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Postgraduate DiplomaAerospace, UAM, Drones & Space Applications open

Diploma in Applied Supersonic/Hypersonic Aerothermodynamics

Online postgraduate diploma of 800 hours in applied supersonic/hypersonic aerothermodynamics. 8 modules covering compressible flow, hypersonic phenomena, aerodynamic heating, intakes and air-breathing propulsion, hypersonic simulation, atmospheric re-entry and supersonic aerodynamic design with ISO 2533, NASA-STD-7009A and ANSYS Fluent, with an assigned technical tutor.

Duration6–8 months
ModeOnline
LanguageEnglish
Start datesSet by the faculty
AwardSEIUM Institute diploma
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Learning outcomes

What you will be able to do

01

Apply compressible flow theory to supersonic problems.

02

Characterise the phenomena specific to the hypersonic regime.

03

Estimate aerodynamic heating with analytical methods.

04

Analyse air intakes and high-speed air-breathing propulsion.

05

Simulate hypersonic flows with CFD and DSMC.

06

Assess re-entry configurations and their stability.

07

Design supersonic aerodynamic configurations with efficiency criteria.

Profile

Who it's for

  • Aerodynamics engineers.
  • Aerothermodynamics engineers.
  • CFD analysts.
  • Re-entry systems engineers.
  • High-speed flow researchers.
  • Spacecraft design engineers.
  • Engineering or science graduates looking to enter the aerospace sector.
Standards & tools

What you'll work with

  • ISO 2533 (standard atmosphere)
  • NASA-STD-7009A (standard for models and simulations)
  • ECSS-E-ST-31C (space thermal control)
  • AIAA G-077-1998 (guide for verification and validation of CFD simulations)
  • ASME V&V 20 (verification and validation in CFD and heat transfer)
  • ANSYS Fluent
  • SU2
  • NASA CEA
  • SPARTA
  • MATLAB
Syllabus

8 modules

  1. 1.1Mach number and flight regimes
  2. 1.2Isentropic relations
  3. 1.3Normal shock waves
  4. 1.4Oblique shocks
  5. 1.5Prandtl-Meyer expansion
  6. 1.6Convergent-divergent nozzles
  7. 1.7Fanno and Rayleigh flows
  8. 1.8Method of characteristics
  9. 1.9Shock-boundary layer interaction
  10. 1.10Practical exercise: calculating shocks in a two-dimensional intake
  1. 2.1Thin shock layer
  2. 2.2Modified Newtonian theory
  3. 2.3Viscous interaction
  4. 2.4Entropy layer
  5. 2.5Real gas effects
  6. 2.6Dissociation and ionisation
  7. 2.7Chemical and thermal non-equilibrium
  8. 2.8Rarefaction and Knudsen number
  9. 2.9Communications blackout
  10. 2.10Workshop: Newtonian aerodynamics of a cone
  1. 3.1Compressible boundary layer
  2. 3.2Recovery temperature
  3. 3.3Fay-Riddell correlation
  4. 3.4Reference temperature method
  5. 3.5Transition in hypersonic flow
  6. 3.6Radiative heating
  7. 3.7Wall catalycity
  8. 3.8Leading edges and nose
  9. 3.9Engineering correlations
  10. 3.10Practical exercise: stagnation point heat flux
  1. 4.1Supersonic intakes
  2. 4.2Total pressure recovery
  3. 4.3Intake start and unstart
  4. 4.4Ramjet
  5. 4.5Scramjet principles
  6. 4.6Supersonic combustion at a conceptual level
  7. 4.7Airframe-engine integration
  8. 4.8Waverider configurations
  9. 4.9X-43 and X-51 experimental programmes
  10. 4.10Case study: mixed-compression intake
  1. 5.1Upwind schemes and limiters
  2. 5.2Thermochemical gas models
  3. 5.3Shock-adapted meshing
  4. 5.4Direct simulation Monte Carlo
  5. 5.5Catalytic wall conditions
  6. 5.6Coupling with wall conduction
  7. 5.7Uncertainty in high-temperature models
  8. 5.8Validation with flight data
  9. 5.9Computing resources
  10. 5.10Lab: simulating a wedge in SU2
  1. 6.1Ballistic and lifting trajectories
  2. 6.2Re-entry corridor
  3. 6.3Blunt-body capsules
  4. 6.4Lifting bodies
  5. 6.5Static and dynamic stability
  6. 6.6Deceleration and heat load
  7. 6.7Mars and Titan entries
  8. 6.8Supersonic parachutes
  9. 6.9Lessons from historical missions
  10. 6.10Case study: re-entry profile of a capsule
  1. 7.1Supersonic commercial aviation
  2. 7.2Sonic boom and its mitigation
  3. 7.3Area rule
  4. 7.4Swept and delta wings
  5. 7.5Wave drag
  6. 7.6Supersonic control and stability
  7. 7.7Shape optimisation
  8. 7.8Validation testing
  9. 7.9Environmental requirements
  10. 7.10Workshop: estimating wave drag
  1. 8.1Configuration and mission
  2. 8.2Inviscid flow analysis
  3. 8.3Heating estimation
  4. 8.4Numerical simulation
  5. 8.5Stability analysis
  6. 8.6Comparison with correlations
  7. 8.7Design recommendations
  8. 8.8Conclusions
  9. 8.9Report and presentation
  10. 8.10Final project: final review with the tutor
Methodology, software & labs

