Figure 2.2.1 - Wing design in XFLR5
Polars were generated for the XFLR5 wing design in Figure 2.2.1. For XFLR5, inviscid flow and a rectangular wing modified from the NACA 23012 airfoil (from the UIUC database) was used. For the XFLR5 simulation, parameters included a Reynold's number of ~50,000, standard air conditions, and a point mass of 304 [g] for the CG of the drone was used. In actuality, the wings placed on the drone had a sanded leading edge as opposed to true airfoil shape and were elliptical planform wings so the XFLR5 simulation will have discrepancies and was therefore only used as a rough estimate of the polars and as an additional piece of information for our wing design and analysis.
Figure 2.2.2 - Polars for wings centered around CG and each wing at 30 degrees angle of incidence
Figure 2.2.3 - Polars for wings centered around CG and each wing, front wing at 25 degrees angle of incidence and back wing at 30 degrees angle of incidence.
Figure 2.2.3 - Polars for wings with wing off-center of CG by 1.5 [cm] (front wing moved closer to CG). Front wing at 25 degrees angle of incidence and back wing at 30 degrees angle of incidence.