Experimental investigation of the transonic shock-wave/boundary-layer interaction over a shock-generation bump
- Submitting institution
-
City, University of London
- Unit of assessment
- 12 - Engineering
- Output identifier
- 1319
- Type
- D - Journal article
- DOI
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10.1063/5.0018763
- Title of journal
- Physics of Fluids
- Article number
- 106102
- First page
- -
- Volume
- 32
- Issue
- 10
- ISSN
- 1070-6631
- Open access status
- Not compliant
- Month of publication
- October
- Year of publication
- 2020
- URL
-
-
- Supplementary information
-
-
- Request cross-referral to
- -
- Output has been delayed by COVID-19
- No
- COVID-19 affected output statement
- -
- Forensic science
- No
- Criminology
- No
- Interdisciplinary
- No
- Number of additional authors
-
2
- Research group(s)
-
-
- Proposed double-weighted
- No
- Reserve for an output with double weighting
- No
- Additional information
- Shock wave boundary layer interaction at transonic speed is an important cause of buffeting, limiting the speed in commercial aircraft flights. A new statistical schlieren method has been developed, which allows high resolution visualization of flow structures that are not immediately visible from the raw schlieren snapshot. With the publication the industry has now gained a robust tool to identify buffeting in wind-tunnel experiments in a low-cost, quick and easy-to-setup alternative, especially for expensive tests in cryogenic tunnels. This offers to reduce largely the testing costs for such investigations, which are essential in final tests for aircraft certification
- Author contribution statement
- -
- Non-English
- No
- English abstract
- -