An Investigation of Vortex Path and Strength of Finned Missiles at High Angle of Attack and Numerical Calculation of Induced Rolling Moment PDF Download
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Author: Charles S. W. Wong
Publisher:
ISBN:
Category : Projectiles, Aerial
Languages : en
Pages : 76
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Book Description
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).
Author: Charles S. W. Wong
Publisher:
ISBN:
Category : Projectiles, Aerial
Languages : en
Pages : 76
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Book Description
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).
Author: Daniel G. Udelson
Publisher:
ISBN:
Category : Projectiles, Aerial
Languages : en
Pages : 112
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Book Description
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.
Author: Steven I. Kane
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 74
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Book Description
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).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1034
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Book Description
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: Air Force Cambridge Research Laboratories (U.S.)
Publisher:
ISBN:
Category : Bibliographical literature
Languages : en
Pages : 240
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Author: Henry W. Woolard
Publisher:
ISBN:
Category : Aerodynamic measurements
Languages : en
Pages : 40
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Author: William L. Oberkampf
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 148
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Author: James DeSpirito
Publisher:
ISBN:
Category : Computational fluid dynamics
Languages : en
Pages : 212
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Book Description
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.
Author: Robert William Conlan
Publisher:
ISBN:
Category : Guided missiles
Languages : en
Pages : 64
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Book Description
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.
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1450
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Book Description
