Hegedus Aerodynamics

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Hi. My name is Martin Hegedus. Welcome to my adventure. Welcome to Hegedus Aerodynamics.

In Feburary of 2008, after thirteen and a half years of employment, I left Nielsen Engineering and Research to pursue this adventure. Some of the reasons for this decision were to: 1) increase my ownership in the things I create, 2) further my professional development, and 3) have more say in investments.

The goal of Hegedus Aerodynamics is to provide quality service and products to the aeronautic and astronautic communities in regards to aerodynamic prediction and to have fun and pride in the work that is done.

Hegedus Aerodynamics is actively developing software to support the aerodynamic community. As a part of this effort, a graphical user interface for aerodynamic analysis, called Aero Troll, is being developed and is freely available for download here. Please take a look and, if you would like, provide feedback.

In addition, Hegedus Aerodynamics is seeking market data. If you can, please share your aerodynamic analysis, software, and consulting needs and insights to martin@hegedusaero.com. The information will be much appreciated.

News

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:
a)Wing. The Wing component allows for deflected leading and trailing edges and for changes in dihedral along the span. The current wing component does not model thickness or camber.
b)Box. One or more of the six Box component sides can be eliminated. The forward face of the box can be specified to PANAIR as a flow through face.
c)Panel. The Panel component allows the user to specify a surface by means of a quadrilateral or a python function.
d)Ground Plane. The Ground Plane component specifies the X-Y plane (Z=0) as a plane of symmetry for PANAIR. To correctly model a horizontal plane of symmetry, the PANAIR program must be patched with a patch obtainable from www.hegedusaero.com. Instructions for applying the patch are given below.
e)Field Pts. The Field Pts component allows the user to specify a rectangular grid of points at which the pressure in the field is calculated.
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.