Post-doctoral offer
Full-time
PhD
Between 0 and 2 years
Post-doctoral research assistant
14/02/2027
JOB DESCRIPTION:
Ultra-short and thin nacelles are a well-known solution to compensate the weight and drag penalties related to an increased fan diameter. In particular, the reduced wet surface of a short nacelle reduces friction drag at cruise. However, short nacelles are subject to flow separation in off-design conditions (especially take-off), which creates distortion and severely penalizes the fan efficiency. Peters et al. [[1]] have shown that inlets with a length-to-diameter ratio L/D below 0.25 are not robust without the use of an additional feature such as variable-geometry. In this context, we have proposed a slotted-inlet variable geometry concept as a potential enabler for nacelles with length-to-diameter ratios lower than 0.25. Through RANS numerical simulations, we showed that the slotted inlet could alleviate flow separation observed under incidence conditions on a very short L/D=0.19 nacelle. We also observed that there could be a potential for passive actuation since the steep flow turning around the nacelle lips that led to flow separation also causes forward-pulling forces on the slot.
In order to simulate the strong fan-inlet interactions and the fan performance under distortion, we propose to model the fan stages by using a body force approach. This principle, not new in turbomachinery, has been used to deal with short nacelles [[2]], cross-wind conditions [[3]] or aero-propulsive coupling [[4]]. Although this method cannot give access to the whole phenomenology of the flow inside the thrusters, it is able to capture first order phenomena with lower computational cost, compatible with preliminary design.
[1] Andreas Peters, Zoltán S Spakovszky, Wesley K Lord, and Becky Rose. Ultrashort nacelles for low fan pressure ratio propulsors. Journal of Turbomachinery, 137(2):021001, 2015.
[2] Thollet, W. Body Force Modeling of Fan—Airframe Interactions. Diss. Ph. D. thesis, ISAE-SUPAERO, 2017.
[3] Minaker, Quentin J., and Jeffrey J. Defoe. “Prediction of Crosswind Separation Velocity for Fan and Nacelle Systems Using Body Force Models: Part 1: Fan Body Force Model Generation without Detailed Stage Geometry.” International Journal of Turbomachinery, Propulsion and Power 4.4 (2019): 43.
[4] Benichou, Emmanuel, et al. “Numerical Low-Fidelity Method for Improved Analysis of Breakthrough Aero-Propulsive Systems .” 1st Aerospace Europe Conference, 2020.
MISSIONS:
The proposed work will pursue ongoing efforts to develop an adaptive nacelle design framework, using in-house Python scripts for geometry generation, body-force modelling, and the commercial StarCCM+ solver. The objective is to confirm the potential of the slotted-inlet concept by designing a nacelle for a new, given fan design, implementing the slot geometry, setting up body-force modelling of different fan designs, and performing numerical simulations on different off-design conditions including take-off, incidence, cross-wind. We will investigate means to refine the geometry through aerodynamic analysis and shape optimization, and assess actuation requirements in different scenarios (opening/closing the slot in different conditions). We will also explore scaling effects and define requirements for future wind tunnel or flight tests.
Design and Off-Design Analysis of a Semi-Embedded Distributed-Propulsion Nacelle Concept
N/A
Post-doctoral offer
Full-time
PhD
Between 0 and 2 years
Post-doctoral research assistant
14/02/2027
Job description
Ultra-short and thin nacelles are a well-known solution to compensate the weight and drag penalties related to an increased fan diameter. In particular, the reduced wet surface of a short nacelle reduces friction drag at cruise. However, short nacelles are subject to flow separation in off-design conditions (especially take-off), which creates distortion and severely penalizes the fan efficiency. Peters et al. [[1]] have shown that inlets with a length-to-diameter ratio L/D below 0.25 are not robust without the use of an additional feature such as variable-geometry. In this context, we have proposed a slotted-inlet variable geometry concept as a potential enabler for nacelles with length-to-diameter ratios lower than 0.25. Through RANS numerical simulations, we showed that the slotted inlet could alleviate flow separation observed under incidence conditions on a very short L/D=0.19 nacelle. We also observed that there could be a potential for passive actuation since the steep flow turning around the nacelle lips that led to flow separation also causes forward-pulling forces on the slot.
