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National Advisory Committee for Aeronautics, Report - Summary of Section Data on Trailing Edge High Lift Devices

A summary has been made of available data on the charac-
teristics of airfoil sections with trailing-edge high-lift devices.
Data for plain, split, and slotted flaps are collected and analyzed.
The efects of each of the rariables inrolred in the design of the
various types of flap are examined and, in cases where suficient
data are giren, optimum configurations are deduced. Tl’hererer
possible, the ejects of airfoil section, Reynolds number, and
lead Eng-edge roughness are shown. For single and double
slottedfiaps, where a large amount of unrelated data are avail-
able, maximum lift coeficie-nts of many configurations are
presented in tables.

A rather large amount of data on the section aerodynamic
characteristics of trailing-edge flaps has been obtained during
the course of the last several years. Some of the data has
been obtained as a part of a general program on the investiga-
tion of these characteristics; but a large amount, particularly
that obtained during the war, has of necessity been directed
toward the development of high-lift devices for specific air-
planes and, as a result, is generally unrelated to the over-all
program. This report is prepared with a view of collecting
and correlating, insofar as possible, the data that are avail-
able for the purpose of providing a guide for the selection
of the type or size of high-lift device for specific applications
and for showing, if possible, means for predicting the char-
acteristics of configurations which have not been specifically
tested.

In some few cases, the only data available to show the
effects of fundamental flap design parameters were obtained
on rectangular Wings of constant section and of aspect ratio 6.
In all other cases, only section data have been included
in this report, both in an attempt to keep the size of the
report below a reasonable limit- and because of the fact that
the application of the section data to finite span wings can
be considered a separate problem. For this reason, no data
are shown on the eflects of flap tips, on cut—outs, on fuselage
interference, or on slipstream efi'ects. No detailed analyses
have been made. on the effects of the flap characteristics
on the performance of airplanes.