Document Type
Paper
Abstract
The purpose of this report is to expand knowledge on the lift and drag properties of thin triangular airfoils, and determine whether or not they are a viable option for low-Reynolds number applications. Thin triangular airfoils were thought to be more efficient than standard NACA airfoils under specific conditions. This experiment was performed through the wind tunnel testing of a NACA 2412 and nine thin triangular airfoils with varying max camber points. Between the Reynolds numbers of 30-42,000, lift and drag values were collected at varying angles of attack. Overall, it was found that the thin triangular airfoils proved to have unique lift and drag characteristics when compared to the standard NACA 2412.
Optimizing Max Camber Points Along Thin Triangular Airfoils for Higher Lift/Drag Ratios
The purpose of this report is to expand knowledge on the lift and drag properties of thin triangular airfoils, and determine whether or not they are a viable option for low-Reynolds number applications. Thin triangular airfoils were thought to be more efficient than standard NACA airfoils under specific conditions. This experiment was performed through the wind tunnel testing of a NACA 2412 and nine thin triangular airfoils with varying max camber points. Between the Reynolds numbers of 30-42,000, lift and drag values were collected at varying angles of attack. Overall, it was found that the thin triangular airfoils proved to have unique lift and drag characteristics when compared to the standard NACA 2412.
