Given the component of free-stream velocity in the direction perpendicular to the camber line is 15 units and the velocity induced by the vortex sheet is 4 units at a point. The angle of attack for the thin airfoil is α. Then which of the following condition is true in case of thin airfoil theory?

Incompressible Flow over Airfoils topics include: Airfoil nomenclature and characteristics, vortex sheet, kutta condition, kelvin’s circulation theorem, symmetric and cambered airfoils, modern low speed airfoils, viscous, laminar and turbulent flows. Incompressible flow over airfoils is important for understanding airflow around airfoils. This helps determine the best materials and shapes for wings and propellers for the speed range of the aircraft.  Incompressible flow is a flow where density is constant in both time and space. Although all real fluids are compressible, a flow is often... Show more

Incompressible Flow over Airfoils topics include: Airfoil nomenclature and characteristics, vortex sheet, kutta condition, kelvin’s circulation theorem, symmetric and cambered airfoils, modern low speed airfoils, viscous, laminar and turbulent flows.

Incompressible flow over airfoils is important for understanding airflow around airfoils. This helps determine the best materials and shapes for wings and propellers for the speed range of the aircraft. 

Incompressible flow is a flow where density is constant in both time and space. Although all real fluids are compressible, a flow is often approximated as incompressible if the effect of the density changes cause only small changes to the calculated results. 

Thin airfoil theory is used to analyze incompressible, inviscid flow over airfoils. 
The theory's assumptions are:
Airflow is incompressible
Airflow is inviscid
Airfoil has infinite length
Airfoil has zero thickness 

The theory's equation is: C= 2πα
Where:
CLis the coefficient of lift
α is the angle of attack 

The theory's assumptions eliminate the possibility of drag.

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