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:

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).

Download or read book Prediction of Aerodynamics of Missiles at High Angles of Attack in Supersonic Flow written by Marnix F. E. Dillenius and published by . This book was released on 1975 with total page 203 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).

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.

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).

Download or read book Technical Abstract Bulletin written by Defense Documentation Center (U.S.) and published by . This book was released on 1963 with total page 824 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1987 with total page 1124 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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.

Download or read book Normal Force Center of Pressure and Zero lift Drag of Several Ballistic type Missiles at Mach Numbers of 4 05 written by Edward F. Ulmann and published by . This book was released on 1954 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted at Mach number 4.05 to determine the aerodynamic characteristics of several missile models having turbulent boundary layers and to compare these results with available method of predicting the aerodynamic characteristics. (The condition of the boundary layer was determined by the china-clay-lacquer boundary-layer-visualization technique.) Normal force and pitching moment were measured through an angle-of-attack range of 0 to between 4 and 8 degrees, depending upon balance limitations, and at roll angles of 0 and 45 degrees; drag was measured only at 0 degrees angle of attack.

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.

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:

Download or read book Static Stability and Drag Characteristics of the HAST Missile at Mach Numbers 2 25 3 0 and 4 0 written by J. T. Best (Jr.) and published by . This book was released on 1974 with total page 194 pages. Available in PDF, EPUB and Kindle. Book excerpt: Static-force tests were conducted at Mach number 2.25, 3, and 4 on a 0.25 -scale model of the High Altitude Supersonic Target (HAST) missile.

Download or read book International Aerospace Abstracts written by and published by . This book was released on 1997 with total page 656 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Government Reports Announcements Index written by and published by . This book was released on 1978 with total page 904 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Government reports annual index written by and published by . This book was released on 199? with total page 1008 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Government Reports Annual Index Keyword A L written by and published by . This book was released on 1982 with total page 1016 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerospace America written by and published by . This book was released on 1992 with total page 662 pages. Available in PDF, EPUB and Kindle. Book excerpt: