Wind-Tunnel Investigation of Control-Surface Characteristics. 8 - A Large Aerodynamic Balance of Two Nose Shapes Used with a 30-Percent-Chord Flap on an NACA 0015 Airfoil
Abstract
Force tests in two-dimensional flow have been made in the NACA 4- by 6-foot vertical tunnel of the characteristics of an NACA 0015 airfoil with a balanced flap having a chord 30 percent of the airfoil chord, a flap-nose overhang 50 percent of the flap chord, and a tab having a chord 20 percent of the flap chord. The results are presented in the form of aerodynamic section characteristics for a sealed and an unsealed gap at the flap nose. The slope of the lift curve and the lift effectiveness of the balanced flap were slightly less than those for the NACA 0009 airfoil with the same flap. The aerodynamic balance of 50 percent of the flap chord caused overbalance through some range of deflections for both nose shapes tested with gaps sealed and unsealed. The blunt nose shape was more effective in reducing hinge moments than the medium nose shape. Unsealing the gap at the nose of the flap caused a decrease in the slope of the lift curve and an increase in the effectiveness of the balance for both nose shapes.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1942
- Accession Number
- ADA801376
Entities
People
- Clarence L. Gillis
- Richard I. Sears
Organizations
- National Advisory Committee for Aeronautics