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Estimation Of Leading Edge Thrust For Supersonic Wings Of Arbitrary Plabform
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Book Synopsis Theoretical Lift and Damping in Roll of Thin Sweptback Wings of Arbitrary Taper and Sweep at Supersonic Speeds by : Frank S. Malvestuto
Download or read book Theoretical Lift and Damping in Roll of Thin Sweptback Wings of Arbitrary Taper and Sweep at Supersonic Speeds written by Frank S. Malvestuto and published by . This book was released on 1949 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: Design curves are presented which permit rapid estimation of the lift-curve slope and damping-in-roll derivative for given values of aspect ratio, taper ratio, Mach number, and leading edge sweep.
Book Synopsis A Computer Program for Wing Subsonic Aerodynamic Performance Estimates Including Attainable Thrust and Vortex Lift Effects by : Harry W. Carlson
Download or read book A Computer Program for Wing Subsonic Aerodynamic Performance Estimates Including Attainable Thrust and Vortex Lift Effects written by Harry W. Carlson and published by . This book was released on 1982 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Calculation of Downwash Behind Supersonic Wings with an Application to Triangular Plan Forms by : Max A. Heaslet
Download or read book The Calculation of Downwash Behind Supersonic Wings with an Application to Triangular Plan Forms written by Max A. Heaslet and published by . This book was released on 1948 with total page 726 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method is developed, consistent with the assumptions of small perturbation theory, which provides a means of determining for a known load distribution, the downwash behind a wing in supersonic flow. THe analysis is based upon the use of supersonic doublets which are distributed over the plan form and wake of the wing in a manner determined from the wing loading.
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722485009 Total Pages :66 pages Book Rating :4.4/5 (85 download)
Book Synopsis Improved Method for Prediction of Attainable Wing Leading-Edge Thrust by : National Aeronautics and Space Administration (NASA)
Download or read book Improved Method for Prediction of Attainable Wing Leading-Edge Thrust written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-08 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: Prediction of the loss of wing leading-edge thrust and the accompanying increase in drag due to lift, when flow is not completely attached, presents a difficult but commonly encountered problem. A method (called the previous method) for the prediction of attainable leading-edge thrust and the resultant effect on airplane aerodynamic performance has been in use for more than a decade. Recently, the method has been revised to enhance its applicability to current airplane design and evaluation problems. The improved method (called the present method) provides for a greater range of airfoil shapes from very sharp to very blunt leading edges. It is also based on a wider range of Reynolds numbers than was available for the previous method. The present method, when employed in computer codes for aerodynamic analysis, generally results in improved correlation with experimental wing-body axial-force data and provides reasonable estimates of the measured drag. Carlson, Harry W. and McElroy, Marcus O. and Lessard, Wendy B. and McCullers, L. Arnold Langley Research Center...
Book Synopsis Characteristics of Thin Triangular Wings with Triangular-tip Control Surfaces at Supersonic Speeds with Mach Lines Behind the Leading Edge by : Warren A. Tucker
Download or read book Characteristics of Thin Triangular Wings with Triangular-tip Control Surfaces at Supersonic Speeds with Mach Lines Behind the Leading Edge written by Warren A. Tucker and published by . This book was released on 1948 with total page 738 pages. Available in PDF, EPUB and Kindle. Book excerpt: A theoretical analysis, based on the linearized equation for supersonic flow, of characteristics of triangular-tip control surfaces on thin triangular wings. By restriction to case for which Mach lines from wing apex lie behind the leading edge, a simplified treatment was possible; results of previous work on lift of triangular wings could be used to derive expressions for lift effectiveness, pitching moment, rolling-moment effectiveness, hinge moment due to control deflection, and hinge moment due to angle of attack. Comparisons were made with two-dimensional case.
