- Debdoot Ghosh

# Figure out any past or future problem with multiple solutions, discuss the solution and back your ar

*Figure out any past or future problem with multiple solutions, discuss the solution and back your argument with proper reasoning.*

IN this article, I discussed a problem I faced related to aerodynamics while I was an intern in SimulationLab, Pune. The problem was the lift to drag ratio of an aircraft wing decreases significantly at high Angle of Attacks, the angle between the velocity vector of freestream air with the reference line of the wing, at hypersonic speeds i.e., at least more than five times the speed of sound flight.

There were already substantial improvements have been done by previous researchers in hypersonic airfoil design, like- putting vorticity generators over the wing to create flow separations, Bi-or-Quad flapped airfoil based wing to dismissing the effects of shock waves form at hypersonic speeds, sinusoidal generators at the leading edges of the wing to decrease the adverse effects of the shock waves but creating flow separations, low-density fuel injection over the wing to decrease the friction and hence the drag generation, etc. All the above-mentioned solutions have their own advantages and disadvantages. I wanted to design a completely new wing model which is relatively more simple and compact but highly effective at hypersonic speeds.

After a lot of brainstorming and analyzing previous works, I came up with a new solution. I designed a new Multi-feature wing in which spherical bumps of varying sizes are embedded asymmetrically over the bottom of the wing. The design was modeled as a 3D CAD file. Then to investigate the aerodynamic attributes of the design it was simulated at appropriate configurations and flight conditions with a CFD (Computational Fluid Dynamics) solver. The observations were-the coefficient of lift increased proportionally with an increase in the Angle of Attack and freestream velocity. Also, an increase in the Lift to Drag ratio was observed with the separation between two adjacent spherical bumps. Thus, from the observations, it was concluded that the wing is suitable to use at hypersonic flights and in aircraft which demands high maneuverability.

This is how I found a solution for the above mentioned problem of multiple ways of approaching and solution. Later, my work was greatly appreciated by the Director of SimulationLab.

**The design of the wing:**

**Y-axis: Mach No. (Freestream Velocity / speed of sound)**

**X-axis: Angle of Attack (AoA)**