Investigation of drag reduction by boundary layer suction on a 50-deg swept tapered wing at M (free-stream) = 2.5 to 4 /
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.
Drag (Aerodynamics)
Airplanes > Airplanes / Wings, Swept-back.

Summary

Tests were conducted in the 40-in. supersonic Tunnel A of the von Karman Gas Dynamics Facility to determine the effectiveness of boundary layer suction for laminar flow control on a tapered, three-dimensional, 50-deg swept supersonic wing. Test Mach numbers were 2.5, 3, 3.5, and 4 with a Reynolds number range (based on boundary-layer rake location) from 4.3 to 19.5 million for angles of attack of zero and =3 deg. Wake drag, suction drag, and total drag coefficients and the corresponding suction coefficients are presented, along with fully turbulent wake drag coefficients for the no-suction case.

Note

"October 1964."

Physical Description

20 pages : illustrations, 28 cm

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