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Calculation Of High Angle Of Attack Aerodynamics Of Fighter Configurations
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Book Synopsis Calculation of High Angle of Attack Aerodynamics of Fighter Configurations by : Chuan-Tau Edward Lan
Download or read book Calculation of High Angle of Attack Aerodynamics of Fighter Configurations written by Chuan-Tau Edward Lan and published by . This book was released on 1991 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational method for lateral-directional aerodynamics of fighter configuration is developed. The leading edge vortices are represented by free vortex filaments which are adjusted iteratively to satisfy the force-free condition. The forebody vortex separation, both symmetrical and asymmetrical, is calculated using slender body theory. Effect of boundary layer separation on lifting surfaces is accounted for using the effective sectional angles of attack. The latter are obtained iteratively by matching the nonlinear sectional lift with the computed resulted based on lifting surface theory. Results for several fighter configurations are employed for comparison with available data. It is shown that the present method produces resonable results in predicting sideslip derivatives, while role and yaw rate derivatives do not compare very well with forced oscillation test data at high angles of attack. Industrial usage of this has produced mixed results. At this time, the use of these methods in a production manner is not recommended.
Book Synopsis Calculation of High Angle of Attack Aerodynamics of Fighter Configurations by : Chuan-Tau Edward Lan
Download or read book Calculation of High Angle of Attack Aerodynamics of Fighter Configurations written by Chuan-Tau Edward Lan and published by . This book was released on 1991 with total page 180 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational method for lateral-directional aerodynamics of fighter configurations is developed. The leading-edge vortices are represented by free vortex filaments which are adjusted iteratively to satisfy the force- free condition. The forebody vortex separation, both symmetrical and asymmetrical, is calculated using slender body theory. Effect of boundary layer separation on lifting surfaces is accounted for using the effective sectional angels of attack. The latter are obtained iteratively by matching the nonlinear sectional lift with the computed resulted based on lifting-surface theory. Results for several fighter configurations are employed for comparison with available data. It is shown that the present method produces reasonable results in predicting sideslip derivatives, while roll- and yaw-rate derivatives do not compare very well with forced oscillation test data at high angles of attack. Industrial usage of this has produced mixed results. At this time, the use of these methods in a production manner is not recommended.
Book Synopsis Calculation of High Angle of Attack Aerodynamics of Fighter Configurations by : Chuan-Tau Edward Lan
Download or read book Calculation of High Angle of Attack Aerodynamics of Fighter Configurations written by Chuan-Tau Edward Lan and published by . This book was released on 1991 with total page 332 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational method for unsteady aerodynamics of fighter configurations at high angles of attack is developed. The leading-edge vortices are represented by free vortex filaments which are adjusted iteratively to satisfy the force-free condition. The small-disturbance, unsteady potential equation is solved in the frequency domain for motions in pitching, plunging, flapping, side movement, rolling, and yawing oscillation in compressible flow. Computed results in rolling moment coefficients due to side acceleration are compared with data for 60-deg and 80-deg delta wings. Lateral-directional characteristics for an F-106b configuration are also compared with data obtained in forced oscillation tests. It is shown that reasonable results can be obtained by the present unsteady flow method, but not by steady flow theory. Calculation of dynamic stall effects on a rectangular wing of aspect ratio 4 is demonstrated by using experimental section data. Although no data for the wing are available, the results appear plausible. Industrial usage of this has produced mixed results. At this time, the use of these methods in a production manner is recommended.
Book Synopsis Calculation of High Angle of Attack Aerodynamics of Fighter Configurations. Volume 1. Steady by :
Download or read book Calculation of High Angle of Attack Aerodynamics of Fighter Configurations. Volume 1. Steady written by and published by . This book was released on 1991 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational method for lateral-directional aerodynamics of fighter configuration is developed. The leading edge vortices are represented by free vortex filaments which are adjusted iteratively to satisfy the force-free condition. The forebody vortex separation, both symmetrical and asymmetrical, is calculated using slender body theory. Effect of boundary layer separation on lifting surfaces is accounted for using the effective sectional angles of attack. The latter are obtained iteratively by matching the nonlinear sectional lift with the computed resulted based on lifting surface theory. Results for several fighter configurations are employed for comparison with available data. It is shown that the present method produces resonable results in predicting sideslip derivatives, while role and yaw rate derivatives do not compare very well with forced oscillation test data at high angles of attack. Industrial usage of this has produced mixed results. At this time, the use of these methods in a production manner is not recommended.
