For NACA 0018 and NACA 23015 airfoils with chord length 800 mm, find the maximum

Question

For NACA 0018 and NACA 23015 airfoils with chord length 800 mm, find the maximum thickness values in mm. (b) Indicate the airfoil numbers from Figure 1 to identify a supercritical airfoil and a supersonic airfoil. (c) on the given graph paper, provide scaled sketches of C_s graphs for a symmetric airfoil and a cambered airfoil taking a from -4 deg to +8 deg on horizontal axis. Take .25 deg for the cambered airfoil. Take the slope, dc/dx 0.11/deg for both airfoils. From your graphs, find c_a for a 6 deg for each airfoil. 2. (a)Take x and z along horizontal and vertical axes, consider vortex filaments N1 and N2 located at x .6m and 10 m respectively. The respective vortex strengths are ri 12 miles and 6 m2/s. At any given point, the respective induced velocity vectors are vi and v_a Show v_h and v_a at the points (2, 0) and (8, 0). Also show the resultant Induced velocity, V at (2, 0) and (8, 0). (b) Sketch a velocity profile for the flow with V 10 y from y =0 m to y 0.4 m. To make a loop in the flow, sketch a rectangle abcda with |ab| |cd| 0, 5 m; ab along the line y 0.05 m and cd along the line y 0.3 m. Find the circulation around the loop, abcda. 3. (a) Sketch the edge of a vortex sheet from 0 to mc along the same edge, x 0 to x c) to represent a thin symmetric airfoil. Include free stream velocity vector, V at an angle of attack, a radians. Also include induced velocity vector dw (x) due to vortex strength of elemental vortex. Write an in terms of y(E)d Ex and Proceed further to write w an integral expression. Write an equation with the same integral expression Va and provide reasons in support of using va in the equation.

Explanation / Answer

1.

(a) NACA 0018, Chord length = 800 mm

Max. thickness = 0.18 x 800 mm = 144 mm

NACA 23015

Maximum thickness = 0.15 x 800 mm =120 mm

(b). 293 is Supersonic & 392 is super critical airfoil

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