In order to simulate the strong fan-inlet interactions and the fan performance under distortion, we propose to model the fan stages by using a body force approach. This principle, not new in turbomachinery, has been used to deal with short nacelles [[2]], cross-wind conditions [[3]] or aero-propulsive coupling [[4]]. Although this method cannot give access to the whole phenomenology of the flow inside the thrusters, it is able to capture first order phenomena with lower computational cost, compatible with preliminary design
[1] Andreas Peters, Zoltán S Spakovszky, Wesley K Lord, and Becky Rose. Ultrashort nacelles for low fan pressure ratio propulsors. Journal of Turbomachinery, 137(2):021001, 2015.
[2] Thollet, W. Body Force Modeling of Fan—Airframe Interactions. Diss. Ph. D. thesis, ISAE-SUPAERO, 2017.
[3] Minaker, Quentin J., and Jeffrey J. Defoe. “Prediction of Crosswind Separation Velocity for Fan and Nacelle Systems Using Body Force Models: Part 1: Fan Body Force Model Generation without Detailed Stage Geometry.” International Journal of Turbomachinery, Propulsion and Power 4.4 (2019): 43.
[4] Benichou, Emmanuel, et al. “Numerical Low-Fidelity Method for Improved Analysis of Breakthrough Aero-Propulsive Systems .” 1st Aerospace Europe Conference, 2020.
Mission
The proposed work will pursue ongoing efforts to develop an adaptive nacelle design framework, using in-house Python scripts for geometry generation, body-force modelling, and the commercial StarCCM+ solver. The objective is to confirm the potential of the slotted-inlet concept by designing a nacelle for a new, given fan design, implementing the slot geometry, setting up body-force modelling of different fan designs, and performing numerical simulations on different off-design conditions including take-off, incidence, cross-wind. We will investigate means to refine the geometry through aerodynamic analysis and shape optimization, and assess actuation requirements in different scenarios (opening/closing the slot in different conditions). We will also explore scaling effects and define requirements for future wind tunnel or flight tests.
Dynamic and Stability of Wake Vortices
N/A
Internship offer
Full-time
4.35€ / h – 35 h / week
Master's degree
Between 0 and 2 years
Intern
01/12/2026
The aim of this internship is to characterize the formation and near-field evolution of wing-tip vortices over a range of Reynolds and Mach numbers by means of Unsteady Reynolds-Averaged Navier–Stokes (URANS) simulations. In particular, we seek steady solutions of the URANS equations, i.e., RANS solutions corresponding to equilibrium states of the flow. These computed flows will constitute the base states of the global stability analyses, in which turbulence is accounted for through a linearized Spalart–Allmaras model. The quality of these base flows will directly determine the reliability of the stability predictions.
The first part of the internship will be devoted to getting to grips with generic URANS solvers on a reference wing-tip vortex configuration for which detailed experimental data are available. Particular attention will be paid to the meshing strategy, since the vortex core is a thin region of intense rotation that must be resolved over long downstream distances.
The second part will consist of a parametric study of wing configurations at several Reynolds and Mach numbers. Beyond computing the flows, the student will analyse the physics of the vortices: roll-up of the vortex sheet, downstream evolution of circulation, core radius and axial velocity, and sensitivity of the vortex core to turbulence modelling. The computed vortices will be compared to analytical models such as the Batchelor vortex, in order to extract the parameters governing their stability (swirl number, axial velocity deficit or excess) and to position each configuration with respect to known instability criteria from literature.
Looking ahead, at the end of the project, the resulting database of converged RANS equilibrium solutions will serve as base states for the first global stability analyses.
Therefore, the goals of this internship can be summarised as follows:
- Getting to grips with the URANS solvers and the CFD mesh generation software (ANSYS ICEM, Gmsh or similar).
- Validating the numerical set-up on a reference wing-tip vortex case against experimental and numerical data.
- Computing the flow around wings at several Reynolds and Mach numbers on dedicated meshes.
- Providing the RANS base flows for the global stability analysis tools.
