ESDU 14004:2014

$89.05

Lift and rolling moment due to spoilers on wings at subsonic speeds with trailing-edge flaps undeployed

Published By	Publication Date	Number of Pages
ESDU	2014-11-01	68

Guaranteed Safe Checkout

Category: ESDU

If you have any questions, feel free to reach out to our online customer service team by clicking on the bottom right corner. We’re here to assist you 24/7.
Email:[email protected]

Description

ESDU 14004 considers the flat plate (deployed in a plane normal
to the section chord) and flap (pivoting about a hinge) types of
rectangular spoilers on the upper surface of a wing with
trailing-edge flaps undeployed. It discusses the flow behaviour
with variation of spoiler deployment and wing angle of attack, as
well as the effect of spoiler chordwise position on wing lift-curve
slope.

A method is presented for predicting the lift coefficient
increment (usually negative, i.e. a decrement) and rolling moment
coefficient due to spoiler deployment on the upper surface of a
wing at subsonic speeds. The two-dimensional lift coefficient
increment characteristics are first determined, and the
corresponding three-dimensional lift coefficient increment and
rolling moment coefficient characteristics are then deduced.

The method is applicable for any form of porosity (perforations,
hinge-line gaps, spoiler segmentation or edge castellation) up to
0.38 of the spoiler area. Spoiler chordwise locations from 0.4c to
the trailing-edge are covered for spoiler deployment height to wing
chord ratios from 0.04 to 0.15. Spoiler deployment height is
defined as the height above the wing surface and it is the height
of the spoiler trailing-edge above the wing surface in the case of
flap-type spoilers. The method is applicable for both
straight-tapered and cranked wings with spoilers sweptback up to 45
degrees for Mach numbers up to 0.7. Lift increment and rolling
moment behaviour is affected by wing angle of attack, and limits of
applicability for both minimum and maximum angles of attack are
suggested. Sketches comparing predicted data with test data show
that in most cases predictions lie within 0.03 for lift coefficient
increment and within 0.003 for rolling moment coefficient.