The objective of my paper was to demonstrate the results of the effects of tangential blowing by utilising a low-cost method to show those results. The use of direct wind tunnel imagery in the process of verifying the impact of the blowing jets is a rare method to find in aerodynamics research. However, in this paper we reveal that the advantages of this method are derived from its simplicity. Circumventing the heavy requirements of computational fluid dynamics (CFD), the imagery method plots the bounding stream paths that reveals crucial details about the nature of the streamlines and general fluid flow.
An extension of the windtunnel project, this paper aims to demonstrate the the qualitative evaluation of simple aerodynamic regimes is possible without the utilisation of complex computationally intensive evaluation methods.
Underlying Principles
For most cases in aerodynamic prototyping, we wish to understand if the given design is better than the normative contrapositive. For example, if I claim my prototype would make the wing more aerodynamic and less turbulent, we are only interested in perceiving that difference.
Therefore, I developed this analysis with the aid of greyscaling images and determining the shape of the air flowing around.
Transparent test section construction allowed the camera setup demonstrated in fig. 1.3 to capture imagery produced from the airfoil’s interactions. 1 - the high frame rate camera was calibrated
to extract true-color images of the streamlines flowing over the airfoil; 2 - the frame section was utilised as the plane of reference to make all observations.
Aerodynamic interactions are made visible by the flow visualiser which injects opaque CO2 onto the regions of interest.
Experimental verification required the construction of a modified scaled-down wing section with the NACA 2412 airfoil. The modified airfoil incorporates a Trailing Edge Blowing (TEB) construction the nozzle jet surfacing at 0.85 the length of the chord. Sillicon tubes (5mm), which remains in the prescribed 1% − 5% of the chord length in diameter, is implanted through the wing onto
its upper face.
The corrected points are then plotted graphically, replicating the position co-ordinates that trace the streamline from the previous
step. These graphs plot the upper and lower layers of the streamline, containing data regarding their thickness and shape from which we imply their nature.
The correlation between the top graph and the bottom one determine the turbulence state of the system. Therefore, by the sole analysis of this, we can determine many conclusions without having to determine several other methods of complex inference in aerodynamics. This method is cheaper and more time/resource efficient than anything out there.
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