es pressure drag on a well designed aerofoil?
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- Which of these are asymmetrical airfoil?answer with FOUR decimal places on final answer, and in scientific notation for less than 1 values. Include the units on the answer. Question NACA 664-221 Chord c = 150 cm 1) What is the CL range to achieve the minimum coefficient of drag? 2) What is the thickness ratio of the airfoil?True or False: Flow over conventional airfoils are highly viscous at lower angles of attack
- Consider an airfoil at 12◦ angle of attack. The normal and axial forcecoefficients are 1.2 and 0.03, respectively. Calculate the lift and dragcoefficients.Describe the downwash angle of a finite span wing and induced drag coefficient!What is an asymmetrical airfoil?( is it positive camber or negative camber)
- Calculate the lift and moment coefficients using thin airfoil theory approximations for a range of angle of attacks for the following airfoils below. 1. NACA 0008 2. NACA 0018 3. AG04 4. Clark-Y 5. NACA 2415 Angle of attacks taken to be between 0 degree to 15 degree. Also calculate value of Cm at quarter chord. (Cm at 0.25c) for each. Reynolds number 1000000Discuss and comment on the effect of drag polar for Re 5003352.discuss various designs of winglets to reduce induced drag.