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Author : Luckert. H.J.
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
Download or read book Lift Distribution on Swept - Back Wings in Yaw written by Luckert. H.J. and published by . This book was released on 1947 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Seymour Lampert
Publisher :
ISBN 13 :
Total Pages : 64 pages
Book Rating : 4.3/5 (91 download)
Download or read book Rolling and Yawing Moments for Swept-back Wings in Sideslip at Supersonic Sppeds written by Seymour Lampert and published by . This book was released on 1951 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method is presented for determining the rolling and yawing moments of swept-back wings in steady sideslip at supersonic speeds. The case treated in particular is that of a swept tapered wing with all edges subsonic.
Author : Robert T. Jones
Publisher :
ISBN 13 :
Total Pages : 708 pages
Book Rating : 4.F/5 ( download)
Download or read book The Spanwise Distribution of Lift for Minimum Induced Drag of Wings Having a Given Lift and a Given Bending Moment written by Robert T. Jones and published by . This book was released on 1950 with total page 708 pages. Available in PDF, EPUB and Kindle. Book excerpt: The problem of the minimum induced drag of wings having a given lift and a given span is extended to include cases in which the bending moment to be supported by the wing is also given. Expressions for the spanwise load distribution and the minimum drag in terms of the lateral position of the load centroid are given. The results show a 15-percent reduction of the induced drag with a 15-percent increase in span over that for an elliptic loading having the same total lift and bending moment.
Author : M. J. Queijo
Publisher :
ISBN 13 :
Total Pages : 54 pages
Book Rating : 4.3/5 (91 download)
Download or read book Theoretical Span Load Distributions and Rolling Moments for Sideslipping Wings of Arbitrary Plan Form in Incompressible Flow written by M. J. Queijo and published by . This book was released on 1955 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method of computing span loads and the resulting rolling moments for sideslipping wings of arbitrary plan form in incompressible flow is derived. The method requires that the span load at zero sideslip be known for the wing under consideration. Because this information is available for a variety of wings, this requirement should not seriously restrict the application of the present method. The basic method derived herein requires a mechanical differentiation and integration to obtain the rolling moment for the general wing in sideslip. For wings having straight leading and trailing edges over each semispan, the rolling moment equation in terms of plan-form parameters and the lateral center of pressure of the lift due to angle of attack. Calculated span loads and rolling-moment parameters are compared with experimental values. The comparison indicates good agreement between calculations and available experimental data.
Author : J. Weissinger
Publisher :
ISBN 13 :
Total Pages : 48 pages
Book Rating : 4.:/5 (862 download)
Download or read book The Lift Distribution of Swept-back Wings written by J. Weissinger and published by . This book was released on 1982 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Harvard Lomax
Publisher :
ISBN 13 :
Total Pages : 48 pages
Book Rating : 4.3/5 (91 download)
Download or read book Linearized Lifting-surface Theory for Swept-back Wings with Slender Plan Forms written by Harvard Lomax and published by . This book was released on 1949 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: The spanwise and chordwise distribution of loading, the lift, and the induced drag of a swept-back wing of slender plan form are developed by means of linearized lifting-surface theory. The results are applicable for all free-stream Mach numbers. The term slender implies that the ratio of the reduced span to over-all length of the wing is small.
Author : United States. Air Force. Air Matériel Command
Publisher :
ISBN 13 :
Total Pages : 40 pages
Book Rating : 4.:/5 (758 download)
Download or read book The Lift Distribution of Swept-back Wings written by United States. Air Force. Air Matériel Command and published by . This book was released on 1946 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two procedures for calculating the lift distribution along the span are given, in which better account is taken of the distribution of circulation over the area than in the Prandtl lifting-line theory. The methods are also applicable to wings with sweepback. Calculated results according to two methods agree excellently. Using the second, simpler method one needs about 3 hours for the calculation of the lift distribution of a straight wing, and about eight hours for this calculation for the swept-back wing. The results are compared with those of the Multhopp method and with experimental results. Finally there is a brief not on the swept-back wing in sideslip.
Author : Donald E. Hewes
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.3/5 (91 download)
Download or read book The Effects of Mass Distribution on the Low-speed Dynamic Lateral Stability and Control Characteristics of a Model with a 45° Sweptback Wing written by Donald E. Hewes and published by . This book was released on 1951 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: The trends in lateral stability and control produced variations of the mass distribution were determined for a model with a 45 degree sweptback wing. Calculations were made to correlate the trends determined by theory with those determined from tests of a free-flying dynamic model in the Langley free-flight tunnel.
