We created a tool using Matlab to model the lift, drag, and flight performance (range and endurance) of a small aircraft. The model was validated using CFD data that was given to us for a small aircraft. This was then used to design a glider optimized for range. One design was down selected (out of 5) and that design was then further iterated upon and improved. This design was then manufactured out of foam and then tested and trimmed for max range (slightly different trim than calculated due to manufacturing errors). The design was then tested, fine tuned and repaired. During the competition, the glider carried a sensory payload that recorded altitude, as well as other data. The post flight data was then analyzed and a summary presentation was made.

The goal was to create a model to calculate the Coefficient of lift curve, Drag Polar, Range, and Endurance. This model was Validated with a comparison to CFD data from the Tempet UAS, a CU drone aircraft.

I created the coefficient of lift model using a lift curve slope calculation (that accounted for downwash). I then compared this with the CFD data that i imported and cleaned. 

I also helped with the drag polar calculations and its code logic and development. The drag took into account the induced drag from the aircraft's lift as well as the parasite drag from the skin friction. The coefficient of friction was approximated using given values of gliders and small aircraft. The surface area was found by approximating the aircraft as simple shapes such as cones and Rectangular cuboids.

Another partner and I also did all of the Range and Endurance calculations for both the tempest data and our model. This was done by using the lift vs drag curve. 

A more detailed method can be seen in the following document:

The glider was thrown off of a gently sloping hill and the trim was tuned to prevent stall as well as attempt to maximize glide range. Videos of the testing can be seen in slides 9 and 11 in the Post Flight Analysis presentation.

There was a pitch up mid way through the flight resulting in a stall that the aircraft did not have the height to recover from.