Book Synopsis Calculation of High Angle of Attack Aerodynamics of Fighter Configurations. Volume 2. User Manual for VORSTAB-II. by :
Download or read book Calculation of High Angle of Attack Aerodynamics of Fighter Configurations. Volume 2. User Manual for VORSTAB-II. written by and published by . This book was released on 1991 with total page 175 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational method for lateral-directional aerodynamics of fighter configurations is developed. The leading-edge vortices are represented by free vortex filaments which are adjusted iteratively to satisfy the force- free condition. The forebody vortex separation, both symmetrical and asymmetrical, is calculated using slender body theory. Effect of boundary layer separation on lifting surfaces is accounted for using the effective sectional angels of attack. The latter are obtained iteratively by matching the nonlinear sectional lift with the computed resulted based on lifting-surface theory. Results for several fighter configurations are employed for comparison with available data. It is shown that the present method produces reasonable results in predicting sideslip derivatives, while roll- and yaw-rate derivatives do not compare very well with forced oscillation test data at high angles of attack. Industrial usage of this has produced mixed results. At this time, the use of these methods in a production manner is not recommended.
Book Synopsis Calculation of High Angle of Attack Aerodynamics of Fighter Configurations. Volume 3. Unsteady by :
Download or read book Calculation of High Angle of Attack Aerodynamics of Fighter Configurations. Volume 3. Unsteady written by and published by . This book was released on 1991 with total page 59 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational method for unsteady aerodynamics of fighter configurations at high angles of attack is developed. The leading-edge vortices are represented by free vortex filaments which are adjusted iteratively to satisfy the force-free condition. The small-disturbance, unsteady potential equation is solved in the frequency domain for motions in pitching, plunging, flapping, side movement, rolling, and yawing oscillation in compressible flow. Computed results in rolling moment coefficients due to side acceleration are compared with data for 60-deg and 80-deg delta wings. Lateral-directional characteristics for an F-106b configuration are also compared with data obtained in forced oscillation tests. It is shown that reasonable results can be obtained by the present unsteady flow method, but not by steady flow theory. Calculation of dynamic stall effects on a rectangular wing of aspect ratio 4 is demonstrated by using experimental section data. Although no data for the wing are available, the results appear plausible. Industrial usage of this has produced mixed results. At this time, the use of these methods in a production manner is recommended.
Book Synopsis A Selective Bibliography on High-angle-of-attack Aerodynamics of Aircraft and Aircraft Components at Subsonic Speeds by : Henry W. Woolard
Download or read book A Selective Bibliography on High-angle-of-attack Aerodynamics of Aircraft and Aircraft Components at Subsonic Speeds written by Henry W. Woolard and published by . This book was released on 1974 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722961794 Total Pages :120 pages Book Rating :4.9/5 (617 download)
Book Synopsis Calculation of Aerodynamic Characteristics of Airplane Configurations at High Angles of Attack by : National Aeronautics and Space Administration (NASA)
Download or read book Calculation of Aerodynamic Characteristics of Airplane Configurations at High Angles of Attack written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt: Calculation of longitudinal and lateral directional aerodynamic characteristics of airplanes by the VORSTAB code is examined. The numerical predictions are based on the potential flow theory with corrections of high angle of attack phenomena; namely, vortex flow and boundary layer separation effects. To account for the vortex flow effect, vortex lift, vortex action point, augmented vortex lift and vortex breakdown effect through the method of suction analogy are included. The effect of boundary layer separation is obtained by matching the nonlinear section data with the three dimensional lift characteristics iteratively. Through correlation with results for nine fighter configurations, it is concluded that reasonably accurate prediction of longitudinal and static lateral directional aerodynamics can be obtained with the VORSTAB code up to an angle of attack at which wake interference and forebody vortex effect are not important. Possible reasons for discrepancy at higher angles of attack are discussed. Tseng, J. B. and Lan, C. Edward Unspecified Center AIRCRAFT CONFIGURATIONS; ANGLE OF ATTACK; BOUNDARY LAYER SEPARATION; DIRECTIONAL STABILITY; LONGITUDINAL STABILITY; VISCOUS FLOW; AERODYNAMIC CONFIGURATIONS; AERODYNAMIC INTERFERENCE; FIGHTER AIRCRAFT; FLOW THEORY; LIFT; POTENTIAL FLOW; SUCTION; VORTICES...
