Aerodynamic Characteristics Analysis of Transonic Wing Flow Around Space Shuttle

Xuanning Wang

doi:10.54254/2755-2721/2026.KA27405

Applied and Computational EngineeringOpen access

Aerodynamic Characteristics Analysis of Transonic Wing Flow Around Space Shuttle

Research Article

Open Access

Aerodynamic Characteristics Analysis of Transonic Wing Flow Around Space Shuttle

Xuanning Wang ^1*

¹ Beijing Huiwen Middle School

^*Corresponding author: simonwangsalmonfish@gmail.com

Published on 2 October 2025

ACE Vol.188

ISSN (Print): 2755-273X

ISSN (Online): 2755-2721

ISBN (Print): 978-1-80590-397-0

ISBN (Online): 978-1-80590-398-7

Download Cover

Abstract

The Space Shuttle orbiter, a pioneering reusable spacecraft, navigated complex aerodynamic challenges during atmospheric re-entry. This paper investigates the aerodynamic behavior of transonic flow around its delta-wing design, focusing on shock-induced separation, vortex formation, and unsteady aerodynamic effects during descent and landing phases. Utilizing computational fluid dynamics (CFD) methods, including Euler and Navier–Stokes equations with zonal grid techniques, alongside experimental wind-tunnel campaigns, the study evaluates lift, drag, pressure distribution, and stability derivatives across Mach numbers from 0.8 to 1.2. Key findings highlight the significant influence of wing–body aerodynamic coupling on flutter speed and control surface effectiveness. By integrating numerical predictions with empirical data, the analysis validates existing models and provides insights into practical implications for future aerospace vehicle design. The results offer engineers critical guidance for optimizing designs and mitigating aeroelastic risks, particularly in reentry and subsonic-to-transonic transition scenarios.

Keywords:

CFD simulations, space shuttle, wind-tunnel validation

View PDF

References

[1]. Ellison, J. C. (1975). Transonic aerodynamic characteristics of a space shuttle orbiter (NASA TM X-2862). NASA.

[2]. Rainey, R. W., Ware, G. M., Powell, R. W., Brown, L. W., & Stone, D. R. (1972). Grumman H-33 space shuttle orbiter aerodynamic and handling qualities investigation (NASA-CR-112196). NASA.

[3]. Chyu, W. J., Cavin, R. K., & Erickson, L. L. (1978). Static and dynamic stability analysis of the space shuttle vehicle-orbiter (NASA-TP-1179). NASA.

[4]. Malmuth, N. D., Wu, C. C., & Cole, J. D. (1985). Slender body theory and Space Shuttle transonic aerodynamics (NASA-CR-172405). NASA.

[5]. Freeman, D. C., Jr. (1980). Dynamic stability derivatives of space shuttle orbiter obtained from wind-tunnel and approach and landing flight tests (NASA-TP-1604). NASA.

[6]. McClure, W. B. (1992). An experimental study of the driving mechanism and control of the unsteady shock-induced turbulent separation in a Mach 5 compression corner flow (Doctoral dissertation). University of Texas at Austin.

[7]. (N.A.) (2020). Preliminary aerodynamic design of a reusable booster flight demonstrator. CEAS Space Journal, 12(3), 215–229.

References

[1]. Ellison, J. C. (1975). Transonic aerodynamic characteristics of a space shuttle orbiter (NASA TM X-2862). NASA.

[2]. Rainey, R. W., Ware, G. M., Powell, R. W., Brown, L. W., & Stone, D. R. (1972). Grumman H-33 space shuttle orbiter aerodynamic and handling qualities investigation (NASA-CR-112196). NASA.

[3]. Chyu, W. J., Cavin, R. K., & Erickson, L. L. (1978). Static and dynamic stability analysis of the space shuttle vehicle-orbiter (NASA-TP-1179). NASA.

[4]. Malmuth, N. D., Wu, C. C., & Cole, J. D. (1985). Slender body theory and Space Shuttle transonic aerodynamics (NASA-CR-172405). NASA.

[5]. Freeman, D. C., Jr. (1980). Dynamic stability derivatives of space shuttle orbiter obtained from wind-tunnel and approach and landing flight tests (NASA-TP-1604). NASA.

[7]. (N.A.) (2020). Preliminary aerodynamic design of a reusable booster flight demonstrator. CEAS Space Journal, 12(3), 215–229.

Cite this article

Wang,X. (2025). Aerodynamic Characteristics Analysis of Transonic Wing Flow Around Space Shuttle. Applied and Computational Engineering,188,1-5.

Data availability

The datasets used and/or analyzed during the current study will be available from the authors upon reasonable request.

About volume

Volume title: Proceedings of CONF-MCEE 2026 Symposium: Advances in Sustainable Aviation and Aerospace Vehicle Automation

ISBN: 978-1-80590-397-0(Print) / 978-1-80590-398-7(Online)

Editor: Ömer Burak İSTANBULLU

Conference website: https://2025.confmcee.org/kayseri.html

Conference date: 14 November 2025

Series: Applied and Computational Engineering

Volume number: Vol.188

ISSN: 2755-2721(Print) / 2755-273X(Online)

© 2024 by the author(s). Licensee EWA Publishing, Oxford, UK. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY) license. Authors who publish this series agree to the following terms:

1. Authors retain copyright and grant the series right of first publication with the work simultaneously licensed under a Creative Commons Attribution License that allows others to share the work with an acknowledgment of the work's authorship and initial publication in this series.

2. Authors are able to enter into separate, additional contractual arrangements for the non-exclusive distribution of the series's published version of the work (e.g., post it to an institutional repository or publish it in a book), with an acknowledgment of its initial publication in this series.

3. Authors are permitted and encouraged to post their work online (e.g., in institutional repositories or on their website) prior to and during the submission process, as it can lead to productive exchanges, as well as earlier and greater citation of published work (See Open access policy for details).