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The surface of many airfoils can be described with an equation of the form xa₁x y ‚ = + 0 = ₂2 [²₁ √²/² + tc ±[ao, 0.2 arx + a₂ (²)² + α3 (²)³ + α₁ (²) * Where t is the maximum thickness as a fraction of the chord length (tmax = ct). Given that c=1 m and t=0.2 m, the following values for y have been measured for a particular airfoil: X (m) 0.18 0.33 0.53 0.74 0.88 Y(m) 0.08409 0.0954 0.05823 0.06507 0.03001 Determine the constants ao, a₁, az, az and a4. 3₁ Thickness Ipa

The surface of many airfoils can be described with an equation of the form xa₁x y ‚ = + 0 = ₂2 [²₁ √²/² + tc ±[ao, 0.2 arx + a₂ (²)² + α3 (²)³ + α₁ (²) * Where t is the maximum thickness as a fraction of the chord length (tmax = ct). Given that c=1 m and t=0.2 m, the following values for y have been measured for a particular airfoil: X (m) 0.18 0.33 0.53 0.74 0.88 Y(m) 0.08409 0.0954 0.05823 0.06507 0.03001 Determine the constants ao, a₁, az, az and a4. 3₁ Thickness Ipa

Advanced Engineering Mathematics
Advanced Engineering Mathematics
10th Edition
ISBN:9780470458365
Author:Erwin Kreyszig
Publisher:Erwin Kreyszig
Chapter2: Second-order Linear Odes
Section: Chapter Questions
Problem 1RQ
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The surface of many airfoils can be described with an equation of the form 3 tc y = +6²₂ [²√²+² xa₁x + a₂ 2 (²) ²³. + az ²3 (²) ³² + ²₂ (²) * ¹ a₁ 0.2 Where t is the maximum thickness as a fraction of the chord length (tmax = ct). Given that c=1 m and t=0.2 m, the following values for y have been measured for a particular airfoil: X (m) 0.18 0.33 0.53 0.74 0.88 Y(m) 0.08409 0.0954 0.05823 0.06507 0.03001 Determine the constants ao, a₁, az, a3 and a4. 3² Thickness leva
Transcribed Image Text:The surface of many airfoils can be described with an equation of the form 3 tc y = +6²₂ [²√²+² xa₁x + a₂ 2 (²) ²³. + az ²3 (²) ³² + ²₂ (²) * ¹ a₁ 0.2 Where t is the maximum thickness as a fraction of the chord length (tmax = ct). Given that c=1 m and t=0.2 m, the following values for y have been measured for a particular airfoil: X (m) 0.18 0.33 0.53 0.74 0.88 Y(m) 0.08409 0.0954 0.05823 0.06507 0.03001 Determine the constants ao, a₁, az, a3 and a4. 3² Thickness leva
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