Experimental Database

The NWTF experimental database is a catalogue of validated datasets with links to data saved on university (or other) repositories.

Get in contact here to learn more.

DrivAer Experimental Aerodynamic Dataset

Author:
Max Varney, Martin Passmore, Felix Wittmeier, Timo Kuthada
Facility:
University of Loughborough
Date created / revision:
10 September 2020
This is a dataset for the 25% scale DrivAer model. Data was collected in the Large Wind Tunnel at Loughborough University, a 2.5m^2, closed working section, fixed ground open return tunnel.

The CAD geometry for the mounting hardware and the wind tunnel are all included in the dataset as ASCII .stl files, with the units in m. The CAD geometry of the DrivAer model has not been duplicated for this dataset.

Photos of the set up and some unique model dimensions are also included. The model was supplied by FKFS and is a 25% scale DrivAer model with three backs, the estate, fast and notchback variants. The model included the 5 spoke wheels, complex underbody, wing mirrors, the drivetrain, an open front grill and a porous radiator. As the model is not symmetric, in the engine bay and on the underside, it was set at a geometric 0 yaw condition as measured in the wind tunnel. This is estimated to be +/-0.1 degrees.

No corrections (for example blockage) have been applied to the data. All the data is presented in SI units and all measurements are from the origin (mid-track, mid-wheelbase on the tunnel floor) with x positive downstream and z positive up, using the right hand rule to find positive y.

The data is split into '_Mean' and '_Instantaneous' for each measurement type (Force, Pressure, Flow Field). All the data was taken during the same test session with a total sample time of 300 seconds typically and 100 seconds for the measurements in the stagnation region. The different data sets are not correlated with each other in time. The Force data was sampled at 300Hz, Pressure data at 260Hz and the Flow Field data at 5Hz. The data presented in the '_Mean' folders is the arithmetic mean of that presented in the '_Instantaneous' folders.

All the '_Mean' folders contain Comma Separated Variable (csv) files, for ease of parsing with your desired programming language, and the same data is provided in a .dat file that is set up to be read into TecPlot. The csv format was used to reduce size and complexity for the '_Instantaneous' data. Example MATLAB code has been provided (tested in 2018a) that reads both the '_Mean' and '_Instantaneous' csv files for the pressure and flow field measurements, plotting them accordingly.

Half aircraft wind tunnel model data

Author:
Shaun Skinner
Facility:
University of Glasgow
Date created / revision:
25 August 2020
Data object contains model geometry, aerodynamic loads, and velocity field measurements of the trailing vortex from PIV.

Experimental investigation of the effect of yaw angle on the inflow of a two-bladed propeller

Author:
Richard Green
Facility:
University of Glasgow
Keyword:
two-bladed propeller
Date created / revision:
6 March 2020
An experimental investigation has been performed to measure the inflow of a two-bladed propeller. This is conducted over a range of advance ratios (J =0.36 to 1.54) and yaw angles (γ = 0 to 20◦) at a Reynolds number of Re ≈ 111000, based on the chord length and advancing blade resultant velocity at the 70% spanwise position. Drawing on experimental results, three major qualitative trends are observed, that characterise the axial induced inflow of inclined propellers: the formation of an approximately sinusoidal inflow trend around the azimuth featuring broad regions of increased and reduced inflow, an azimuthal phase shift of the trend from the advancing and retreating blade positions, and the dependencies of the inflow maxima, minima and phase shift on advance ratio, yaw angle and radial position. These are subsequently compared against two widely used assumptions for calculating the aerodynamic environment of inclined propellers; firstly, that inflow at each radial and azimuthal element is calculated using an axial approximation of the whole propeller disc operating within the same condition as that element, and secondly, uniform induced inflow across the entire propeller plane. The comparison demonstrates the limitations of said assumptions by highlighting their inability to account for components of the trailed and shed vortical systems of the propeller wake.

Air jet flow control on pitching aerofoils

Author:
Simon Prince, Richard Green, Vahik Khodaglian
Facility:
Cranfield University
Keyword:
aerofoil
Date created / revision:
8 July 2019
Experimental data on the effect of steady and pulsed air jet vortex generator blowing on a RAE9645 aerofoil section in dynamic stall.