Deterministic QoS Guarantees in Next -Generation LEO Satellite Constellations
N/A
PhD offer
Full-time
5-35k€ gross salary / YEAR
Master's degree
Between 0 and 2 years
Doctoral student
07/09/2026
Low Earth Orbit (LEO) satellite constellations — such as Starlink, OneWeb, Kuiper, and Telesat Lightspeed — are rapidly becoming a cornerstone of next-generation communication infrastructures and future 6G networks.
With thousands of satellites orbiting at altitudes between 500 and 2000 km, these systems offer unprecedented global coverage combined with significantly lower latency than traditional geostationary systems. The emergence of LEO constellations opens transformative opportunities for time-sensitive applications. These applications demand deterministic end-to-end delay guarantees — strict, provable upper bounds on latency — rather than best-effort performance. However, providing such guarantees in LEO constellations remains an open and largely unsolved problem.
Preliminary research conducted at ISAE-SUPAERO has demonstrated that Network Calculus (NC), a mathematical framework for computing worst-case performance bounds in communication networks, can be successfully adapted to LEO satellite constellations. This PhD aims to develop a comprehensive analytical and algorithmic framework for deterministic QoS guarantees in dynamic LEO satellite constellations within a collaborative project PEPR FRONTIER funded by the ANR with many partners like CNRS, Sorbonne Université et mines-Telecom Bretagne.
Towards a more operation-centric approach to aircraft design
PhD offer
Full-time
2153€ net pay before income tax /month
Between 0 and 2 years
Doctoral student
30/06/2026
The thesis is proposed in the framework of the EA²GLE Graduate school related to the electrification of Aircraft and Automobiles and is co-funded by the AMI CMA PEGASE and the Occitanie Region.
The research activities aim to develop design methodologies for low-carbon aviation by addressing the challenges of incorporating operational constraints, failure scenarios, and multi-mission requirements into the optimisation process. The developed methodologies will be applied to the design of architectures of more electric aircraft in the category CS23.
The outcomes of the thesis will enable aircraft manufacturers to design safer, more efficient and more environmentally sustainable aircraft, while reducing design risks, development costs, and time to market.
This thesis will be organized based on several well-defined research axes which will structure the project:
- Axis 1 (Month 1 to 6): this axis will focus on proposing a ConOps for aircraft in the General Aviation segment (which will be the scope of this thesis) and more specifically for larger aircraft specified under CS-23. This will be done thanks to a review of current aircraft in this category, not only including missions but also geographical profiles, and will also include a review of design constraints for propulsive and non-propulsive systems.
- Axis 2 (Month 7 to16): this axis will aim at improving the models in the FAST-OAD-CS23-HE framework which is developed to assess Hybrid Electric aircraft of category CS23. It will include the proposition of models for the sizing of non-propulsive systems on General Aviation aircraft and their impact on the sizing of propulsive systems (which therefore requires higher fidelity modeling on thermal machines). Additional work on the impacts of usage of thermal machines and batteries on their respective lifespan and performances is also expected.
- Axis 3 (Month 17 to 24): this axis will focus on the methodological aspect of deploying multi- mission optimization in an OAD framework. In particular, tradeoffs between different objective functions such as costs or environmental impacts will be investigated. The use of a simplified test case is proposed for this axis.
- Axis 4 (Month 25 to 30): this axis will further develop the work done in the previous months with a specific application to the TBM900 family and will investigate the possibility and viability of electrifying propulsive and non-propulsive functions.
- Month 31 to 36 will be dedicated to the redaction of the manuscript and preparation of the defense.
This work is expected to lead to the publication of at least 1 scientific article in a top-tier journal and at least two international conferences.
