What will be the location of maximum camber for NACA 13250 with chord length of 2m?īased on NACA -5 digit series, location of maximum camber = (second and third digit)/2 in hundredth of chord from leading edge Thicker airfoils cannot generate required amount of flow characteristics such as critical mach number.ħ. Hence, supersonic airfoils are used to provide required velocity. Let’s consider we need to design supersonic aircraft then, which type of airfoil should be adopted?Ĭlarification: Supersonic aircraft needs to fly at much higher speed. Find the value of drag co-efficient for airfoil.Ĭlarification: Given, Drag = 25N, dynamic pressure q = 10Pa, chord c = 2m. Airfoil has chord of 2m and is experiencing dynamic pressure of 10Pa. An airfoil is such that the drag produced by airfoil is 25N. Hence, for any airfoil induced drag = 0N.ĥ. Hence, there will be no downwash acting on the flow. Determine lift-induced drag by this camber airfoil.Ĭlarification: Given, Lift=200N, velocity = 500m/s.įor cambered airfoil the downwash angle = 0°. A cambered airfoil is operating with 200N of lift. In now days not most people use this terms but at some places it is still in use.Ĥ. However, if both surfaces are curved then, it is called a double cambered airfoil. What do you mean by double cambered airfoil?ī) Airfoil with flat upper and lower surfaceĬ) Airfoil with curved upper and lower surfaceĬlarification: Traditionally, airfoils with only curved upper surface and flat bottom was termed as camber airfoil. Pressure will be the same if AOA is 0° in case of symmetric airfoil.Ģ. This will provide pressure difference which will generate lift force. Pressure on the upper surface is _Ĭlarification: Pressure on the upper surface of an airfoil is lower than that of the lower surface. Aircraft Design Questions on “Airfoil Selection-3”.ġ.

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