Consider a NACA 1412 airfoil at an angle of attack of 4 ∘. If the free-stream Mach number is 0.8, calculate the lift coefficient. Refer to the Appendix graph given below for standard values. The lift coefficient is

Consider the data for the NACA 2412 airfoil given in the figure below. Calculate the lift and moment about the quarter chord (per unit span) for this airfoil when the angle of attack is 8º and the freestream is at the standard sea level conditions with a velocity of 25m/s. The chord of this airfoil is 0.8m. NACA 2412 airfoil Eq.

The airfoil section of the wing of the British Spitfire of World War II fame is an NACA 2 2 1 3 at the wing root, tapering to an NACA 2 2 0 5 at the wing tip. The root chord is 8. 3 3 ft . The measured profile drag coefficient of the NACA 2 2 1 3 airfoil is 0. 0 0 6 at a Reynolds number of 9 × 1 0 6. Consider the Spitfire ...

Consider again the NACA 2412 airfoil discussed in Problem 4.10. The airfoil is flying at a velocity of 60 m/s at a standard altitude of 3 km (see Appendix D). The chord length of the airfoil is 2 m. Calculate the lift per unit span when the angle of attack is 4°

A light airplane uses a NACA 4415 airfoil. It has a rectangular wing planform, with an area of 15.3 m2 and a span of 10.2 m. The aircraft is flying at a gross weight of 7340 N. (a) Neglecting any finite wing effects induced drag) and assuming sea level conditions, at what angle of attack will the aircraft be flying when its airspeed is 160 km/h?

Question: Consider an NACA 2412 airfoil (the meaning of the number designations for standard NACA airfoil shapes is discussed in Chapter 4).

The airfoil data in Appendix D were obtained in the NACA two-dimensional Low Turbulence Pressure Tunnel at the NACA Langley Memorial Laboratory. This facility went into operation in Spring 1941. The tunnel was especially designed for …

Question: 1.6 Consider an NACA 2412 airfoil (the meaning of the number designations for standard NACA airfoil shapes is discussed in Chapter 4). The following is a tabulation of the lift, drag, and moment coefficients about the quarter chord for this airfoil, as a function of angle of attack. a (degrees) -2.0 0 2.0 4.0 са 0.006 0.006 0.006 0. ...

For the NACA 2412 airfoil, the lift coefficient and moment coefficient about the quarter-chord at -6° angle of attack are -0. 39 and -0. 045, respectively. At 4°. angle of attack, these coefficients are 0.65 and -0. 037, respectively. Calculate the location of the aerodynamic center. (10 %)

For the NACA 2412 airfoil, the lift coefficient and moment coefficient about the quarter-chord at -6° angle of attack are -0.39 and -0.045, respectively. At 4° angle of attack, these coefficients are 0.65 and -0.037, respectively. Calculate the location of the aerodynamic center. (Round the final answer to three decimal places.)