Book Synopsis Theoretical Loading at Supersonic Speeds of Flat Swept-back Wings with Interacting Trailing and Leading Edges by : Doris Cohen
Download or read book Theoretical Loading at Supersonic Speeds of Flat Swept-back Wings with Interacting Trailing and Leading Edges written by Doris Cohen and published by . This book was released on 1949 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: By the method of superposition of conical flows, the load distribution is calculated for regions of a long swept-back wing behind the points at which the Mach lines from the trailing-edge apex intersect the leading edge. It is found that a good approximation on the load can be obtained by the application of a fairly simple correction factor to the two-dimensional subsonic distribution. The similarity of two-dimensional flow is used to derive expressions for the loss of lift behind the Mach lines from the tips of the wing.
Book Synopsis Wing Theory in Supersonic Flow by : Elie Carafoli
Download or read book Wing Theory in Supersonic Flow written by Elie Carafoli and published by Elsevier. This book was released on 2013-10-22 with total page 611 pages. Available in PDF, EPUB and Kindle. Book excerpt: Division II: Aerodynamics, Volume 7: Wing Theory in Supersonic Flow examines the cases of isolated simple wings, wings with vertical plane tail, cruciform wings, and simple or cruciform wings fitted with a body. This book presents the method for the actual calculation of isolated wings or of more complex system. Organized into 12 chapters, this volume starts with an overview of the basic equations in the mechanics of inviscid fluids. This text then presents a unified theory that is established for angularly shaped wings in supersonic flow. Other chapters consider the method for calculating the characteristics of drag, lift, and moments for various shapes of the trailing edge line. This book discusses as well the wings of ordinary shapes, delta wings, yawed wings, polygonal wings, trapezoid wings, and arrow-head or swept-back wings. The final chapter deals with a delta wing with a central fusiform body. This book is a valuable resource for teachers, students, and specialists engaged in modern aerodynamics.
Book Synopsis Supersonic Lift and Pitching Moment of Thin Sweptback Tapered Wings Produced by Constant Vertical Acceleration by :
Download or read book Supersonic Lift and Pitching Moment of Thin Sweptback Tapered Wings Produced by Constant Vertical Acceleration written by and published by . This book was released on 1951 with total page 47 pages. Available in PDF, EPUB and Kindle. Book excerpt: Theoretical approximations to the nondimensional lift and pitching moment produced by constant vertical acceleration, the CL(alpha) and CM(alpha) derivatives, respectively, are derived for a series of thin sweptback tapered wings with streamwise tips. The analysis is essentially the application of a recently published solution of the linearized time-dependent wave equation for wings in accelerated motion. The results are independent of camber and thickness and are applicable for a range of supersonic speed for which the wing is wholly contained between the Mach cones springing from the wing apex and from the trailing edge of the root section (subsonic leading edge and supersonic trailing edge). Design curves are presented which permit rapid estimation of the derivatives CL(alpha) and CM(alpha) for given values of aspect ratio, taper ratio, Mach number, and leading-edge sweep.
Book Synopsis Time-dependent Air Forces on Wings with Supersonic Leading and Trailing Edges and Subsonic Side Edges with Application to a Wing Deforming Harmonically According to a General Polynomial Equation by : Joseph A. Drischler
Download or read book Time-dependent Air Forces on Wings with Supersonic Leading and Trailing Edges and Subsonic Side Edges with Application to a Wing Deforming Harmonically According to a General Polynomial Equation written by Joseph A. Drischler and published by . This book was released on 1962 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of wing leading-edge radius and Reynolds number on longitudinal aerodynamic characteristics of highly swept wing-body configurations at subsonic speeds by : William P. Henderson
Download or read book Effects of wing leading-edge radius and Reynolds number on longitudinal aerodynamic characteristics of highly swept wing-body configurations at subsonic speeds written by William P. Henderson and published by . This book was released on 1976 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781720460107 Total Pages :52 pages Book Rating :4.4/5 (61 download)
Book Synopsis Design of Supersonic Transport Flap Systems for Thrust Recovery at Subsonic Speeds by : National Aeronautics and Space Administration (NASA)
