Welcome to Hegedus Aerodynamics.
The goal of Hegedus Aerodynamics is to provide quality software to the aeronautics community and to have fun and pride in the work that is done.
As a part of this effort, an aerodynamic analysis tool with a graphical user interface for aerodynamic analysis, called Aero Troll, is being developed and is freely available for download here. The goal of Aero Troll is to allow users to describe and carry out aerodynamic analysis on simplified geometries. The tool supports education, academic aerodynamic analysis, and verification and validation efforts. Please take a look and, if you would like, provide feedback.
Dec. 8th 2013: Version 0.3.0b of Aero Troll, which includes 2D CFD, has been made available on the software page.
Nov. 2013: I've added a Reynolds number case study for RANS CFD results of a series of 2D shapes.
June 2013: I've added RANS CFD results for a series of 2D flat plates.
June 2013: I've added some of my notes in regards to central finite difference RANS codes to the notes section of the examples page. These notes describe, to a certain extent, the upcoming release of Aero Troll with 2D CFD capability.
July 2012: I've added RANS CFD results for a decelerator to show an example of base drag.
Nov. 4th 2011: My notes on Pulliam and Chaussee's diagonal implicit approximate-factorization algorithm were added to the notes section on the example cases page.
Oct. 24th 2011: DPW4 example was uploaded to the example cases section.
Jan. 10th 2011: Vassberg NACA 0012 example was uploaded to the example cases section.
Dec. 14th 2010: Cone Shoulder example was uploaded to the CFD case studies section on the example cases page.
Sept. 8th 2009: Version 0.2.0b of Aero Troll has been released!
Listed below are the new additions and modifications for Version 0.2.0b of Aero Troll.
|1)||A PANAIR helper agent was added which displays the PANAIR abutments and performs rudimentary checks on them.|
|2)||Supersonic/Hypersonic local surface methods were added. The selection set of windward methods are: 1) modified Newtonian, 2) tangent-wedge, and 3) tangent-cone. The selection set of leeward methods are: 1) p infinity and 2) Prandtl-Meyer expansion. The impact methods are based on those described in the Mark IV Supersonic-Hypersonic Arbitrary-Body Computer Program (http://handle.dtic.mil/100.2/AD778444). The current local surface methods in Aero Troll do not take into account shielding.|
|3)||The following components were added:|
|4)||Circumferential segments were added to the Nose+Body component.|
|5)||Individual circumferential segments for Nose+Body and Body components can be deactivated.|
|6)||Body component was modified to allow for varying radial distribution. Currently, either a linear or circular arc (ogive) distribution can be selected.|
|7)||Sweep for fins can be specified by either the leading or trailing edge.|
|8)||The ability to copy, cut, and paste components has been added.|
|9)||The ability to hide components has been added.|
|10)||The ability to unset auto close has been added.|
|11)||The ability to clear all the components from the component tree by selecting a menu item from the component tree popup menu has been added.|
|12)||The ability to specify whether a wake will stick to a component has been added.|