In aircraft design, the pressure coefficient Cp is usually measured during wind tunnel testing of an aircraft component to predict structural loads, as well as lift and drag forces. Let Cp=(p−p[infinity])/ (0.5*rhoU[infinity]^2)where U[infinity] is the airspeed of the test at pressure p[infinity] and using a fluid of density rho. The pressure difference p ‐ p[infinity] is measured directly where p is the pressure located at a point on the surface of the test component. Estimate the uncertainty in Cp under the following conditions: Δp = p − p[infinity] = 1,000 N/m2, uΔp = 15 N/m2; rho = 1.20 kg/m3, urho = 0.01 kg/m3; U[infinity] = 50.0 m/s, u_U[infinity] = 0.21 m/s. Assume 95% confidence in stated values.