Download or read book Subsonic Unsteady Aerodynamics for General Configurations Part 2 Volume 2 Computer Program N5KA written by and published by . This book was released on 1972 with total page 260 pages. Available in PDF, EPUB and Kindle. Book excerpt: A technique for predicting steady and oscillatory aerodynamic loads on general configurations has been developed which is based on the Doublet- Lattice Method and the method of images. Chord- and spanwise loading on lifting surfaces and longitudinal body load distributions are determined. Configurations may be composed of an assemblage of bodies (elliptic cross sections and a distribution of width or radius) and lifting surfaces (arbitrary planform and dihedral, with or without control surfaces). Loadings predicted by this method are required for flutter, gust, frequency response and static aeroelastic analyses and may be used to determine static and dynamic stability derivatives. The methods described in this report are intended to be used by airplane designers to calculate with improved accuracy, the unsteady aerodynamic pressures that act on a lifting surface being propelled at subsonic speeds. The new feature of these calculations is that the effects on the pressure field induced by interference between the fuselage, for example, and the wing or the wing, pylon and nacelle, are taken into account. These calculations are an essential ingredient of flutter analyses and will improve the confidence level of such calculations in preventing wing-store flutter and flutter of advanced vehicles where fuselages are relatively large, provide some lifting capability and cause noticeable interference effects. The general requirement for such calculations are contained in Military Specification MIL-A-8870A(USAF).
Download or read book Subsonic Unsteady Aerodynamics for General Configurations Part 1 Volume 2 Computer Program H7WC written by and published by . This book was released on 1971 with total page 156 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two methods of accounting for body-lifting surface interference in unsteady flow are considered. The first method is described in Part 1 of the report, while the second will be described in another paper. The first method is a direct application of nonplanar lifting surface elements to both the lifting surfaces and the body surfaces. The body is treated as an annular wing. This type of idealization must be used with an axial doublet introduced to account for body incidence effects. The undesirable effects of the annular wing representation are then reduced. The report also describes an improvement of the Doublet-Lattice Method of Albano and Rodden. The improvement pertains to wing- tail problems where there exists a small vertical (non-zero) separation between the wing and tail planes.
Download or read book Subsonic Unsteady Aerodynamics for General Configurations Part 2 Volume 1 Application of the Doublet Lattice Method and the Method of Images to Lifting Surface Body Interference written by and published by . This book was released on 1972 with total page 255 pages. Available in PDF, EPUB and Kindle. Book excerpt: A technique for predicting steady and oscillatory aerodynamic loads on general configurations has been developed which is based on the Doublet- Lattice Method and the method of images. Chord- and spanwise loading on lifting surfaces and longitudinal body load distributions are determined. Configurations may be composed of an assemblage of bodies (elliptic cross sections and a distribution of width or radius) and lifting surfaces (arbitrary planform and dihedral, with or without control surfaces). Loadings predicted by this method are required for flutter, gust, frequency response and static aeroelastic analyses and may be used to determine static and dynamic stability derivatives. The methods described in this report are intended to be used by airplane designers to calculate with improved accuracy, the unsteady aerodynamic pressures that act on a lifting surface being propelled at subsonic speeds. The new feature of these calculations is that the effects on the pressure field induced by interference between the fuselage, for example, and the wing or the wing, pylon and nacelle, are taken into account. These calculations are an essential ingredient of flutter analyses and will improve the confidence level of such calculations in preventing wing-store flutter and flutter of advanced vehicles where fuselages are relatively large, provide some lifting capability and cause noticeable interference effects.
