Investigation of flow separation on a two-dimensional flat plate haveing a variable-san trailing-edge flap at M [free stream] = 3 and 5 /
by S.R. Pate.

Description

Main Author

Pate, S. R.

Related Names

ARO, Inc.
Arnold Engineering Development Center
United States. Air Force.

Language(s)

English

Published

Arnold Air Force Station, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1964.

Subjects

Laminar boundary layer.
Trailing edges (Aerodynamics)
Trailing edge flaps.

Summary

An experimental investigation of separated boundary-layer flow was conducted on a two-dimensional flat plate having a variable-span trailing edge flap in the 12-in. Supersonic Tunnel (D) of the von Karman Gas Dynamics Facility. The tests were made at Mach numers 3 and 5 at zero angle of attack and over a Reynolds number range (based on plate length) from 0.26 to 16.7 x 10 to the 6th power. Model surface pressure distributions, schlieren photographs, and velocity distributions are presented. The effects of unit Reynolds number, plate length, flap span, and flap deflection angle on the separated region are investigated, and comparisons are made with existing theory.

Note

"March 1964."

Physical Description

43 pages : illustrations, 28 cm

Locate a Print Version

Find in a library

Viewability