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Book Estimation of Leading edge Thrust for Supersonic Wings of Arbitrary Planform

Download or read book Estimation of Leading edge Thrust for Supersonic Wings of Arbitrary Planform written by Harry W. Carlson and published by . This book was released on 1978 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Numerical Methods and a Computer Program for Subsonic and Supersonic Aerodynamic Design and Analysis of Wings with Attainable Thrust Considerations

Download or read book Numerical Methods and a Computer Program for Subsonic and Supersonic Aerodynamic Design and Analysis of Wings with Attainable Thrust Considerations written by and published by . This book was released on 1984 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Estimation of Leading edge Thrust for Supersonic Wings of Arbitrary Plabform

Download or read book Estimation of Leading edge Thrust for Supersonic Wings of Arbitrary Plabform written by Harry W. Carlson and published by . This book was released on 1978 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Improved Method for Prediction of Attainable Wing Leading Edge Thrust

Download or read book Improved Method for Prediction of Attainable Wing Leading Edge Thrust written by Harry W. Carlson and published by . This book was released on 1996 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book The Calculation of Downwash Behind Supersonic Wings with an Application to Triangular Plan Forms

Download or read book The Calculation of Downwash Behind Supersonic Wings with an Application to Triangular Plan Forms written by Maxwell Alfred Heaslet and published by . This book was released on 1948 with total page 52 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.

Book Survey and Analysis of Research on Supersonic Drag due to lift Minimization with Recommendations for Wing Design

Download or read book Survey and Analysis of Research on Supersonic Drag due to lift Minimization with Recommendations for Wing Design written by Harry W. Carlson and published by . This book was released on 1992 with total page 164 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Estimation of Wing Nonlinear Aerodynamic Characteristics at Supersonic Speeds

Download or read book Estimation of Wing Nonlinear Aerodynamic Characteristics at Supersonic Speeds written by and published by . This book was released on 1980 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book A Computer Program for Wing Subsonic Aerodynamic Performance Estimates Including Attainable Thrust and Vortex Lift Effects

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 Theoretical Loading at Supersonic Speeds of Flat Swept back Wings with Interacting Trailing and Leading Edges

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 Preliminary Investigation at Supersonic Speeds of Triangular and Sweptback Wings

Download or read book Preliminary Investigation at Supersonic Speeds of Triangular and Sweptback Wings written by Macon C. Ellis and published by . This book was released on 1949 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results from a supersonic wind-tunnel investigation of a series of thin triangular and sweptback wings are presented. The triangular wing series consisted of eight triangular wings of vertex angles such that a range of leading-edge postions both inside and outside the Mach cone at the test Mach numbers of 1.43 and 1.71 was obtained. The three swept wings had angles of sweep at 45, 55, and 63 degrees and were tested at a Mach number of 1.43.

Book Improved Method for Prediction of Attainable Wing Leading Edge Thrust

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...