Download or read book The NASTRAN Theoretical Manual written by and published by . This book was released on 1981 with total page 946 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Technical Abstract Bulletin written by and published by . This book was released on 1981 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASTRAN User s Manual written by and published by . This book was released on 1970 with total page 974 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The NASTRAN Theoretical Manual written by and published by . This book was released on 1970 with total page 504 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Subsonic Unsteady Aerodynamics for General Configurations Part I Volume I Direct Application of the Nonplanar Doublet Lattice Method written by Joseph P. Giesing and published by . This book was released on 1971 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two methods of accounting for body-lifting surface interference in unsteady flow are considered. The first method is a direct application of nonplanar lifting surface elements to both the lifting surfaces and the body surfaces. This type of idealization must be used with an axial doublet introduced to account for body incidence effects. The undesirable effects of the annular wing representation are then reduced. The second approach uses an image system and an axial singularity system to account for the effects of the bodies. The methods described are intended to be used by airplane designers to calculate with improved accuracy, the unsteady aerodynamic pressures that act on a lifting surface being propelled at subsonic speeds. The new feature of these calculations is that the effects on the pressure field induced by interference between the fuselage, for example, and the wing or the wing, pyon and nacelle, are taken into account. These calculations are an essential ingredient of flutter analyses and will improve the confidence level of such calculations in preventing wing-store flutter and flutter of advanced vehicles where fuselages are relatively large, provide some lifting capability and cause noticeable interference effects. (Author).
Download or read book Aeroelastic Addition to NASTRAN written by William P. Rodden and published by . This book was released on 1979 with total page 122 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Contractor Report written by and published by . This book was released on 1979 with total page 828 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Unsteady Aerodynamics for Advanced Configurations written by H. T. Vivian and published by . This book was released on 1965 with total page 130 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book ASTROS Enhancements written by D. J. Neill and published by . This book was released on 1995 with total page 250 pages. Available in PDF, EPUB and Kindle. Book excerpt: ASTROS (Automated STRuctural Optimization System) is a computer program for the multidisciplinary design and analysis of aerospace structures. ASTROS combines mathematical optimization algorithms with traditional structural analysis disciplines such as static forces, normal modes, static aeroelasticity, and dynamic aeroelasticity (flutter), all in a finite element context, to perform automated preliminary design of an aircraft structure. This report is a complete user's manual that documents the many features of ASTROS through version 12 of the software package. It also provides information on system architecture and other topics of interest. This report is Volume 3 of a set; Volume 1 (WL-TR-93-3025) is the user's manual.
Download or read book A Program to Compute Three dimensional Subsonic Unsteady Aerodynamic Characteristics Using the Doublet Lattice Method L216 DUBFLEX Volume 2 Supplemental System Design and Maintenance Document written by and published by . This book was released on 1979 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Journal of Aircraft written by and published by . This book was released on 1999 with total page 488 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Automated Structural Optimization System ASTROS written by E. H. Johnson and published by . This book was released on 1988 with total page 240 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Program to Compute Three dimensional Subsonic Unsteady Aerodynamic Characteristics Using the Doublet Lattice Method L216 DUBFLEX Supplemental system design and maintenance document written by M. Richard and published by . This book was released on 1979 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The program input presented consists of configuration geometry, aerodynamic parameters, and modal data; output includes element geometry, pressure difference distributions, integrated aerodynamic coefficients, stability derivatives, generalized aerodynamic forces, and aerodynamic influence coefficient matrices. Optionally, modal data may be input on magnetic file (tape or disk), and certain geometric and aerodynamic output may be saved for subsequent use.--V. I. The information necessary for execution of the digital computer program L216 on the CDC 6600 is described. L216 characteristics are based on the doublet lattice method. Arbitrary aerodynamic configurations may be represented with combinations of nonplanar lifting surfaces composed of finite constant pressure panel elements, and axially summetric slender bodies composed of constant pressure line elements. Program input consists of configuration geometry, aerodynamic parameters, and modal data; output includes element geometry, pressure difference distributions, integrated aerodynamic coefficients, stability derivatives, generalized aerodynamic forces, and aerodynamic influence coefficient matrices. Optionally, modal data may be input on magnetic field (tape or disk), and certain geometric and aerodynamic output may be saved for subsequent use.--V. II.
Download or read book The NASTRAN Programmer s Manual written by and published by . This book was released on 1969 with total page 1002 pages. Available in PDF, EPUB and Kindle. Book excerpt:
