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Uncertainty analysis in aerofoil! Help!
Wind tunnel experiment using a constant velocity to determine Cl, Cd and Cm at different angle of attack (-5, 0, 5, 10, 15) of a symmetric airfoil. Error analysis of the experimental investigation to asses uncertainties in Cd, Cl, Cm and express the uncertainties in terms of %total error.
Cl Cd Cm
-0.313179134 || -0.013358668 || -0.064538757 (AOA= -5)
0.092060251 || -0.009305424 || -0.07130352 (AOA= 0)
0.55759136 || 0.017421587 || -0.089932608 (AOA= 5)
0.836392744 || 0.065190563 || -0.057779321 (AOA= 10)
1.048609998 || 0.119631326 || -0.024041582 (AOA= 15)
Cl, Cd, Cm were calculated from the lifts and drag (using trapezoidal rule) obtained for each location .but no idea about error analysis.
Need help on error analysis. How to do an error analysis to find the uncertainty?? Don't have any other previous experimental values.
Homework Statement
Wind tunnel experiment using a constant velocity to determine Cl, Cd and Cm at different angle of attack (-5, 0, 5, 10, 15) of a symmetric airfoil. Error analysis of the experimental investigation to asses uncertainties in Cd, Cl, Cm and express the uncertainties in terms of %total error.
Cl Cd Cm
-0.313179134 || -0.013358668 || -0.064538757 (AOA= -5)
0.092060251 || -0.009305424 || -0.07130352 (AOA= 0)
0.55759136 || 0.017421587 || -0.089932608 (AOA= 5)
0.836392744 || 0.065190563 || -0.057779321 (AOA= 10)
1.048609998 || 0.119631326 || -0.024041582 (AOA= 15)
Homework Equations
Cl, Cd, Cm were calculated from the lifts and drag (using trapezoidal rule) obtained for each location .but no idea about error analysis.
The Attempt at a Solution
Need help on error analysis. How to do an error analysis to find the uncertainty?? Don't have any other previous experimental values.