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An Investigation Of Vortex Path And Strength Of Finned Missiles At High Angle Of Attack And Numerical Calculation Of Induced Rolling Moment
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Book Synopsis An Investigation of Vortex Path and Strength of Finned Missiles at High Angle of Attack and Numerical Calculation of Induced Rolling Moment by : Charles S. W. Wong
Download or read book An Investigation of Vortex Path and Strength of Finned Missiles at High Angle of Attack and Numerical Calculation of Induced Rolling Moment written by Charles S. W. Wong and published by . This book was released on 1971 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: The vortex paths and strengths generated by finless, planar and cruciform missiles have been measured in the subsonic wind tunnel. Measurements for the finless missile were taken at wind tunnel speeds of 70 and 100 m.p.h. and at angles of attack of 10, 15, 20 degrees. The planar and cruciform missile measurements were taken at wind tunnel speeds of 70 m.p.h. with angles of attack of 15 and 20 degrees for the planar fin and 15 degrees for the cruciform fin. Computer program results have been generated for the vortex induced rolling moment on a missile with planar fins at a high angle of attack with the input vortex positions and strengths taken from the results of this report. (Author).
Book Synopsis Vortex Induced Rolling Moments on Finned Missiles at High Angle of Attack by : Daniel G. Udelson
Download or read book Vortex Induced Rolling Moments on Finned Missiles at High Angle of Attack written by Daniel G. Udelson and published by . This book was released on 1968 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt: Previous analytical studies endeavoring to account for vortex induced rolling moments on missiles have not successfully correlated with experimental results. This points up the need for a theoretically more sophisticated treatment, which the present work attempts to satisfy. A model for the two dimensional cross flow past the tail body combination is employed and the Blasius complex contour integral used to find the moments. The final result contained herein presents the complete mathematical solution for the two dimensional ideal flow past a planar tail body combination. It is in closed analytic form with the exception of one definite integral which has been reduced to a form suitable for numerical calculation. All terms of the solution (integrated as well as the integral) are best calculated for various values of the parameters on a large scale digital computer.
Book Synopsis Vortex Induced Rolling Moments on Cruciform Missiles at High Angle of Attack by : Steven I. Kane
Download or read book Vortex Induced Rolling Moments on Cruciform Missiles at High Angle of Attack written by Steven I. Kane and published by . This book was released on 1971 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt: The problem of predicting the induced roll phenomena associated with finned missiles at high angles of attack has been approached by examining the interaction between the body wake vortex system and the finned surfaces of the missile. The application of the classic Blasius moment integral to this problem permits the independent evaluation of each singularity in the flow field which may contribute to the moments. This method is applicable to missiles employing fin schemes of any geometry and is used herein to analyze the induced roll of a typical cruciform missile configuration. A computer program has been developed to generate numerical solutions utilizing those parameters which affect the magnitude and direction of the induced roll. (Author).
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1972 with total page 1034 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Bibliography, with Abstracts, of AFCRL Publications from 1 April to 30 June 1971 by : Air Force Cambridge Research Laboratories (U.S.)
