Vortex Induced Rolling Moments on Cruciform Missiles at High Angle of Attack PDF Download
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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: 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: 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: 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:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1126
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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: 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: Air Force Cambridge Research Laboratories (U.S.)
Publisher:
ISBN:
Category : Bibliographical literature
Languages : en
Pages : 240
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Book Description
Author: C. A. Smith
Publisher:
ISBN:
Category :
Languages : en
Pages : 94
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Book Description
This report describes improved methods for calculating the aerodynamic characteristics of cruciform missiles to high angles of attack. These include a more accurate method of calculating the effects of the vorticity generated by crossflow over the body between the first and second set of fins, an improved fin trailing vortex model, and numerous minor improvements. The improved methods have been incorporated into an existing computer program that computes component forces and moments on a cruciform missile, including effects of arbitrary roll and control deflection.
Author: Marnix F. E. Dillenius
Publisher:
ISBN:
Category :
Languages : en
Pages : 203
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Book Description
Improvements have been added to a computer program previously reported in NEAR Technical Report 74 for calculating the loadings on cruciform wing-body combinations at supersonic speeds and it has been extended to wing-body-tail combinations. An improvement in the accuracy of calculating the pressures acting on the combination enables good agreement between experimental and theoretical fin forces and moments up to 20 deg to angle of attack. An option has been added to the computer program to include the effect of nose vortices on the loading of the canard fins and body. In addition, the necessary distributions of leading-edge and side-edge suction forces have been calculated to set up the model of the separation vortices from the leading edges and side edges of the canard fins using the Polhamus vortex-lift analogy. For the case considered, compressibility was shown to have little effect on the trajectories of vortices from the canard fins to the empennage. In addition, the effect of the nose and canard vortices on the cruciform tail forces and moments have been determined. Thus, the capability for determining the characteristics of a complete missile has been developed. A listing of the computer program and a calculative example are included. Extensive comparisons between the prediction of the computer program and experiment are included with generally good agreement. (Author).
Author:
Publisher:
ISBN:
Category : Engineering
Languages : en
Pages : 716
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Book Description
Includes proceedings of various meetings and conferences.
Author: William L. Oberkampf
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 148
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Book Description
