Wind-Tunnel Investigation of an NACA 23012 Airfoil with an 18.05-Percent-Chord Maxwell Slat and with Trailing Edge Flaps
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1941
- Accession Number
- ADA801134
Entities
People
- Clarence L. Gillis
- John W. Mckee
Organizations
- Langley Research Center