Download or read book Bibliography, with Abstracts, of AFCRL Publications from 1 April to 30 June 1971 written by Air Force Cambridge Research Laboratories (U.S.) and published by . This book was released on 1971 with total page 240 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Selective Bibliography on High-angle-of-attack Aerodynamics of Aircraft and Aircraft Components at Subsonic Speeds by : Henry W. Woolard
Download or read book A Selective Bibliography on High-angle-of-attack Aerodynamics of Aircraft and Aircraft Components at Subsonic Speeds written by Henry W. Woolard and published by . This book was released on 1974 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Prediction of Forces and Moments on Finned Missiles at High Angle of Attack in Transonic Flow by : William L. Oberkampf
Download or read book Prediction of Forces and Moments on Finned Missiles at High Angle of Attack in Transonic Flow written by William L. Oberkampf and published by . This book was released on 1980 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Numerical Investigation of Aerodynamics of Canard-controlled Missile Using Planar and Grid Tail Fins by : James DeSpirito
Download or read book Numerical Investigation of Aerodynamics of Canard-controlled Missile Using Planar and Grid Tail Fins written by James DeSpirito and published by . This book was released on 2004 with total page 212 pages. Available in PDF, EPUB and Kindle. Book excerpt: Viscous computational fluid dynamic simulations were used to predict the aerodynamic coefficients and flow field around a canard-controlled missile in subsonic and transonic flow. Computations were performed at Mach 0.6 and 0.9, six angles of attack between 0 deg and 10 deg, and with planar and grid tail fins. The computations were validated with wind tunnel data. Flow visualizations showed that the canard downwash produced a low-pressure region on the starboard side of the missile that produced a large induced side force. The canard trailing vortices interacted with the tail fins until alpha> 8 deg, producing a pressure differential on the leeward tail fin, leading to the adverse induced roll effects. Visualizations of the flow through the grid fin structure showed choking of the flow at Mach 0.9 and Mach 1.5. The validated simulations results showed that grid fins did not improve the canard roll-control effectiveness at subsonic and transonic speeds as well as they did at the low supersonic speed.
Book Synopsis Vortex Induced Rolling Moment on Cruciform Configured Missiles by : Robert William Conlan
Download or read book Vortex Induced Rolling Moment on Cruciform Configured Missiles written by Robert William Conlan and published by . This book was released on 1973 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: A simplified treatment of vortex induced rolling moment on cruciform configured missiles is presented. Potential flow is assumed along with steady state conditions so that the problem can be classified as a pure boundary value problem. The final integral for roll moment is made analytic so that residue calculus can be used to find a closed form solution. Comparison of this equation with strip theory for a cruciform finned missile for various fin span-to-body radius ratios is good.
Download or read book Government Reports Index written by and published by . This book was released on 1971 with total page 1450 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Bibliography of Scientific and Industrial Reports by :
Download or read book Bibliography of Scientific and Industrial Reports written by and published by . This book was released on 1971 with total page 728 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Numerical Investigation of Aerodynamics of Canard-Controlled Missile Using Planar and Grid Tail Fins. Part 1. Supersonic Flow by : James DeSpirito
Download or read book Numerical Investigation of Aerodynamics of Canard-Controlled Missile Using Planar and Grid Tail Fins. Part 1. Supersonic Flow written by James DeSpirito and published by . This book was released on 2002-09 with total page 91 pages. Available in PDF, EPUB and Kindle. Book excerpt: Viscous computational fluid dynamic simulations were used to predict the aerodynamic coefficients and flowfield around a generic canard-controlled missile configuration in supersonic flow. Computations were performed for Mach 1.5 and 3.0, at six angles of attack between 0 and 10, with 0 and 10 canard deflection, and with planar and grid tail fins, for a total of 48 cases. Validation of the computed results was demonstrated by the very good agreement between the computed aerodynamic coefficients and those obtained from wind tunnel measurements. Visualizations of the flowfield showed that the canard trailing vortices and downwash produced a low-pressure region on the starboard side of the missile that in turn produced an adverse side force. The pressure differential on the leeward fin produced by the interaction with the canard trailing vortices is primarily responsible for the adverse roll effect observed when planar fins are used. Grid tail fins improved the roll effectiveness of the canards at low supersonic speed. No adverse rolling moment was observed with no canard deflection, or at the higher supersonic speed for either tail fin type due to the lower intensity of the canard trailing vortices in these cases. Flow visualizations from the simulations performed in this study help in the understanding of the flow physics and can lead to improved canard and tail fin designs for missiles and rockets.
