ESDU 14005:2014

$89.05

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

Published By	Publication Date	Number of Pages
ESDU	2014-11-01	83

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Category: ESDU

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Description

ESDU 14005 provides an empirical method of predicting the lift
coefficient increment (usually negative, i.e. a decrement) and
rolling moment coefficient due to upper-surface spoiler deployment
on a wing at subsonic speed with trailing-edge flaps deployed.

The method predicts the additional lift coefficient increment
over that obtained when the spoiler is deployed on the wing with
flaps undeployed (calculated using ESDU 14004). The corresponding
change in rolling moment coefficient due to a spoiler deployed on
one semi-span wing panel when flaps are deployed can then be
determined. The method of ESDU 14005 is used in conjunction with
that of ESDU 14004 to obtain the total lift coefficient increment
and total rolling moment coefficient due to spoiler deployment on
wings with deployed flaps.

The method of ESDU 14005 applies to plain, single- or
double-slotted flaps having flap/wing chord ratio of 0.2 to 0.4
with flap deployment angles up to 60° and the same range of wing
planform and spoiler parameters as the method of ESDU 14004. It
applies for practical Reynolds numbers and Mach numbers up to 0.29
for wings with or without venting from the lower to upper surface.
Sketches comparing predicted data with test data show that in most
cases predictions lie within 0.1 for total lift coefficient
increment and within 0.01 for total rolling moment coefficient.
Some guidance is included on the effect of lower-surface venting
which can increase spoiler effectiveness by 30 per cent for
flap-type spoilers with large deflection angles. Two worked
examples illustrate the use of the method.