The coefficient of lift of a wing can be calculated using theequation:

where:

L = the lift force produced by the wing = 5.8 ? 0.1 N

? = the density of air = 1.2 ? 0.06 kg/m3

v = the velocity of the air flowing over the wing = 17.2 ? 0.4m/s

A = the wing platform area = 9.17 x 10^-2 ? 0.3 x 10^-2 m^2

(a) Determine the nominal value of CL. This is the value of CLthat is calculated from the measured values.

(b) Calculate the potential error in CL by calculating themaximum possible CL, taking into account the potential variances inthe measurements. Be careful to choose the correct ? error,depending on if the parameter is in the numerator ordenominator.

(c) Use the Taylor Series-derived first order error propagationformula to calculate the potential error in CL.

Transcribed Image Text:

CL L 0.5 x pv2 x A x ΧΑ CL L 0.5 x pv2 x A x ΧΑ

Answer rating: 100% (QA)

Answer a The nominal value of the coefficient of lift CL can be calculated using the given equation ... View the full answer