ESDU 84026
Aerofoil maximum lift coefficient for Mach numbers up to 0.4.
Abstract:
ESDU 84026 provides a simple empirically derived method for estimating maximum lift coefficient. The method predicts the increment in lift coefficient by which the maximum exceeds the value at zero incidence, and a prediction method for lift coefficient at zero incidence is included. Graphs of the increment show its variation with aerofoil geometry and Reynolds number for aerofoils with smooth or rough leadingedges; rough here would cover ice formation while smooth includes the level of roughness required just to fix transition. A further empirical factor is provided to extend the method to apply to modern aerofoils with rear loading. The accuracy is assessed in terms of the standard deviation of prediction from experiment for nearly 500 points, subdivided by aerofoil type, leadingedge condition and Reynolds number. The overall standard deviation was about 0.08. The method is programmed as part of ESDUpac A9315, see ESDU 93015.A computer program of the method is included as part of ESDU LiCrA Toolbox apps and ESDUpacs A9931 and B9931 from (ESDU 99031). See the 'Software' tab, above.
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Data Item ESDU 84026  

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This Data Item contains 7 interactive graph(s) as listed below.
Graph  Title 

Figure 1  Lift coefficient increment for aerofoils with smooth leading edges z_{u1.25} / c < 0.017 
Figure 2  Lift coefficient increment for aerofoils with smooth leading edges z_{u1.25} / c ≥ 0.017 
Figure 3  Lift coefficient increment for aerofoils with rough leading edges z_{u1.25} / c < 0.017 
Figure 4  Lift coefficient increment for aerofoils with rough leading edges z_{u1.25} /c ≥ 0.017 
Figure 5  Factor on C_{Lm} for modern aerofoils 
Figure 6  Parameter in equation (7.1) 
Figure 7  Parameter in equation (7.1) 