ESDU 83040: Rapid estimation of spanwise loading of wings

Abstract:

ESDU 83040 gives a simple and rapid means of estimating the spanwise loading of a wide range of cambered and twisted wing planforms for unseparated subcritical flow. It is based on lifting-surface theory and extends, to take account of camber and twist, the basic method of ESDU TD Memo 6403 for spanwise loading due to incidence of uncambered and untwisted wings. The effect of camber is treated by considering it as imparting an equivalent incremental twist to the wing. A simple artifice is used to represent the twist distribution by a combination of linear segments. From the linear representation effective values of local twist are devised for use in the method. Spanwise loadings can be estimated either at a given incidence or a given wing lift coefficient. The method is applicable to wing planforms for which the reduced aspect ratio (β A) is in the range 1.5 to 12 and the sweep parameter (Atan Λ_½) is in the range 0 to 6. The wings can have any taper ratio (γ) between 0 to 1 with straight, cranked or curved leading edges, and straight or cranked trailing edges. The method is illustrated by three worked examples.

A computer program, ESDUpac A9510, described in ESDU 95010, is available that calculates the spanwise loadings directly from steady lifting-surface theory using the Multhopp-Richardson solution.

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 83040
Format:	PDF with software with interactive graphs
Status:	Amendment (D), 01 Jan 2013 Published in Release 2013-07 (Jul 2013)
Previous Releases:	ESDU 83040 Amendment C
ISBN:	978 0 85679 455 1

The Data Item document you have requested is available only to subscribers.

Subscribers login here.
If you are not an ESDU subscriber find out how to subscribe.

This Data Item is complemented by the following software:

Toolbox Apps

Name

Details

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.

Programs

Name

Details

ESDUpac A9510

Title	Computer program for estimation of spanwise loading of wings with camber and twist in subsonic attached flow.
Version	1.3

This program is only available to subscribers.

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 8 interactive graph(s) as listed below.

Graph	Title
Figure 1	Theoretical spanwise centre of pressure
Figure 2	Theoretical spanwise centre of pressure
Figure 3	Theoretical spanwise centre of pressure
Figure 4	Theoretical spanwise centre of pressure
Figure 5	Theoretical spanwise centre of pressure
Figure 6	The function F(η, η‾)
Figure 7	The function G(η)
Figure 8	The function H(η)

ESDU 83040

Method for the rapid estimation of spanwise loading of wings with camber and twist in subsonic attached flow.