Book Synopsis High Angle of Attack Aerodynamics by : Josef Rom
Download or read book High Angle of Attack Aerodynamics written by Josef Rom and published by Springer Science & Business Media. This book was released on 2012-12-06 with total page 408 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamics of aircraft at high angles of attack is a subject which is being pursued diligently, because the modern agile fighter aircraft and many of the current generation of missiles must perform well at very high incidence, near and beyond stall. However, a comprehensive presentation of the methods and results applicable to the studies of the complex aerodynamics at high angle of attack has not been covered in monographs or textbooks. This book is not the usual textbook in that it goes beyond just presenting the basic theoretical and experimental know-how, since it contains reference material to practical calculation methods and technical and experimental results which can be useful to the practicing aerospace engineers and scientists. It can certainly be used as a text and reference book for graduate courses on subjects related to high angles of attack aerodynamics and for topics related to three-dimensional separation in viscous flow courses. In addition, the book is addressed to the aerodynamicist interested in a comprehensive reference to methods of analysis and computations of high angle of attack flow phenomena and is written for the aerospace scientist and engineer who is familiar with the basic concepts of viscous and inviscid flows and with computational methods used in fluid dynamics.
Book Synopsis A Study of Prediction Methods for the High Angle-of-attack Aerodynamics of Straight Wings and Fighter Aircraft by : Oden J. McMillan
Download or read book A Study of Prediction Methods for the High Angle-of-attack Aerodynamics of Straight Wings and Fighter Aircraft written by Oden J. McMillan and published by . This book was released on 1984 with total page 208 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Calculation of Aerodynamic Characteristics of Airplane Configurations at High Angles of Attack by : Jing-Biau Tseng
Download or read book Calculation of Aerodynamic Characteristics of Airplane Configurations at High Angles of Attack written by Jing-Biau Tseng and published by . This book was released on 1988 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Calculation of Aerodynamic Characteristics of Airplane Configurations at High Angles of Attack by : J. B. Tseng
Download or read book Calculation of Aerodynamic Characteristics of Airplane Configurations at High Angles of Attack written by J. B. Tseng and published by . This book was released on 1988 with total page 186 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Conventional and Square Stores on the Longitudinal Aerodynamic Characteristics of a Fighter Aircraft Model at Supersonic Speeds by : William J. Monta
Download or read book Effect of Conventional and Square Stores on the Longitudinal Aerodynamic Characteristics of a Fighter Aircraft Model at Supersonic Speeds written by William J. Monta and published by . This book was released on 1980 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 538 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Aerodynamic Characteristics of Airplanes at High Angles of Attack by : Joseph R. Chambers
Download or read book Aerodynamic Characteristics of Airplanes at High Angles of Attack written by Joseph R. Chambers and published by . This book was released on 1977 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Analysis of a Fighter Aircraft with a Higher Order Paneling Method by : A. R. Dusto
Download or read book Aerodynamic Analysis of a Fighter Aircraft with a Higher Order Paneling Method written by A. R. Dusto and published by . This book was released on 1980 with total page 1284 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents results from analyses of steady and unsteady flows about several configurations involving the wing of the F-5 fighter airplane. The analyses were performed using higher order panel methods and the configurations analyzed included the following: the clean wing (both in an unbounded and in a wind tunnel wall bounded atmosphere), the wing with an external missile store mounted at the wing tip, and the wing with an external missile store mounted on a pylon at the lower surface of the wing. The flow mach number ranged from 0.6 to 1.35 in steady flow and from 0.6 to 0.95 in unsteady flow. Each steady flow case is analyzed at three angles of attack (0.5 deg, 0.0 deg, 0.5 deg) while each unsteady flow case consisted of unsteady pitch oscillation about zero angle of attack. The reduced frequency of the oscillation was in the range from 0.2498 to 0.3955. The computed results include chordwise pressure distributions along wing sections at eight spanwise locations from 18.1 to 97.7 per cent semispan. The results also include the coefficients of lift and pitching moment for each complete configuration as well as the coefficients of aerodynamic force and couple arising from the pressure on only the surface of the missile store.
Book Synopsis Static Force Tests of a Model of a Twin-jet Fighter Airplane for Angles of Attack from -100 to 1100 and Sideslip Angles from -400 to 400 by : Ernie L. Anglin
Download or read book Static Force Tests of a Model of a Twin-jet Fighter Airplane for Angles of Attack from -100 to 1100 and Sideslip Angles from -400 to 400 written by Ernie L. Anglin and published by . This book was released on 1971 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt: Static force tests of model of twin jet fighter aircraft at various angles of attack and sideslip angles to obtain data for theoretical spin studies.
