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Question: please help i need help with the naca 4412 airfoil...

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Please Help.!! I need help with the NACA 4412 airfoil problem which is the 2nd picture.!! First picture is just info for the 2nd Problem which i need help with.!! Please show all steps and calculations.!! Thank you.!! U may need to download XLRF5 (which is free) to just show the CL vs alpha graphs.!! Thank U.!!

Homework Problem 1.2A 100 km/hr Pa= 101 kPa To = 15C The production car of problem 1.1 was purchased by a high school student who is a racing enthusiast. He decides to make his own rear wing using an aluminum flat plate and two pieces of round tubing. The flat plate is 2 m wide (span) by 0.3 m long (chord). The pieces of round tubing are 3 cm in diameter and 0.3 m tall. A) Come up with an estimate for the additional dras (in newtons) caused by using this rear wing. As a first order approximation, assume the cylinder and plate are seeing the freestream velocity and that the plate is at zero angle of attack. Assume a fully turbulent boundary layer on the plate. B) Compare the drag of the cylinder supports to the plate alone. What % of the drag of the wing and supports is attributed to the supports. C) Now you have better data for the velocity near the flat plate wing. By using a pitot probe, you have found that the velocity at the wing location is actually about 80% of freestream and that the average velocity on the cylinder supports is actually about 50% of freestream. Now generate a new estimate for the drag (newtons) caused by the cylinder supports and wing.
plate for a rear wing. He his new rectaninss performance at the top speed for the car. If the chord of the wing is ncoduction car of problem 1.2 has realized his error in choosing a flat lar wing design. You are now asked in as a consultant to help with The owner of the He has reviewed the literature and chosen a NACA 4412 airfoil for prodicting tihs time and the top speed U 200 km/hr (P.-101 kPa, and T.- 15 C) this time ar t0 be l m the supplied data given from Abbott and VonDoenhoff (2-D), what is the imum lift coefficient (C max) and at what angle of attack does this expected escur ? What is the drag coefficient (C) and pitching moment coefficient at max Cmais he drat -scure the slope of the G vs α curve over the linear portion of the graph and max lift (Cmou)? compare tothe theoretical value of 2,trad, how do they compare-use % difference ? make a plot of CL versus α for a wing (3-D) of span 2m with endplates of C) Now Im (h I m). Note that the angle of attack for zero lift is negative. Recall the lift curve. Assu compare (2-D). that the relations we developed in class are only valid over the linear portion of me an elliptic plan form. Plot G vs α on the same graph and D) Assuming the values for Ci are invariant with regards to Reynolds number over the linear portion of the lift curve, make a plot of downforce generated (in N) versus speed for the 3-D wing of part C).Use three angles of attack: 0,6, and 12 degrees and use a speed range of 0 to 120 kph. E) For the 6 degree angle of attack, derive an equation for the total drag on the wing as a function of speed. For the 2-D (Profile) drag data use the Reynolds number case corresponding closest to the top speed. F) If the wing is at a 6 degree angle of attack, calculate and plot the additional forces at the wheels (front and rear pairs) due to the wing (a statics problem !). Dimensions are to the c/4 location on the wing. Assume the 2-D pitching moment coefficient is valid for the 3-D wing. The car is rear wheel drive and traveling at 150 Kph. 2 m AT 2.8 m
3 6 20036 3 2 0032 2.8 2.4 0024 0.020 2.0 1.6 1.2 0 8 0016 0012 o.008 0 004 0.4 0.1 -0.4 ac position 0.2 -02 -0.8 o 30x 10 0245 0068 0.246 0.05 0247 0041 Standard roughness 1- 0.3 03 o 6.0 9.0 à 6.0 -0.4 -04 1.6 0 20e simulated split flap deflected 60 96.0 0.5 0 5 -32 24 -16 -8 08 16 24 32 Section angle of attack ao. deg 1.6 -1.2 -08 0.4 0 04 08 12 16 Section lift coefficient. C Aerodynamic characteristics of the NACA 4412 airfoil.
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