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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
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.
Distribution Statement:
APPROVED FOR PUBLIC RELEASE