Accession Number:

AD0405150

Title:

INVESTIGATION OF DRAG REDUCTION BY BOUNDARY LAYER SUCTION ON A 72.5-DEG SWEPT WIND AT M 2 AND 2.25

Descriptive Note:

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1963-05-01

Pagination or Media Count:

26.0

Abstract:

Tests were conducted in the 40-Inch Supersonic Tunnel A of the von Karman Gas Dynamics Facility to determine the effectiveness of boundary layer suction for laminar flow control on a two-dimensional, 72.5-deg swept wing having a subsonic leading edge. Test Mach numbers were 2 and 2.25 with a Reynolds number range based on wing chord from 3 to 14 million for angles of attack of 0.15, 0.45, and 0.75 deg. With suction, full chord laminar flow was maintained at M 2, alpha 0.15, 0.45, and 0.75 deg up to a length Reynolds number of approximately 9 million. At M 2.25 and alpha 0.15 deg, full chord laminar flow was maintained up to a Reynolds number of 6.5 x 10 to the 6th power and for alpha 0.45 and 0.75 deg, up to a Reynolds number of 3 x 10 to the 6th power. Selected data are presented.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE