Experiments with an airfoil model on which the boundary layers are controlled without the use of supplementary equipment

Description:

This report describes test made in the Variable Density Wind Tunnel of the NACA to determine the possibility of controlling the boundary layer on the upper surface of an airfoil by use of the low pressure existing near the leading edge. The low pressure was used to induce flow through slots in the upper surface of the wing. The tests showed that the angle of attack for maximum lift was increased at the expense of a reduction in the maximum lift coefficient and an increase in the drag coefficient.

Creator(s): Abbott, I H
Creation Date: April 1, 1931
Partner(s):
UNT Libraries Government Documents Department
Collection(s):
National Advisory Committee for Aeronautics Collection
Technical Report Archive and Image Library
Usage:
Total Uses: 57
Past 30 days: 2
Yesterday: 0
Creator (Author):
Date(s):
  • Creation: April 1, 1931
Description:

This report describes test made in the Variable Density Wind Tunnel of the NACA to determine the possibility of controlling the boundary layer on the upper surface of an airfoil by use of the low pressure existing near the leading edge. The low pressure was used to induce flow through slots in the upper surface of the wing. The tests showed that the angle of attack for maximum lift was increased at the expense of a reduction in the maximum lift coefficient and an increase in the drag coefficient.

Language(s):
Subject(s):
Contributor(s):
Serial Title: NACA Technical Notes
Partner:
UNT Libraries Government Documents Department
Collection:
National Advisory Committee for Aeronautics Collection
Collection:
Technical Report Archive and Image Library
Identifier:
Resource Type: Report
Format: Text
Rights:
Access: Public
Statement: No Copyright, Unclassified, Unlimited, Publicly available