How you'll learn

100% online programme on the SEIUM campus, with downloadable material, recorded classes and an assigned technical tutor. No fixed timetables: you progress at your own pace within the intake, so it fits around your job.

Each module combines theory, guided reading of the original standard and applied exercises. The working software is ANSYS Fluent, SU2, NASA CEA, SPARTA and MATLAB, in free, academic or evaluation versions. Practical work is based on real procedures: calculating shocks and expansions in simple geometries, numerical simulation of hypersonic flows and estimating stagnation point heating. Assessment is continuous per module plus the final project.

Standards covered: ISO 2533, NASA-STD-7009A, ECSS-E-ST-31C, AIAA G-077-1998, ASME V&V 20.

Assigned technical tutor:every module ends with a deliverable that your tutor marks individually.
Standards-based learning:guided reading of ISO 2533, NASA-STD-7009A and ECSS-E-ST-31C applied to real cases, not as a theoretical annex.
Industry software:ANSYS Fluent, SU2, NASA CEA, SPARTA and MATLAB, in free, academic or evaluation versions.
Final project:An aerothermodynamics project covering inviscid analysis, heating estimation, numerical simulation and stability of a high-speed configuration, reviewed by your tutor.
Flexible format:100% online, no fixed timetables, compatible with full-time work.
Capstone project

Build it end to end

Your final project follows the real engineering workflow, step by step, reviewed by your tutor.

Configuration and inviscid analysis
Define the configuration and mission and analyse the inviscid flow field.
Heating estimation
Estimate aerodynamic heating with engineering correlations.
Numerical simulation
Simulate the configuration numerically and compare with correlations.
Stability and design recommendations
Analyse stability and draw up design recommendations.
Final project
Conclusions, report and presentation, reviewed by your tutor.
Career opportunities

Where this takes you

Aerodynamics engineerAerothermodynamics engineerCFD analystRe-entry systems engineerHigh-speed flow researcherSpacecraft design engineer
Admissions & scholarships

Requirements

  • Prior technical training or professional experience in the sector. No university degree is required.
  • Internet connection and a computer able to run the programme software.
  • English sufficient to read technical standards.

Ready to start?

Send your application today. Our admissions team replies within 72 hours with your study plan and funding options.

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FAQ

Frequently asked questions

The programme totals 800 hours over 6–8 months. You set your own pace within each intake, and your tutor helps you plan the workload around your job.

You work with ANSYS Fluent, SU2, NASA CEA, SPARTA and MATLAB, using free, academic or evaluation versions. Your tutor indicates the free alternative wherever one exists.

A SEIUM Institute diploma, awarded on passing the continuous assessment and the final project. It is SEIUM's own qualification, not an official state degree; its recognition depends on the programme completed and the regulations of each country.

Yes. Modules passed are recognised in a higher programme in the same area (postgraduate diploma or master's). Ask about the recognition policy when you enrol.

Prior technical training or professional experience in the sector (no university degree required), a computer able to run the software and English sufficient to read technical standards.

Start dates are set by SEIUM's faculty for each intake. Our admissions team will confirm the next available date when you apply.

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