Mathematical Modelling & Programming

PROPRIETARY MATHEMATICAL MODELLING EXPERIENCE

Propeller blade aerodynamic design and optimization

- propeller blade aerodynamic analysis codes (blade element method, airfoil databanks, modified momentum theory) - existing Fortran models translated into Matlab and capabilities of the models were further enhanced

- open rotor blade aerodynamic analysis codes (blade element method, airfoil databanks, modified momentum theory) - existing Fortran models translated into Matlab and capabilities of the models were further enhanced

- propeller blade aerodynamic optimization codes (blade element method, airfoil databanks, modified momentum theory) - existing Fortran models translated into Matlab and capabilities of the models were further enhanced

- ducted propeller blade aerodynamic analysis codes (blade element method, airfoil databanks, modified momentum theory) - existing Fortran models translated into Matlab and capabilities of the models were further enhanced

- ducted propeller blade aerodynamic optimization codes (blade element method, airfoil databanks, modified momentum theory) - existing Fortran models translated into Matlab and capabilities of the models were further enhanced

- propeller blade FEA codes (time & frequency domain beam FEM models) - models developed in Matlab

NON-PROPRIETARY MATHEMATICAL MODELLING EXPERIENCE

Fixed wing aerodynamics

- Light/GA aircraft wing structural analysis and design - models developed in MS Excel and MathCAD

- Light/GA aircraft wing aerodynamics (lifting line models) - models developed in MS Excel, MathCAD & Matlab

Helicopter / Autogyro rotor blade aeromechanics

- development of improved airfoil aerodynamic databanks for full range of angles of attack and transonic Mach numbers (lift, drag and moment coefficients) - models developed in Matlab

- modelling of blade aerodynamics (blade element method, modified momentum theory) - models developed in Matlab and Maple

- dynamic inflow models (modified Peters-He 3-state model, modified momentum theory) - models developed in Matlab

- FEA of blade structural dynamics (time & frequency domain beam FEM models) - models developed in Matlab

- flight mechanics - new models developed in Matlab; existing Fortran models translated into Matlab

- flight dynamics and vehicle trim modelling - translated existing Fortran models into Matlab

Data science, visualisation and machine learning

- R & RStudio - processing, visualization and analysis of business data using various R packages. Creation of online dashboards and apps using R Shiny package

- Python - data analysis and machine learning using various Python packages, including sklearn, tensorflow and keras.

- Javascript, SQL, HTML & CSS - development of business dashboard and apps using nodejs, Cloud Foundry and Predix

- Alation, Dataiku & Spotfire - business analytics and self-service analytics training

- AWS stack - AWS practitioner certification

- Solidity and Ethereum - smart contracts and practical use of blockchain for business operations

NON-PROPRIETARY MATHEMATICAL MODELLING PORTFOLIO

AERODYNAMIC CHARACTERISTICS OF NACA 0012 AIRFOIL FOR FULL RANGE OF ANGLES OF ATTACK

The codes are based on Prouty's method of approximation airfoil aerodynamic characteristics (lift coefficient and drag coefficient) improved during my PhD research and combined with my own interpolation of NACA 0012 pitching moment coefficient data published by Leishmann. The compressibility effects are neglected in post-stall region of angles of attack. More detailed information on functionality and validation of the codes can be found here.

The codes were used in a rotorcraft blade element model developed during CAA ARB sponsored 'Aeroelastic Modelling of Gyroplane Rotors' research project and can be used for simulation of 2D airfoil aerodynamics. Approximation of aerodynamic characteristics of alternative airfoils designs can be developed by tweaking of airfoil parameters used in the codes.

Figure 1 shows trends of lift coefficient for a number of free-stream Mach numbers and full range of angles of attack.

Fig. 1 - Values of lift coefficient of NACA 0012 airfoil as generated by prouty_lift.m code.

Figure 2 shows values of NACA 0012 drag coefficient for the same range of angles of attack and Mach numbers.

Fig. 2 - Values of drag coefficient of NACA 0012 airfoil as generated by prouty_drag.m code.

Figure 3 shows approximation of NACA 0012 pitching moment coefficient data for different Mach numbers and full range of angles of attack.

Fig. 3 - Values of pitching moment coefficient at quarter-chord of NACA 0012 airfoil as generated by prouty_cm.m code.

INTERNATIONAL STANDARD ATMOSPHERE (ISA) CALCULATOR

This code calculates parameters of Standard Atmosphere - air pressure, air density, kinematic and dynamic viscosity, air temperature and speed of sound.