Book Synopsis High Angle of Attack Missile Aerodynamics at Mach Numbers 0.30 to 1.5 by :
Download or read book High Angle of Attack Missile Aerodynamics at Mach Numbers 0.30 to 1.5 written by and published by . This book was released on 1980 with total page 330 pages. Available in PDF, EPUB and Kindle. Book excerpt: A large body of wind tunnel data was generated by tests of a smooth missile model with several interchangeable nose parts. The tests were conducted at subsonic through supersonic speeds at angles of attack from 0 to 180 degrees. They were part of the FDL and SAMSO technology studies which preceded design of the MX missile. Measurements of both surface pressures and total forces and moments were made at a variety of Mach numbers and Reynolds number combinations. This data was supplemented with wake flow-field measurements of the impact pressure and flow direction at angles of attack where maximum induced side force was expected to occur. A review of the literature for subsonic and transonic aerodynamic characteristics of bodies of revolution was conducted. A comprehensive discussion is provided of the important variables of the high angle of attack flow phenomena. The test data provided insight into the effect of several variables that had not been adequately treated in the past. The high angle of attack data was analyzed to deduce the vortex shedding location, the vortex strength, and the vortex paths in the wake. Discrete vortex theory was examined as a method which could be modified, based on experimental data, and used to predict the aerodynamic characteristics of missiles to greater accuracy. An alternate approach to developing a prediction method was explored by means of a correlation of the surface pressure data.
Book Synopsis An Improved Semiempirical Method for Calculating Aerodynamics of Missiles with Noncircular Bodies by : Frankie Gale Moore
Download or read book An Improved Semiempirical Method for Calculating Aerodynamics of Missiles with Noncircular Bodies written by Frankie Gale Moore and published by . This book was released on 1997 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamics of Missiles Wih Offset Fin Configurations by : Gregg L. Abate
Download or read book Aerodynamics of Missiles Wih Offset Fin Configurations written by Gregg L. Abate and published by . This book was released on 1989 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of Flow and Stability Characteristics for a Body of Revolution with Fins and Flare in Presence of Plume Induced Separation at Mach Numbers 0.7 to 1.4 by : Calvin Wayne Dahlke
Download or read book An Investigation of Flow and Stability Characteristics for a Body of Revolution with Fins and Flare in Presence of Plume Induced Separation at Mach Numbers 0.7 to 1.4 written by Calvin Wayne Dahlke and published by . This book was released on 1977 with total page 200 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a wind tunnel test, simulating rocket motor exhaust jet effects on missile aerodynamic at Mach numbers of 0.7 to 1.4 are presented. A normal jet plume simulator was used to induce afterbody boundary layer separation. Flow visualization techniques including both shadowgraph and oil flow photographs were taken. The primary emphasis for this report is the force and moment measurements taken on twelve configurations including: five tail fin configurations; body alone; three forward fin configurations; body flare combination; and two combinations of forward fins/strakes with tail fins. All force and moment coefficients are presented in plotted form. One configuration is shown with ground plane interference simulation. (Author).
Book Synopsis Numerical Investigation of Aerodynamics of Canard-Controlled Missile Using Planar and Grid Tail Fins. Part 1. Supersonic Flow by :
Download or read book Numerical Investigation of Aerodynamics of Canard-Controlled Missile Using Planar and Grid Tail Fins. Part 1. Supersonic Flow written by and published by . This book was released on 2002 with total page 91 pages. Available in PDF, EPUB and Kindle. Book excerpt: Viscous computational fluid dynamic simulations were used to predict the aerodynamic coefficients and flowfield around a generic canard-controlled missile configuration in supersonic flow. Computations were performed for Mach 1.5 and 3.0, at six angles of attack between 0 and 10, with 0 and 10 canard deflection, and with planar and grid tail fins, for a total of 48 cases. Validation of the computed results was demonstrated by the very good agreement between the computed aerodynamic coefficients and those obtained from wind tunnel measurements. Visualizations of the flowfield showed that the canard trailing vortices and downwash produced a low-pressure region on the starboard side of the missile that in turn produced an adverse side force. The pressure differential on the leeward fin produced by the interaction with the canard trailing vortices is primarily responsible for the adverse roll effect observed when planar fins are used. Grid tail fins improved the roll effectiveness of the canards at low supersonic speed. No adverse rolling moment was observed with no canard deflection, or at the higher supersonic speed for either tail fin type due to the lower intensity of the canard trailing vortices in these cases. Flow visualizations from the simulations performed in this study help in the understanding of the flow physics and can lead to improved canard and tail fin designs for missiles and rockets.
