ESDU 70011
Liftcurve slope and aerodynamic centre position of wings in inviscid subsonic flow.
Abstract:
ESDU 70011 presents data for the liftcurve slope and aerodynamic centre position for wings with straight leading and trailingedges and streamwise tips in subsonic flow. The data were derived from liftingsurface theory and are presented in carpet form for βA up to 12, A tanΛ _{½} up to 6 and taper ratio (λ) from 0 to 1, where A is aspect ratio, β is (1  M^{2})^{½} where M is Mach number, and Λ_{½} is the halfchord sweep. The data can be applied to other than straighttapered planforms by means of the equivalent wing planform concept (ESDU 76003 or ESDU 76015). Comparisons with a wide range of test data indicate that the liftcurve slope of wings on wingbody combinations is predicted to within about 5% and that aerodynamic centre position is predicted generally to within 0.03 of the aerodynamic mean chord.A computer program of the method (ESDUpac A7011) is provided and includes an extension to cover wings with modestly swept forward halfchord lines.
For information, an improved form of the HelmboldDiederich equation for wing liftcurve slope is given which provides predictions largely within ±2% of the values obtained from this Data Item for βA ≥ 1.5.
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Data Item ESDU 70011  

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ESDUpac A7011 
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This Data Item contains 12 interactive graph(s) as listed below.
Graph  Title 

Figure 1a  Lift Curve Slope λ = 0 
Figure 1b  Lift Curve Slope λ = 0.125 
Figure 1c  Lift Curve Slope λ = 0.25 
Figure 1d  Lift Curve Slope λ = 0.5 
Figure 1e  Lift Curve Slope λ = 1 
Figure 2a  Aerodynamic Centre A tan Λ_{1/2} = 0 
Figure 2b  Aerodynamic Centre A tan Λ_{1/2} = 1 
Figure 2c  Aerodynamic Centre A tan Λ_{1/2} = 2 
Figure 2d  Aerodynamic Centre A tan Λ_{1/2} = 3 
Figure 2e  Aerodynamic Centre A tan Λ_{1/2} = 4 
Figure 2f  Aerodynamic Centre A tan Λ_{1/2} = 5 
Figure 2g  Aerodynamic Centre A tan Λ_{1/2} = 6 
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