Download or read book Design of Supersonic Transport Flap Systems for Thrust Recovery at Subsonic Speeds written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-29 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: A study of the subsonic aerodynamics of hinged flap systems for supersonic cruise commercial aircraft has been conducted using linear attached-flow theory that has been modified to include an estimate of attainable leading edge thrust and an approximate representation of vortex forces. Comparisons of theoretical predictions with experimental results show that the theory gives a reasonably good and generally conservative estimate of the performance of an efficient flap system and provides a good estimate of the leading and trailing-edge deflection angles necessary for optimum performance. A substantial reduction in the area of the inboard region of the leading edge flap has only a minor effect on the performance and the optimum deflection angles. Changes in the size of the outboard leading-edge flap show that performance is greatest when this flap has a chord equal to approximately 30 percent of the wing chord. A study was also made of the performance of various combinations of individual leading and trailing-edge flaps, and the results show that aerodynamic efficiencies as high as 85 percent of full suction are predicted.Mann, Michael J. and Carlson, Harry W. and Domack, Christopher S.Langley Research CenterSUBSONIC SPEED; SUPERSONIC TRANSPORTS; DESIGN ANALYSIS; FLAPPING; AERODYNAMIC CONFIGURATIONS; LEADING EDGE FLAPS; TRAILING EDGE FLAPS; PITCHING MOMENTS; LEADING EDGE THRUST; VORTICES; DEFLECTION
Book Synopsis Validation of a Computer Code for Analysis of Subsonic Aerodynamic Performance of Wings with Flaps in Combination with a Canard Or Horizontal Tail and an Application to Optimization by : Harry W. Carlson
Download or read book Validation of a Computer Code for Analysis of Subsonic Aerodynamic Performance of Wings with Flaps in Combination with a Canard Or Horizontal Tail and an Application to Optimization written by Harry W. Carlson and published by . This book was released on 1990 with total page 132 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Influence of Airfoil Geometry on Delta Wing Leading-edge Vortices and Vortex-induced Aerodynamics at Supersonic Speeds by : Richard M. Wood
Download or read book Influence of Airfoil Geometry on Delta Wing Leading-edge Vortices and Vortex-induced Aerodynamics at Supersonic Speeds written by Richard M. Wood and published by . This book was released on 1992 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigations at Supersonic Speeds of 22 Triangular Wings Representing Two Airfoil Sections for Each of 11 Apex Angles by : Eugene S. Love
Download or read book Investigations at Supersonic Speeds of 22 Triangular Wings Representing Two Airfoil Sections for Each of 11 Apex Angles written by Eugene S. Love and published by . This book was released on 1949 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of tests of 11 triangular wings were conducted at Mach numbers 1.62, 1.92, and 2.40 to determine the effect of leading-edge shape and to compare actual test values with the nonviscous linear theory. The two series of wings had identical plan forms, a constant thickness ratio of 8 percent, a constant location of maximum-thickness point of 18 percent, and a range of apex half-angles from 10 to 45 degrees. The first series had an elliptical leading edge and the second series, a wedge leading edge. Measurements were made of lift, drag, pitching moment, and pressure distribution, the latter being confined to three wings at one Mach number.
Book Synopsis Supersonic Lift and Pitching Moment of Thin Sweptback Tapered Wings Produced by Constant Vertical Acceleration by : Frank S. Malvestuto
Download or read book Supersonic Lift and Pitching Moment of Thin Sweptback Tapered Wings Produced by Constant Vertical Acceleration written by Frank S. Malvestuto and published by . This book was released on 1951 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: Design curves are presented which permit rapid estimations of lift and pitching moment for given values of aspect ratio, taper ratio, Mach number, and leading-edge sweep.
Book Synopsis Investigations at Supersonic Speeds of 22 Triangular Wings Representing Two Airfoil Sections for Each of 11 Apex Angles by : Eugene S. Love
Download or read book Investigations at Supersonic Speeds of 22 Triangular Wings Representing Two Airfoil Sections for Each of 11 Apex Angles written by Eugene S. Love and published by . This book was released on 1951 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis On the Hypersonic Flow Over a Delta Wing with Very Supersonic Leading Edges by : Norman D. Malmuth
Download or read book On the Hypersonic Flow Over a Delta Wing with Very Supersonic Leading Edges written by Norman D. Malmuth and published by . This book was released on 1965 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
