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 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.Indexed under:
Details:
| Data Item ESDU 84026 | |
|---|---|
| Format: |
|
| Status: |
|
| Previous Releases: | |
| ISBN: |
|
The Data Item document you have requested is available only to subscribers or purchasers.
- Subscribers login here.
- If you are not an ESDU subscriber you can
- find out how to subscribe, or
- purchase this Data Item from the IHS Standards Store.
The graphs listed below are available only to subscribers.
- Subscribers login here.
- If you are not an ESDU subscriber find out how to subscribe.
This Data Item contains 7 interactive graph(s) as listed below.
| Graph | Title |
|---|---|
| Figure 1 | Lift coefficient increment for aerofoils with smooth leading edges zu1.25 / c < 0.017 |
| Figure 2 | Lift coefficient increment for aerofoils with smooth leading edges zu1.25 / c ≥ 0.017 |
| Figure 3 | Lift coefficient increment for aerofoils with rough leading edges zu1.25 / c < 0.017 |
| Figure 4 | Lift coefficient increment for aerofoils with rough leading edges zu1.25 /c ≥ 0.017 |
| Figure 5 | Factor on CLm for modern aerofoils |
| Figure 6 | Parameter in equation (7.1) |
| Figure 7 | Parameter in equation (7.1) |