MACSTAB Calculator

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F70883521%3A28140%2F16%3A43874390" target="_blank" >RIV/70883521:28140/16:43874390 - isvavai.cz</a>

Výsledek na webu

<a href="https://github.com/vogeltanz/MACSTAB-Calculator/releases/download/v0.6.0/MACSTAB.Calculator.zip" target="_blank" >https://github.com/vogeltanz/MACSTAB-Calculator/releases/download/v0.6.0/MACSTAB.Calculator.zip</a>

DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

MACSTAB Calculator

Popis výsledku v původním jazyce

MAC/STAB Calculator is an application for the calculation of the Mean Aerodynamic Chord (MAC) of an arbitrary wing planform and for the STABility estimation (in conceptual design) of a wing/tail aircraft configuration. The knowledge of the mean aerodynamic chord is necessary condition when stability estimation or CFD analysis should be performed. The stability calculation is based on the tail efficiency, the position of Center of Gravity and Neutral Point which are set by user, and also on MACs, areas, and aspect ratios of wing and tail. The appropriate stability is determined by the calculated distance between leading edges and also aerodynamic centers of wing and tail; however, there is always compromise between good maneuverability and high stability of an aircraft. One specialty of this application is option to analyze an image file and convert a wing planform or an airfoil to geometry parameters which then may be processed. This function can be useful in reverse engineering of an arbitrary wing. The whole geometry of wing and tail (including airfoils) may be exported to VSP2 format which can be opened using OpenVSP 2.3.0, or imported to OpenVSP }=3.5.0. Then, the exported wing and tail may be used in conceptual design of an aircraft, or may be analyzed, converted (to STL, MSH etc.), modified, and printed.

Název v anglickém jazyce

MACSTAB Calculator

Popis výsledku anglicky

MAC/STAB Calculator is an application for the calculation of the Mean Aerodynamic Chord (MAC) of an arbitrary wing planform and for the STABility estimation (in conceptual design) of a wing/tail aircraft configuration. The knowledge of the mean aerodynamic chord is necessary condition when stability estimation or CFD analysis should be performed. The stability calculation is based on the tail efficiency, the position of Center of Gravity and Neutral Point which are set by user, and also on MACs, areas, and aspect ratios of wing and tail. The appropriate stability is determined by the calculated distance between leading edges and also aerodynamic centers of wing and tail; however, there is always compromise between good maneuverability and high stability of an aircraft. One specialty of this application is option to analyze an image file and convert a wing planform or an airfoil to geometry parameters which then may be processed. This function can be useful in reverse engineering of an arbitrary wing. The whole geometry of wing and tail (including airfoils) may be exported to VSP2 format which can be opened using OpenVSP 2.3.0, or imported to OpenVSP }=3.5.0. Then, the exported wing and tail may be used in conceptual design of an aircraft, or may be analyzed, converted (to STL, MSH etc.), modified, and printed.

Druh

R - Software

CEP obor

IN - Informatika

OECD FORD obor

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Projekt

<a href="/cs/project/LO1303" target="_blank" >LO1303: Podpora udržitelnosti a rozvoje Centra bezpečnostních, informačních a pokročilých technologií (CEBIA-Tech)</a><br>

Návaznosti

P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)<br>S - Specificky vyzkum na vysokych skolach

Rok uplatnění

2016

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Interní identifikační kód produktu

R/FAI/ÚIUI/2016/MACSTABCalc

Technické parametry

Aplikace naprogramovaná v C++ s využitím knihovny wxWidgets pro operační systém Windows (verze pro Linux je také možná).

Ekonomické parametry

Snížení finančních nákladů na koncepční návrh a analýzu malého podzvukového letounu

IČO vlastníka výsledku

70883521

Název vlastníka

Univerzita Tomáše Bati ve Zlíně