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File xflr5.changes of Package xflr5
------------------------------------------------------------------- Sat Apr 18 12:30:00 UTC 2015 - techwinder@gmail.com - Update to version 6.10.04. * Corrected a potential crash bug when deleting a plane with polars * Added a standard ISA model for the calculation of air properties * Corrected the issues with the reference lengths after wing scaling * Fixed the bugs related to the import operation of a body definition from a text file * Fix for retina displays on OS X * Corrected the export of plane polars to text files to include the sideslip variable * Other minor corrections and improvements ------------------------------------------------------------------- Mon Mar 2 16:07:00 UTC 2015 - sfalken@opensuse.org - Changed Category in .desktop file to clear brp-check-suse failure ------------------------------------------------------------------- Sat Jun 28 14:39:59 UTC 2014 - dmitry_r@opensuse.org - Update to version 6.10.03. Changes sinse version 6.09: * Created a new binary .xfl projet file format. Replaces once and for all the awful .wpa format * Removed the option for independent wing analysis * Introducing type 5 polars for the analysis of variable sideslip * Disabled the horseshoe vortex method for stability polars, for beta-polars, and whenever sidelip is defined. * Aligned theviscous drag vector with freestream velocity rather than with x-axis - slight impact on viscous results * Enabled LLT analysis for all Plane objects * Removed the option for symmetry in 3d analysis * Corrected the bug in type 4 plane analysis-elevator and fin coefficients were incorrectly calculated * Removed the default sizing for panel and matrix arrays. The arrays are now allocated for the size of the largest model loaded in the session. * Corrected some memory leaks * Corrected memory allocation/release mismatches * MASSIVE code cleaning. * Created GUI-independant classes for 3D-panel analysis and LLT analysis * Minor corrections and enhancements ------------------------------------------------------------------- Wed Dec 26 08:15:10 UTC 2012 - dmitry_r@opensuse.org - Update to version 6.09 * see included ReleaseNotes.txt for details - spec file cleanup ------------------------------------------------------------------- Tue Jun 26 00:00:00 UTC 2012 - adeperrois@xflr5.com - xflr5 v6.07 * fixed type 2 batch polar analysis * fixed the issue with incorrect 3D-panel calculations * Corrected the incorrect aileron control derivatives * Corrected the bug in wing analysis with ground effect * Corrected the bug in type 4 analysis for wings and planes * Corrected the bug which modified the chord length as twist increases: impact results for wings with high dihedral * Cleaned, corrected, and improved the code for B-Splines * Removed the option for Min/Max type controls in Stabillity Polars * Added an option to edit Wing Polar paramaters * Fixed the crash bug when defining wings with more than 16 span sections * Corrected a bug leading to incorrect results in stability derivatives with active controls (CPanel::RotateBC()) * Removed the Splined Points Foil option * Other minor corrections and enhancements * Code cleaning ------------------------------------------------------------------- Fri Jan 06 00:00:00 UTC 2012 - adeperrois@xflr5.com - xflr5 v6.06 * Minor corrections and improvements ------------------------------------------------------------------- Sun Jul 24 00:00:00 UTC 2011 - adeperrois@xflr5.com - xflr5 v6.05 beta, July 15th, 2011 * For Type 7 polars, listed the control value instead of the aoa in the top drop down box * Added a calculation form to determine Re.sqrt(Cl) for foil Type 2 polars * Added the Japanese translation to the repository - thanks to Koichi * Minor corrections and improvements ------------------------------------------------------------------- Sun May 15 00:00:00 UTC 2011 - adeperrois@xflr5.com - xflr5 v6.04 beta, May 14th, 2011 * added a settings save at each project save * added and option to view forces on panels as coloured arrows * fixed the incorrect setting of AVL-type controls for flaps in T7 analysis * added the missing write operation in the project file of the control variable for wing operating points * modified the setting of boundary conditions in T7 analysis with activated controls - impact on balanced aoa * modified the wing construction process to allow for a gap in the middle of the wing * corrected the bug which caused the disapperance of the left stability toolbar when switching to 3D view * corrected the bug which prevented from changing the default number of panels in naca foil generation * continued the code cleaning process ------------------------------------------------------------------- Sun Feb 13 00:00:00 UTC 2011 - adeperrois@xflr5.com - XFLR5v6.03 beta rpm release * modified the geometry connection between panels with dihedral and twist - may slightly impact the results * corrected the calculations with sideslip * added multi-threading capability for foil batch analysis * added an option to display the position of point masses in 3d-view * in the export to AVL of point masses, corrected the missing addition of wing x & z position * modified the export format to AVL of with wing flaps * added an option to highlight the currently selected operating point, or the mode in root locs view * changed the interface for stability analysis * added a properties dialog box option for operating points * corrected various minor bugs * made several minor enhancements ------------------------------------------------------------------- Sun Dec 19 00:00:00 UTC 2010 - adeperrois@xflr5.com - XFLR5v6.02 beta rpm release * added an option to load a background image in the foil direct design module * corrected some errors in CoG and inertia automatic calculations, with impact on results * did some deep code cleaning * re-organized the panel analysis code to perform only one far field calculation per operating point * optimized the panel method for increased speed of execution * corrected the mesh edition for NURBS bodies * changed the export format for graphs * implemented the stability method for mixed panel/vlm method * implemented the stability method for full 3D panel method * corrected the bug which lead to incorrect results in 3D panel with Neumann B.C. * corrected the error in the jump in potential at the wing's trailing edage in full 3d panel method * set the estimation of inertia properties at the time of polar definition instead of evaluating at the time of analysis * fixed the bug which could cause a crash when dragging a point in splines design * corrected the asymetric transition location for symetric wings * corrected the source strength influence of thick panels on thin surfaces, with impact on results for planes with body * corrected the Cp 3D color display for VLM2 analysis * added the influence of pressure forces acting on the body to induced pitching moment coefficient * added calculation of neutral point position based on Cma/Cza ratio * corrected various minor bugs * made several minor enhancements ------------------------------------------------------------------- Thu Oct 14 00:00:00 UTC 2010 - adeperrois@xflr5.com - XFLR5v6.01 beta rpm release * Corrected the incorrect balance speed in 3D type 2 polars for planes * Corrected the final moment calculation in stability analysis * Corrected the incorrect lift calculation in stability analysis ------------------------------------------------------------------- Sat Sep 19 00:00:00 UTC 2010 - adeperrois@xflr5.com - XFLR5v6.00 beta rpm release ------------------------------------------------------------------- Fri Apr 3 00:00:00 UTC 2010 - adeperrois@xflr5.com - First rpm release
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