Author : Karl Nickel
Publisher : Hodder Education
ISBN 13 :
Total Pages : 520 pages
Book Rating : 4.3/5 (91 download)
Download or read book Tailless Aircraft in Theory and Practice written by Karl Nickel and published by Hodder Education. This book was released on 1994 with total page 520 pages. Available in PDF, EPUB and Kindle. Book excerpt: Discusses the range of tailless designs, from hanggliders to the US 'Stealth Bomber', and includes a detailed look at particularly significant designs. The authors' own experience in this field allows them to explain and illustrate the topic in a way that appeal to the enthusiast and satisfies the professional aerodynamicist.
Author :
Publisher :
ISBN 13 :
Total Pages : 552 pages
Book Rating : 4.:/5 (28 download)
Download or read book Technical Memorandum written by and published by . This book was released on 1947 with total page 552 pages. Available in PDF, EPUB and Kindle. Book excerpt: Chiefly translations from foreign aeronautical journals.
Author : United States. National Advisory Committee for Aeronautics
Publisher :
ISBN 13 :
Total Pages : 1038 pages
Book Rating : 4.E/5 ( download)
Download or read book Technical Note - National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1956 with total page 1038 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 624 pages
Book Rating : 4.:/5 (31 download)
Download or read book Technical Note written by and published by . This book was released on 1949 with total page 624 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Eugene S. Love
Publisher :
ISBN 13 :
Total Pages : 702 pages
Book Rating : 4.F/5 ( download)
Download or read book Pressure Rise Associated with Shock-induced Boundary-layer Separation written by Eugene S. Love and published by . This book was released on 1955 with total page 702 pages. Available in PDF, EPUB and Kindle. Book excerpt: Some recent contributions to the problem of shock-induced separation of the boundary layer are examined, and additional analytical and experimental results are presented. The probable ranges of pressure rises and flow deflections associated with separation are indicated. Consideration is given to the effects of Mach number, adverse pressure gradient, and Reynolds number for laminar boundary layers and to the effects of Mach number, Reynolds number, and ratio of sepcific heats for turbulent boundary layers.
Author : Edward C. Polhamus
Publisher :
ISBN 13 :
Total Pages : 26 pages
Book Rating : 4.3/5 (91 download)
Download or read book A Simple Method of Estimating the Subsonic Lift and Damping in Roll of Sweptback Wings written by Edward C. Polhamus and published by . This book was released on 1949 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method of modifying existing correction factors of lifting-surface theory to account approximately for the effects of sweep has been derived, and these factors have been applied to existing lifting-line theories for the lift and damping in roll of swept wings. A comparison with experimental data in the low-speed and low lift range indicated good agreement for wings of any plan form. If the Glauert-Prandtl transformation is used, the formulas obtained can be applied to swept wings at subsonic speeds below the critical speed.
Author : A. E. Potter
Publisher :
ISBN 13 :
Total Pages : 358 pages
Book Rating : 4.3/5 (243 download)
Download or read book Theoretical and Experimental Investigation of the Effect of Tunnel Walls on the Forces on an Oscillating Airfoil in Two-dimensional Subsonic Compressible Flow written by A. E. Potter and published by . This book was released on 1956 with total page 358 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : S. Katzoff
Publisher :
ISBN 13 :
Total Pages : 670 pages
Book Rating : 4.F/5 ( download)
Download or read book Calculation of Tunnel-induced Upwash Velocities for Swept and Yawed Wings written by S. Katzoff and published by . This book was released on 1948 with total page 670 pages. Available in PDF, EPUB and Kindle. Book excerpt: The tunnel-induced upwash for a wing of any plan form and load distribution in a rectangular tunnel may be found with the aid of only two charts. One is given in the present paper. The second must be computed for each tunnel. The second chart is given for an open tunnel of 2:1 width-height ratio, a closed tunnel of 2:5 width-height ratio, and a closed tunnel of 10:7 width-height ratio.
Author : Doris Cohen
Publisher :
ISBN 13 :
Total Pages : 14 pages
Book Rating : 4.3/5 (126 download)
Download or read book Theoretical Distribution of Load Over a Swept-back Wing written by Doris Cohen and published by . This book was released on 1942 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: The load over an elliptical wing with 30 degrees sweepback has been calculated by a method, based on vortex theory, which takes account of the chordwise distribution of lifting area. The theory indicates a 14-percent loss in total lift due to the introduction of sweepback, with the greatest loss taking place at the center of the span. An increase in concentration of load at the tips is also indicated. The results are compared with the results previously obtained by somewhat simpler calculations based on the assumption of a single lifting vortex.
