6 degrees for spin rates of 0 and ... |
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| Increasing the Force Limits of the Magnetic Balance System. |
NOV 1977 |
|
| Authors:
Eugene E. Covert; Charles W. Haldeman; Benjamin Ziph; MASSACHUSETTS INST OF TECH CAMBRIDGE AEROPHYSICS LAB
|
| The report describes the construction and testing of new motor generator power supplies and filter inductors for use with the magnetic balance system. Motor generator output is + or - 380 volts with a current limit of + or - 300 amps and a power limit of 50 hp. Connected to the lift and drag circuits the supplies were tested up to 144 amperes in drag and 244 amperes in ... |
|
| Autorotor Launching System. |
11 OCT 1977 |
|
| Authors:
Abraham Flatau; DEPARTMENT OF THE ARMY WASHINGTON DC
|
| Described is an airborne launcher and method of delivering a munition system comprising in combination (a) means to rotate the autorotor to a predetermined angular velocity prior to release from the launcher (b) means which direct the rotation of the autorotor in a clockwise or counterclockwise direction resulting in the desired angle of glide of the munition to a preselected area without the aid of the forward speed of the ... |
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| Three-Dimensional Turbulent Boundary Layer on a Spinning Cone at Angle of Attack. |
OCT 1977 |
|
| Authors:
C. Phillip Ford III; NORTH CAROLINA STATE UNIV RALEIGH DEPT OF MECHANICAL AND AEROSPACE ENGINEERING
|
| This report investigates the three-dimensional turbulent boundary layer on a spinning cone at small angles of attack in incompressible flow. It is assumed that the boundary layer has no effect on the inviscid flow and thus the inviscid flow is used as the outer boundary condition for the boundary layer equations. A momentum integral technique was used to reduce the governing equations to two. The two resulting partial differential equations ... |
|
| Boundary Layer Effects - Proceedings of the U.S. Air Force/Federal Republic of Germany Data Exchange Agreement Meeting (5th). Held at Wright-Patterson AFB, Ohio on 28-29 April 1976. |
JUL 1977 |
|
| Authors:
Anthony W. Fiore; AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OHIO
|
| In 1968 the United States Air Force and the Federal Republic of Germany signed a Data Exchange Agreement numbered AF-68-G-7416 entitled 'Boundary Layer Effects.' The purpose was to exchange data in the area of boundary layer research. It includes both experimental and theoretical boundary layer research at speeds from subsonic to hypersonic in the presence of laminar, transitional, and turbulent boundary layers. The main effort in recent years has been ... |
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| Aerodynamics of Tactical Weapons to Mach Number 3 and Angle of Attack 15 deg. Part I. Theory and Application. |
FEB 1977 |
|
| Authors:
Frank G. Moore; Roy C. Swanson Jr; NAVAL SURFACE WEAPONS CENTER DAHLGREN LAB VA
|
| Several theoretical and empirical procedures are combined to form a useful design tool for computing static and dynamic aerodynamics on missiles, projectiles, and rockets. The Mach number and angle-of-attack range over which the method is applicable are O < or = M < or = 3 and O < or = alpha < or = 15 deg, respectively. Body and wing geometries can be quite general in that pointed or ... |
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| Wake Measurements Behind a Magnetically-Suspended Spinning and Non-Spinning Ogive Cylinder at Angles of Attack. |
FEB 1977 |
|
| Authors:
Douglas M. Finn; Charles W. Haldeman; Eugene E. Covert; MASSACHUSETTS INST OF TECH CAMBRIDGE AEROPHYSICS LAB
|
| Total pressure measurements were performed in the wake of a magnetically-suspended ogive nosed cylinder immersed in a subsonic flow. Profile drag was computed by the momentum defect method and compared to magnetic balance measurements. Impact pressure wake profiles were then recorded to investigate the effects of varying Reynolds number, angle of attack, spin rate, and transition on wake characteristics. Fully turbulent boundary layer conditions served to attenuate this reverse Magnus ... |
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| Experimental Measurements of the Turbulent Boundary Layer on a Yawed, Spinning Slender Body. |
JAN 1977 |
27 pages |
| Authors:
Walter B. Sturek; James E. Danberg; BALLISTIC RESEARCH LABS ABERDEEN PROVING GROUND MD
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| Experimental measurements of the tripped turbulent boundary layer profile characteristics on a yawed, spinning tangent-ogive-cylinder model are described. The profile measurements were made using a flattened total head probe at 30 deg increments completely about the azimuthal plane for three longitudinal stations at M = 3, alpha = 4 deg omega = 0 and 10,000 RPM. Wall static pressure measurements were obtained in order to compute velocity profiles from the ... |
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| Boundary Layer over Spinning Blunt-Body of Revolution at Incidence Including Magnus Forces, |
1977 |
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| Authors:
K. C. Wang; MARTIN MARIETTA LABS BALTIMORE MD
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| An incompressible laminar flow over a spinning blunt-body at incidence is investigated. The approach follows strictly the three-dimensional boundary layer theory, and the lack of initial profiles is readily resolved. The rule of the dependence zone is satisfied with the Krause scheme and complete numerical solutions are obtained for an ellipsoid of revolution at 6 deg incidences and two different spin rates. Spinning causes asymmetry which, in turn, introduces the ... |
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| Experimental Roll-Damping, Magnus, and Static-Stability Characteristics of Two Slender Missile Configurations at High Angles of Attack (0 to 90 deg) and Mach Numbers 0.2 through 2.5. |
JUL 1976 |
115 pages |
| Authors:
Leroy M. Jenke; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AIR FORCE STATION TENN
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| An experimental investigation was conducted to verify that the recently developed high-alpha missile roll-damping test mechanism could be used to obtain the roll-damping characteristics of slender missile configurations and to obtain roll-damping, Magnus, static-stability, and axial-force characteristics of a typical missile configuration. The verification tests were conducted with the Basic Finner Model at M = 0.22 and 2.50. Additional test results were obtained with a Modified Basic Finner Model for ... |
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Reports by Keyword(s)
MAGNUS EFFECT
