A moving shock. A changing load. One connected flow problem.
01 / THE QUESTION
How can shock motion and separated flow be related to the time-dependent aerodynamic response of a supercritical airfoil?
02 / THE APPROACH
The ONERA OAT15A investigation uses time-resolved simulation and post-processing to examine pressure distributions, shock position and aerodynamic loads. Mesh comparisons and available experimental pressure data provide context for assessing the numerical behaviour.
- Pressure distributions
- Shock–load correlation
- Phase-resolved analysis
- Spectral and modal diagnostics
03 / ENGINEERING INSIGHT
Cycle-resolved analysis brings shock motion, separation and load response into a common view.
RELEVANCE TO YOUR PROJECT
Assess unsteady aerodynamic loads
For a design affected by moving shocks or separated flow, mean lift and drag alone may not describe the loading. This research demonstrates how time-resolved pressures, shock position and force histories can be examined together.
- Compare pressure fluctuations and aerodynamic loads across selected operating conditions.
- Identify the frequencies and flow regions that deserve closer investigation.
- Assess what further numerical checks or measurements are needed before a design decision.
A project can be scoped around pressure distributions, force histories, dominant frequencies and comparisons between agreed configurations.
Part of the scientific work informing our R&D programme. Explore our research programme
STUDY SCOPE
An ongoing URANS investigation of the ONERA OAT15A airfoil. Cross-code comparison and further numerical sensitivity checks remain part of the study.