IHS ESDU 84026: Aerofoil maximum lift coefficient for Mach numbers

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 leading-edges; 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, sub-divided by aerofoil type, leading-edge condition and Reynolds number. The overall standard deviation was about 0.08. The method is programmed as part of ESDUpac A9315, see ESDU 93015.

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Details:

Data Item ESDU 84026
Format:	PDF with interactive graphs
Status:	Amendment (C), 01 Jan 1999 Published in Release 2000-03
Previous Releases:	ESDU 84026 Amendment B
ISBN:	978 0 85679 490 2

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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)

ESDU 84026

Aerofoil maximum lift coefficient for Mach numbers up to 0.4.