Modelling of the dynamical performance of a protective structure ceramic-adhesive-composite: analysis of the adhesive layer functionality
N/A
PhD offer
Full-time
2200€ / month
Master's degree
Between 0 and 2 years
Doctoral student
01/06/2026
This thesis proposal is part of an upstream project to improve the performance of so-called ‘dual-hardness’ armour, consisting of a ceramic layer (on the front face) and a composite layer (on the back face, known as the backing), as shown in Figure 1. The main function of the ceramic layer is to slow the progress of the impacting projectile by dissipating energy through fragmentation [Rahbek 2017, Shokrieh 2008, Colar 2013, Colar 2015]. The main function of the backing layer is to retain the ceramic fragments (non-perforation criterion) and to limit the penetration of the protection (penetration criterion). An adhesive is used to join these two materials. At present, this adhesive layer is not explicitly functionalised to contribute to the performance of the armour. One of the main objectives of this project is to understand and model the function of this layer to improve the armouring.
While it is essential to understand the modes of fragmentation of the front face under impact and the modes of backing failure, it is also necessary to consider the influence of adhesive strength on these failure modes. It is the breaking strength of the adhesive that provides the system with sufficient flexural rigidity to limit deflection of the rear face and prevent perforation of the backing layer by ceramic fragments. The adhesive also serves to hold the backing in place. It is also likely to be important to use coupled tests and calculations to understand whether the adhesive layer can help to improve the fragmentation of the ceramic layer. Another objective of this project is therefore to capitalise on the developments of the behaviour models developed during the previous AID ‘tri-layer’ project [Essongue 2022] and the DGA/ISL thesis of Tristan Camalet [Camalet 2020, Duplan 2020, Francart 2017], as well as the developments carried out in the partner laboratories concerning the behaviour of bonded interfaces [Lopez-Puente 2005, Lélias 2018, Jaillon 2019a 2019b, Planas 2024],
In addition, in the development of these protections, research into new materials and optimised assemblies to best satisfy the protection criteria (energy absorption, non-perforation of the backing, punching of the backing, reuse, multi-impact protection, recyclability and environment) is necessary. In this context, two identified partners (currently partners of ISAE-SUPAERO) Arkema for adhesives and St Gobain for protective materials (on the front face and for the backing) wish to participate in the project by supplying adhesive materials (Arkema) or new materials (Saint Gobain). This last point constitutes an opening objective of the project concerning the study of new front panel and backing materials.
The thesis work therefore follows on from these research activities in the field (work carried out at ISAE-SUPAERO/ICA in collaboration with ICUBE and ISL since 2017 (Thesis CAMALET / Post Doc ESSONGUE) and is more particularly interested in the influence of the fracture or holding properties of the adhesive on the modification of the fragmentation of the ceramic and the deflection/damage of the backing. The thesis work is also part of a theme concerning the high-speed modelling of the behaviour of materials and composite structures assembled by gluing (and/or bolting).
Use of AI algorithms and discrete modeling to improve control of a flexible parachute canopy during maneuvers
N/A
PhD offer
Full-time
~2000€ / month
Master's degree
Between 0 and 2 years
Doctorant
Context : The complexity and the unstable and uncertain non-linear nature of the response of large flexible parachute canopies, interacting with a surrounding fluid under the effect of manoeuvring actions, are obstacles for deterministic flight mechanics control models and algorithms. Conventional weakly or strongly coupled finite element simulation methods are costly and unstable, and cannot be used to improve their construction.
Project : To meet this modelling and simulation challenge, the team is developing a research code for structural calculations based on a discrete method [1]. This code is frugal in terms of calculation time and can be used to assess the influence of local effects of tissue deformation on manoeuvring forces. The aim of the thesis is to improve the existing tool to enable dialogue with artificial intelligence (AI) algorithms [2,3] for the analysis of the stability and steerability of the sail. The aim of the thesis is to meet the ambition of getting the sciences of structural mechanics to communicate and interact with those of control and AI mathematical algorithms.
Seamless Integration of Models in a MBSE-MBSA-MDAO Co-Design Process
N/A
PhD offer
Full-time
2600€ / year
Master's degree
Between 0 and 2 years
Doctoral student
31/07/2026
The theme of the interoperability of model-based design and analysis approaches is one of our strong areas of research. This thesis is a continuation of the work carried out as part of the CONCORDE collaborative project between ONERA, ISAE and ENAC. The expected results should enable us to consolidate our advances in the field of synergy between models, and open up new collaborations using the planned laboratory platform.
laboratory platform.
