Tarun's RC Plane
The wings were built using a combination of Thin Airfoil Theory to design the airfoil and Lifting Line Theory to design the wing shape.
-
Thin Airfoil Theory -
-
Allows us to collapse airfoil onto camber line if the max thickness is much less than the chord length.​
-
Enforces the No Penetration Boundary Condition through the introduction of vortices along the camber line.
-
The Thin Airfoil Theory does not address the Kutta Condition, which required an initial condition where the vortex strength per unit length is set to zero at the trailing edge.
-
The Thin Airfoil Theory requires the approximation of all angles used in the derivation to be small, limiting the Theory to non-separated flow.
-
-
Lifting Line Theory -
-
Derived by stacking an infinite number of vortices along the lifting line, where each vortex trails off at a different point in the wingspan.
-
The circulation is solved by setting the sectional lift from the Kutta-Joukowski Theorem equal to the sectional lift from the Thin Airfoil Theory, where the Thin Airfoil Theory has been modified to include downwash.
-
Lift and drag can then be calculated by integrating the circulation along the wingspan.
-
Solution to Finite Wing Theory
-