The half-thickness of the symmetric 4-digit NACA airfoil is Yt where t is the...

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The half-thickness of the symmetric 4-digit NACA airfoil is Yt √ с where t is the maximum actual thickness as a fraction of the chord and c is the chord. = 5 t [0.1 2969 The velocity profile at the chordwise location of maximum thickness of a NACAOOXX (last two digits are unknown) with chord 0.5 m and zero AOA is น U₂ 0.126 €/ 0.3515 (2)² +0.2843 (²)³ - - 0.1015 (2) ¹], 2 3 25 { # (+)-1()* ()*+#()* ( * ) − 1 ( ² ) ² − 7 ( 4 ) ³ + 11 ( 1 ) ² for y₁ < 5 12 = 1 for yw > S (Note: yw is the distance from the wall and 5 = 0.014 (x/c)1/2 m) Part A: What are the boundary layer displacement thickness, o, and the momentum thickness, 0 at the given chordwise location (i.e., the location of maximum actual thickness)? Assume constant density. Displacement Thickness: Momentum Thickness: 0 = XX = m m Part B: Knowing that the effective thickness at the given chordwise location is 94.54 mm, find the last two digits of the NACA airfoil designation. Note that t = XX/100. The half-thickness of the symmetric 4-digit NACA airfoil is Yt √ с where t is the maximum actual thickness as a fraction of the chord and c is the chord. = 5 t [0.1 2969 The velocity profile at the chordwise location of maximum thickness of a NACAOOXX (last two digits are unknown) with chord 0.5 m and zero AOA is น U₂ 0.126 €/ 0.3515 (2)² +0.2843 (²)³ - - 0.1015 (2) ¹], 2 3 25 { # (+)-1()* ()*+#()* ( * ) − 1 ( ² ) ² − 7 ( 4 ) ³ + 11 ( 1 ) ² for y₁ < 5 12 = 1 for yw > S (Note: yw is the distance from the wall and 5 = 0.014 (x/c)1/2 m) Part A: What are the boundary layer displacement thickness, o, and the momentum thickness, 0 at the given chordwise location (i.e., the location of maximum actual thickness)? Assume constant density. Displacement Thickness: Momentum Thickness: 0 = XX = m m Part B: Knowing that the effective thickness at the given chordwise location is 94.54 mm, find the last two digits of the NACA airfoil designation. Note that t = XX/100.