Download or read book Computational Test Cases for a Rectangular Supercritical Wing Undergoing Pitching Oscillations written by Robert M. Bennett and published by . This book was released on 1999 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Computational Test Cases for a Rectangular Supercritical Wing Undergoing Pitching Oscillations written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-12 with total page 132 pages. Available in PDF, EPUB and Kindle. Book excerpt: Proposed computational test cases have been selected from the data set for a rectangular wing of panel aspect ratio two with a twelve-percent-thick supercritical airfoil section that was tested in the NASA Langley Transonic Dynamics Tunnel. The test cases include parametric variation of static angle of attack, pitching oscillation frequency, and Mach numbers from subsonic to transonic with strong shocks. Tables and plots of the measured pressures are presented for each case. This report provides an early release of test cases that have been proposed for a document that supplements the cases presented in AGARD Report 702. Bennett, Robert M. and Walker, Charlotte E. Langley Research Center RTOP 522-31-81-03
Download or read book Test Cases for a Rectangular Supercritical Wing Undergoing Pitching Oscillations written by Robert M. Bennett and published by . This book was released on 2000 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: Steady and unsteady measured pressures for a Rectangular Supercritical Wing (RSW) undergoing pitching oscillations have been presented in Ref I to 3. From the several hundred compiled data points, 27 static and 36 pitching oscillation cases have been proposed for computational Test Cases to illustrate the trends with Mach number, reduced frequency, and angle of attack. The wing was designed to be a simple configuration for Computational Fluid Dynamics (CFD) comparisons. The wing had an unswept rectangular planform plus a tip of revolution, a panel aspect ratio of 2.0, a twelve per cent thick supercritical airfoil section, and no twiSt The model was tested over a wide range of Mach numbers, from 0.27 to 0.90, corresponding to low subsonic flows up to strong transonic flows. The higher Mach numbers are well beyond the design Mach number such as might be required for flutter verification beyond cruise conditions. The pitching oscillations covered a broad range of reduced frequencies. Some early calculations for this wing are given for lifting pressure in Ref 3 and 4 as calculated from a linear lifting surface program and from a transonic small perturbation program. The unsteady results were given primarily for a mild transonic condition at M = 0.70. For these cases the agreement with the data was only fair, possibly resulting from the omission of viscous effects. Supercritical airfoil sections are known to be sensitive to viscous effects (for example, one case cited in Ref 4). Calculations using a higher level code with the full potential equations have been presented in Ref 5 for one of the same cases, and with the Euler equations in Ref 6. The agreement around the leading edge was improved, but overall the agreement was not completely satisfactory.
Download or read book NASA Langley Scientific and Technical Information Output 1999 written by and published by . This book was released on 2000 with total page 182 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book CEAS AIAA ICASE NASA Langley International Forum on Aeroelasticity and Structural Dynamics 1999 written by and published by . This book was released on 1999 with total page 460 pages. Available in PDF, EPUB and Kindle. Book excerpt: These proceedings represent a collection of the latest advances in aeroelasticity and structural dynamics from the world community. Research in the areas of unsteady aerodynamics and aeroelasticity, structural modeling and optimazation, active control and adaptive structures, landing dynamics, certification and qualification, and validation testing are highlighted in the collection of papers. The wide range of results will lead to advances in the prediction and control of the structural response of aircraft and spacecraft.
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Download or read book Aeronautical Engineering A Cumulative Index to a Continuing Bibliography supplement 248 written by and published by . This book was released on 1990 with total page 532 pages. Available in PDF, EPUB and Kindle. Book excerpt:
