Accession Number:

ADA801134

Title:

Wind-Tunnel Investigation of an NACA 23012 Airfoil with an 18.05-Percent-Chord Maxwell Slat and with Trailing Edge Flaps

Descriptive Note:

Wartime rept.

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

Personal Author(s):

• Gillis, Clarence L.
• McKee, John W.

Report Date:

1941-10-01

Pagination or Media Count:

19.0

Abstract:

An investigation was made to determine the optimum slot gap of he Maxwell slat for and the aerodynamic section characteristics, of the NACA 23012 airfoil with several deflections of a slotted and a split flap. It was found that, for he combinations tested, a slot gap of 0.0175 c was the optimum. This gap appreciably increased the maximum lift coefficient and angle of attack at the stall. The effectiveness of the slat, however, dropped with increasing flap deflection.

Descriptors:

• *FLAPS(CONTROL SURFACES)
• *AIRFOILS
• AERODYNAMIC CHARACTERISTICS
• TRAILING EDGES
• SPLITTING
• LIFT
• COEFFICIENTS
• DEFLECTION
• WIND TUNNEL TESTS

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE