Download or read book Body surface Pressure Data on Two Monoplane wing Missile Configurations with Elliptical Cross Sections at Mach 2 50 written by Jerry M. Allen and published by . This book was released on 1983 with total page 162 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effect of Nose Bluntness and Afterbody Shape on Aerodynamic Characteristics of a Monoplanar Missile Concept with Bodies of Circular and Elliptical Cross Sections at a Mach Number of 2 50 written by Ernald B. Graves and published by . This book was released on 1979 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Compilation of Static Stability and Fin Loads Data for Slender Body Missile Models with and Without Tail Fins and Wings written by G. R. Gomillion and published by . This book was released on 1976 with total page 404 pages. Available in PDF, EPUB and Kindle. Book excerpt: This document contains a compilation of aerodynamic data for the Martin Generalized Research Model, which is a composite of several body, wing, and tail fin configurations typical of missile applications. The model variations included five body configurations, three wing configurations at various body locations, and 15 tail fin configurations. Static stability and tail fin loads data are presented in tabulated and plotted form for a Mach number range from 0.20 to 4.63 over an angle-of-attack range from -6 to 60 deg and a sideslip angle range from -20 to 20 deg for the body-alone configurations, body-wing configurations, and the body-wing-tail fin configurations. In addition, the tail fin configurations were tested using the reflection plane technique, and the resulting fin loads data are presented for a Mach number range of 0.80 to 2.16 over an angle-of-attack range from 0 to 210 deg. Volume I contains the narrative and selected plotted data. (Author).
Download or read book Pressure and Static Force Test of Three Elliptic Missile Body Configurations at Mach Numbers 1 5 to 5 0 written by M. E. Sellers and published by . This book was released on 1983 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Flight Investigation of the Zero lift Drag of Two Ram jet Missile Configurations at Mach Numbers from 1 0 to 1 89 written by Clarence A. Brown and published by . This book was released on 1953 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics of a Monoplanar Missile Concept with Bodies of Circular and Elliptical Cross Sections written by Ernald B. Graves and published by . This book was released on 1977 with total page 196 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressure Test of Three Elliptic Missile Body Configuratins written by Marvin E. Sellers and published by . This book was released on 1985 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Improvements to the Missile Aerodynamic Prediction Code Demon3 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-18 with total page 172 pages. Available in PDF, EPUB and Kindle. Book excerpt: The computer program DEMON3 was developed for the aerodynamic analysis of nonconventional supersonic configurations comprising a body with noncircular cross section and up to two wing or fin sections. Within a wing or fin section, the lifting surfaces may be cruciform, triform, planar, or low profile layouts; the planforms of the lifting surfaces allow for breaks in sweep. The body and fin sections are modeled by triplet and constant u-velocity panels, respectively, accounting for mutual body-fin interference. Fin thickness effects are included for the use of supersonic planar source panels. One of the unique features of DEMON3 is the modeling of high angle of attack vortical effects associated with the lifting surfaces and the body. In addition, shock expansion and Newtonian pressure calculation methods can be optionally engaged. These two dimensional nonlinear methods are augmented by aerodynamic interference determined from the linear panel methods. Depending on the geometric details of the body, the DEMON3 program can be used to analyze nonconventional configurations at angles of attack up to 25 degrees for Mach numbers from 1.1 to 6. Calculative results and comparisons with experimental data demonstrate the capabilities of DEMON3. Limitations and deficiencies are listed. Dillenius, Marnix F. E. and Johnson, David L. and Lesieutre, Daniel J. Unspecified Center AERODYNAMIC CHARACTERISTICS; AERODYNAMICS; BODY-WING AND TAIL CONFIGURATIONS; COMPUTER PROGRAMS; DESIGN ANALYSIS; FINS; MISSILE DESIGN; MISSILES; PANEL METHOD (FLUID DYNAMICS); WINGS; AERODYNAMIC INTERFERENCE; ANGLE OF ATTACK; LAYOUTS; NEWTON METHODS; NONLINEARITY; PLANFORMS; THICKNESS; TRANSONIC SPEED...
Download or read book Theoretical Analysis of the Flow Field Over a Family of Ogive Bodies written by Ronnie W.. Guy and published by . This book was released on 1977 with total page 456 pages. Available in PDF, EPUB and Kindle. Book excerpt: Several analytical methods were employed to calculate the flow fields about spherically blunted ogives from Mach numbers of zero to 4.5. The methods used were the Dougles Herman (a panel method) with compressibility correction, the South potential flow program (RAXBOD) and the three dimensional method of characteristics. Bluntnesses varied from zero (sharp nosed) to one (hemispherical nose) and the finess ratio varied from 0.5 to 4.0. Where the computer codes being used permitted, the flow fields were calculated for 2 deg and 0 deg angle of attack; in all other cases only 0 deg angle of attack was considered. Data are presented for body surface distributions of pressure and Mach number and for wave drag. (Author).
Download or read book New Methods for Predicting Nonlinear Lift Center of Pressure and Pitching Moment on Middile Configurations written by Frankie Gale Moore and published by . This book was released on 1992 with total page 192 pages. Available in PDF, EPUB and Kindle. Book excerpt: A new semiempirical method has been developed to predict normal force, pitching moment, and center of pressure on missile configurations up to angles of attack of 30° The method is based on linear theory and slender body techniques at low angle of attack and uses wind tunnel data to derive nonlinear angle-of-attack corrections as angle of attack increaces. The new improved theories include body alone, wing alone, and body-wing and wing-body interference. While the new theory is databased, simple analytical formulas are derived that allow general use of the techniques. Comparison with the linearized approaches used in the former NSWCDD aeroprediction code shows singificant reductions in errors of aerodynamics above 5° to 10° angle of attack. Limited comparisons to other state-of-the-art engineering codes show the new theory to be as good as or better than anything known to be available for computing planar aerodynamics up to 30° angle of attack.
Download or read book Wind Tunnel Tests of Elliptical Missile Body Configurations at Mach Numbers 0 4 to 5 0 written by Donald E. Shereda and published by . This book was released on 1987 with total page 161 pages. Available in PDF, EPUB and Kindle. Book excerpt: A large body of wind tunnel data was generated by tests of missile bodies of varying ellipticity ratios. The tests were conducted at subsonic through high supersonic speeds at angles of attack from -4 to 20 degrees. Measurements of both surface pressure and total forces and moments were made at a variety of Mach numbers and Reynolds number combinations. This data was supplemented with flow visualization data such as vapor screens, oil flows and shadowgraphs at selected supersonic Mach numbers. The missile bodies were power-law bodies with an exponent of 0.5 and ellipticity ratios of 2.0, 2.5, and 3.0 to 1. Comparisons of selected data with various prediction codes (Supersonic/Hypersonic Arbitrary Body Program, NSWC Euler Code, Missile Datcom, and FLO-57 Euler Code) were made. The test data provided insight into the effects of several variables and will provide a good data base for correlations with numerical techniques.
Download or read book Theoretical Analysis of the Flow Field Over a Family of Ogive Bodies written by R. L. Richardson and published by . This book was released on 1979 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: Local body surface pressure coefficients and Mach numbers are presented for tangent ogive bodies at Mach numbers from 2 to 4.5 and at 0 and 2 deg angle-of-attack. These data were obtained using the US Army Missile Research and Development Command three-dimensional method of characteristics computer code. This volume is intended to supplement MIRADCOM Technical Report TD-CR-77-5, published August 1977. (Author).
Download or read book Aerodynamic Characteristics of Wraparound Fins Mounted on Bodies of Revolution and Rheir Influence on the Missile Static Stability at Mach Numbers from 0 3 to 1 3 written by Calvin Wayne Dahlke and published by . This book was released on 1972 with total page 376 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental aerodynamic investigations were conducted for several wraparound fins and one planar fin configuration on bodies of revolution at Mach number ranging from 0.3 to 1.3 and angles of attack from -6 degrees to 6 degrees at 0 degrees at sideslip angle. Six component aerodynamic forces and moments were recorded on the complete missile configuration while simultaneously measuring the aerodynamic normal force and bending moments acting on each fin. The fin configuration parameters varied include chord length, fin thickness, leading edge configuration, tip chord geometry and body, root chord gap. The report presents the plotted coefficient data in two volumes. Volume I contains the complete missile aerodynamic data. Volume 2 contains the individual fin aerodynamic data.
Download or read book A Study of Various Slender and Non slender Fin body Combinations of Missile Configurations written by N. Uchiyama and published by . This book was released on 1976 with total page 190 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic loading on a number of rocket body-control surface combinations has been calculated using methods developed at the University of Tennessee Space Institute over the past five years. Variations in control surface planform, roll angle, control surface deflection or incorporation of elevons, are included. Compressibility is accounted for. Details of the digital computer program are included.
Download or read book Aerodynamic Characteristics at Mach Numbers from 1 60 to 2 16 of a Blunt nose Missile Model Having a Triangular Cross Section and Fixed Triform Fins written by William J. Monta and published by . This book was released on 1971 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The 1995 Version of the NSWC Aeroprediction Code written by Frankie Gale Moore and published by . This book was released on 1995 with total page 114 pages. Available in PDF, EPUB and Kindle. Book excerpt: The NSWC Aeroprediction Code has been extended to angles of attack (AOA) greater than 30 deg. To accomplish this, several data bases were used to approximate the nonlinearities in individual missile component aerodynamics. Theoretical aerodynamic methods are used at small AOA. The new semiempirical model was applied to several configurations and the empirical constants adjusted to eliminate some of the errors associated with wind tunnel measurements of individual missile component loads. The new version of the code (AP95) was then pplied to several other missile configurations and estimates compared to data and other aerodynamic code calculations. Comparisons were made for Mach numbers 0.1 to 10.0 and AOA of 0 to 90 deg (not all data were available on any single configuration). In general, average accuracy levels of ±10 percent could be obrained for axial and normal force coefficeint and ±4 percent of body length for center of pressure, using the AP95. An exception to this was at AOA above 30 deg and at high supersonic Mach numbers, where nonlinearities caused by internal shock interactions were not accounted for. While these accuracy levels are very encouraging for a semiempirical code, improvements in the AP95 methodology could be made by additional missile-component wind-tunnel data at high AOA.
Download or read book Government Reports Announcements Index written by and published by . This book was released on 1984-02 with total page 922 pages. Available in PDF, EPUB and Kindle. Book excerpt:
