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The normal force is ___ x 10<sup>5</sup> N. (Round the final answer to three decimal places.)
Consider an infinitely thin flat plate with a 1 m chord at an angle of attack of 10° in a supersonic flow. The pressure and shear stress
distributions on the upper and lower surfaces are given by p<sub>u</sub> = 4 × 10<sup>4</sup>(x-1)<sup>2</sup> +5.4 x 10<sup>4</sup>, p<sub>l</sub>= 2 x 10<sup>4</sup>(x-1)<sup>2</sup> +1.73 × 10<sup>5</sup>, τ<sub>u</sub>=
288x<sup>-0.2</sup>, and Ï„<sub>l</sub>= 761x<sup>-0.2</sup>, respectively, where x is the distance from the leading edge in meters and p and Ï„ are in newtons per
square meter. Calculate the normal and axial forces, the lift and drag, moments about the leading edge, and moments about the
quarter chord, all per unit span. Also, calculate the location of the center of pressure.
The axial force is ___ N. (Round the final answer to nearest whole number.)
eBook
The lift is ___ x 10<sup>5</sup> N. (Round the final answer to three decimal places.)
The drag is ___ x 10<sup>4</sup> N. (Round the final answer to three decimal places.)
Hint
The moment about the leading edge is ___ x 10<sup>4</sup> Nm. (Round the final answer to three decimal places. Include a minus sign if
necessary.)
Print
The moment about the quarter chord is ___ x 10<sup>4</sup> N/m. (Round the final answer to three decimal places. Include a minus sign if
necessary.)
References
The location of the center of pressure is ___ m. (Round the final answer to three decimal places.)