Analysis of Unsteady Transonic Flow Fields by Means of the Colour Streak Schlieren Method

This article deals with a new approach to the investigation of unsteady transonic flow fields around aerodynamic models and in blade cascades using a schlieren method of flow visualisation. The principle and the application of the Colour Streak Schlieren Method (CSSM) are defined. The characteristic...

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Main Author: J. Ulrych
Format: Article
Language:English
Published: CTU Central Library 2004-01-01
Series:Acta Polytechnica
Subjects:
Online Access:https://ojs.cvut.cz/ojs/index.php/ap/article/view/560
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author J. Ulrych
author_facet J. Ulrych
author_sort J. Ulrych
collection DOAJ
description This article deals with a new approach to the investigation of unsteady transonic flow fields around aerodynamic models and in blade cascades using a schlieren method of flow visualisation. The principle and the application of the Colour Streak Schlieren Method (CSSM) are defined. The characteristic flow field features were observed and analysed around an oscillating NACA 0012 airfoil under the conditions of transonic free stream Mach number (<em>M</em><em>∞ = 0.9</em><em></em>), initial angle of attack (α = +4 deg), one amplitude of oscillation (Δα=±3 deg), and three frequencies of model oscillation (f = 1, 15, 30 Hz). There is a description of the terminal shock wave hysteresis across the investigated area, which was revealed in particular cases. Application possibilities of CSSM and its further development are discussed.
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spelling doaj.art-efec0b8e57b74629b375fafc223dcb312022-12-22T00:42:02ZengCTU Central LibraryActa Polytechnica1210-27091805-23632004-01-01443560Analysis of Unsteady Transonic Flow Fields by Means of the Colour Streak Schlieren MethodJ. UlrychThis article deals with a new approach to the investigation of unsteady transonic flow fields around aerodynamic models and in blade cascades using a schlieren method of flow visualisation. The principle and the application of the Colour Streak Schlieren Method (CSSM) are defined. The characteristic flow field features were observed and analysed around an oscillating NACA 0012 airfoil under the conditions of transonic free stream Mach number (<em>M</em><em>∞ = 0.9</em><em></em>), initial angle of attack (α = +4 deg), one amplitude of oscillation (Δα=±3 deg), and three frequencies of model oscillation (f = 1, 15, 30 Hz). There is a description of the terminal shock wave hysteresis across the investigated area, which was revealed in particular cases. Application possibilities of CSSM and its further development are discussed.https://ojs.cvut.cz/ojs/index.php/ap/article/view/560High-speed aerodynamicsexperimentflow field analysistransonic flow fieldsflow visualisationColour Streak Schlieren Method
spellingShingle J. Ulrych
Analysis of Unsteady Transonic Flow Fields by Means of the Colour Streak Schlieren Method
Acta Polytechnica
High-speed aerodynamics
experiment
flow field analysis
transonic flow fields
flow visualisation
Colour Streak Schlieren Method
title Analysis of Unsteady Transonic Flow Fields by Means of the Colour Streak Schlieren Method
title_full Analysis of Unsteady Transonic Flow Fields by Means of the Colour Streak Schlieren Method
title_fullStr Analysis of Unsteady Transonic Flow Fields by Means of the Colour Streak Schlieren Method
title_full_unstemmed Analysis of Unsteady Transonic Flow Fields by Means of the Colour Streak Schlieren Method
title_short Analysis of Unsteady Transonic Flow Fields by Means of the Colour Streak Schlieren Method
title_sort analysis of unsteady transonic flow fields by means of the colour streak schlieren method
topic High-speed aerodynamics
experiment
flow field analysis
transonic flow fields
flow visualisation
Colour Streak Schlieren Method
url https://ojs.cvut.cz/ojs/index.php/ap/article/view/560
work_keys_str_mv AT julrych analysisofunsteadytransonicflowfieldsbymeansofthecolourstreakschlierenmethod