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Test Section Design for Measuring the Drag Coefficient of a Suborbital Rocket Model at Ma 2.45 Cover

Test Section Design for Measuring the Drag Coefficient of a Suborbital Rocket Model at Ma 2.45

Transactions on Aerospace Research
Volume 2024 (2024): Issue 3 (September 2024)
By: Filip Wasilczuk,  Marcin Kurowski and  Paweł Flaszyński  
Open Access
|Sep 2024
Figures & tables

Figures & Tables

Fig. 1.

Grid used for numerical simulations. The boundary conditions are presented.

Fig. 2.

The sketch of the original and modified support, including the cross-section.

Fig. 3.

Mach contour plot for configurations with original support (a) and thin support (b) – side view.

Fig. 4.

Mach number contour downstream of the support. Cross-section at half of the support span.

Fig. 5.

Density gradient magnitude for the model with original length – top view.

Fig. 6.

Pressure at top and bottom walls, measurements (EXP) and simulations (CFD).

Fig. 7.

Schlieren visualization for configuration “Nose 2”. Red lines are the iso-surface of the density gradient magnitude of 5 kg/m4.

Fig. 8.

Drag coefficient for three nose configurations.
DOI: https://doi.org/10.2478/tar-2024-0018 | Journal eISSN: 2545-2835
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Language: English
Page range: 86 - 100
Submitted on: May 20, 2024
Accepted on: Jul 12, 2024
Published on: Sep 11, 2024
Published by: ŁUKASIEWICZ RESEARCH NETWORK – INSTITUTE OF AVIATION
In partnership with: Paradigm Publishing Services
Publication frequency: 4 issues per year
Keywords:
suborbital rocket,
wind tunnel tests,
aerospace,
drag measurements,
supersonic speed
Related subjects:
Engineering,
Introductions and overviews,
Engineering, other,
Geosciences,
Geosciences, other,
Materials sciences,
Materials sciences, other,
Physics,
Physics, other

© 2024 Filip Wasilczuk, Marcin Kurowski, Paweł Flaszyński, published by ŁUKASIEWICZ RESEARCH NETWORK – INSTITUTE OF AVIATION
This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 License.

Volume 2024 (2024): Issue 3 (September 2024)
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