ESDU 72024: Aerodynamic characteristics of aerofoils in airflow

Abstract:

ESDU 72024 provides a means of estimating the lift-curve slope at zero lift, zero-lift incidence, zero-lift pitching moment coefficient and chordwise location of the aerodynamic centre for any aerofoil in compressible inviscid airflow from a knowledge of a number of parameters characterising the thickness distribution and camber line shape. The data, which are presented in graphical form, were derived by correlating the results of a large number of calculations obtained from exact theory.

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.

Indexed under:

Details:

Data Item ESDU 72024
Format:	PDF with software with interactive graphs
Status:	Amendment (D), 01 Jan 1999 Published in Release 2000-03 (init)
Previous Releases:	ESDU 72024 Amendment C
ISBN:	978 0 85679 023 2

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This Data Item is complemented by the following software:

Toolbox Apps

Name

Details

Toolbox LiCrA-2D Run

Title

ESDU LiCrA: 2D Lift Curve Aerodynamics for Aerofoils

Version

1.0

Details

LiCrA 2D calculates the maximum lift coefficient, the lift coefficient at zero angle of attack and the lift curve of aerofoil sections with or without high-lift devices deployed at low speeds.

Calculations can be made for the aerofoil when there are no high-lift devices deployed but the prediction of the shape of the non-linear part of the lift curve should be treated with caution because it employs a technique developed for use when high-lift devices are deployed. The method is intended for use only for free-stream Mach numbers up to about 0.25.

Toolbox LiCrA-3D Run

Title

ESDU LiCrA: 3D Lift Curve Aerodynamics for Wings and Wing/Body Combinations

Version

1.0

Details

LiCrA 3D calculates the maximum lift coefficient, the lift coefficient at zero angle of attack and the lift curve of straight-tapered wings with or without high-lift devices deployed at low speeds. The basic wing (no devices deployed) may have camber and twist. The program includes methods that allow for the presence of a fuselage.

For completeness, calculations can be made for the wing when there are no high-lift devices deployed but the prediction of the shape of the non-linear part of the lift curve should be treated with caution because it employs a technique developed for use when high-lift devices are deployed. The method is intended for use only for free-stream Mach numbers up to about 0.25. No allowance is made for ground effect.

If required, it will also calculate the spanwise position of the section of the basic wing that has the peak loading due to angle of attack.

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This Data Item contains 9 interactive graph(s) as listed below.

Graph	Title
Figure 1	Lift-curve slope at zero lift (incompressible flow)
Figure 2	Zero-lift incidence (compressible and incompressible flow)
Figure 3	Zero-lift pitching moment coefficient (incompressible flow)
Figure 4a	Chordwise position of aerodynamic centre (incompressible flow) τ = 10°
Figure 4b	Chordwise position of aerodynamic centre (incompressible flow) τ = 20°
Figure 5	Lift-curve slope (compressible flow)
Figure 6	Zero-lift pitching moment coefficient (compressible flow)
Figure 7	Chordwise position of aerodynamic centre (compressible flow)
Figure 8	Aerofoil thickness at x = 0.005c

ESDU 72024

Aerodynamic characteristics of aerofoils in compressible inviscid airflow at subcritical Mach numbers.