PhD ACTAM : Aeroacoustics of multi-axle landing gear
PhD offer
Full-time
Master's degree
Between 0 and 2 years
Doctoral student
This PhD proposes to investigate multi-axle landing gear noise generation mechanisms in order to propose innovative low-noise designs.
Cavitation in cryogenic fluids in microgravity conditions
N/A
PhD offer
Full-time
2100€ / month
Master's degree
Between 0 and 2 years
Doctoral student
01/03/2026
A PhD position is open in the Space Advanced Concepts Laboratory in collaboration with IMFT (institute de mécaniques des fluides des Toulouse)
Supervisors:
- Annafederica Urbano, professor, ISA-SUPAERO
- Sébastien Tanguy, professor, Université Paul Sabatier, IMFT
Technological context and scientific questions
During depressurization for propellant preconditioning (and cooling) prior to engine ignition or propellant transfer (in the context of space depots), bubbles can form and grow due to cavitation. This is a problem due to vapour accumulation under microgravity conditions and the impact on wall heat transfer. More generally, cavitation, under conditions where phase change predominates, is important for many applications (including nuclear power plants) and raises many questions that are not understood at the small scale.
This justifies the development of the SCREAMH2 microgravity wall cavitation experiment (currently in phase A/B development under an ESA contract), in which ISAE-SUPAERO is participating as part of the scientific team.
There are several scientific open questions regarding pool cavitation. It is unclear how the contact line phenomena (nano-region, wall roughness, cavity shape…), the level and dynamics of depressurization, and the nature of the fluid (pure or in the presence of non-condensable gas) impact the growth of these bubbles and the associated wall heat flux.
This thesis project aims to answer these questions by developing numerical models capable of accurately simulating pool cavitation, in parallel with the development of the SCREAMH2 experiment. The results will serve, on the one hand, as support for the experiment and, on the other hand, for its extension, particularly to configurations with multiple bubbles and in the presence of non-condensable gases.
Background
The present project is a continuation of the team’s recent work on the development of a solver for the direct numerical simulation of two-phase flows with phase change. The originality of the solver, based on a semi-implicit compressible projection method, lies in its thermodynamic consistency, which allows it to describe liquid, vapor, and saturation conditions at the interface for a generic fluid.
The solver has recently been extended to phase change in the presence of a contact line (solid, vapor, liquid) and validated for the simulation of nucleate boiling and pool cavitation. It has thus enabled parametric studies and model developments for bubble cavitation in microgravity at the wall. The models will be extended and generalized in this project.
This project aims to further develop the numerical solver and to use it to answer the scientific questions raised.
- Numerical development of the immersed boundary method [5] to include conjugate heat transfer and contact lines. After validation on basic test cases, configurations with complex geometries will need to be addressed. Initially, the simulation of CH4 pool cavitation used for validation in [4] will be reconsidered with the complex geometry (cylindrical support and cavity for the bubble).
- Incondensable gas. The solver will be extended to account for the presence of multi-species vapor and incondensable gases adsorption in the liquid while ensuring thermodynamic consistency at the interface. A surface tension model dependent on local composition will be developed, and the jump conditions will be adapted to take thermo-capillary effects into account. The model will need to be validated for simulation in the presence of Marangoni currents (using existing experimental data).
- Pool cavitation in micro-gravity. Several objectives will be pursued. The first will be to support the SCREAM H2 project with detailed numerical simulations. The second will be to extend the study of pool cavitation to many fluids, considering non-condensable gases and various geometric configurations. In particular, the phase change models developed in [4] will be extended and used to simulate multi-bubble configurations, the interaction between bubbles and their impact on wall heat transfer in microgravity.
Impact
While this project focuses on pool cavitation in microgravity, it is important to note that the developments envisaged are also intended to simulate and study other phenomena involving phase change in compressible flows in the presence of contact lines. These include 1) sloshing in tanks and 2) hydrodynamic cavitation with the development of cavitation pockets. It is planned to study such configurations towards the end of the thesis project, depending on how the project progresses.
Work environment
The PhD will be funded by CNES and will be hosted in the Space Advanced Concepts Laboratory at ISAE Supaero in collaboration with IMFT.