Wind-Tunnel Investigation at Low Speed of a 45 deg Sweptback Untapered Semispan Wing of Aspect Ratio 1.59 Equipped With Various 25-Percent-Chord Plain Flaps
Abstract
A wind-tunnel investigation was made at low speed to determine the aerodynamic characteristics of a 45 deg sweptback untapered semispan wing of NACA 64A010 airfoil section normal to the leading edge and aspect ratio of 1.59 equipped with 25-percent-chord plain unsealed flaps having various spans and spanwise locations. Lift, drag, pitching-moment, and flap hinge-moment data were obtained for the wing with the various flaps deflected up to 60 deg. A comparison is made,with data obtained on the present wing at 0 deg of sweep with an aspect ratio of 3.13. In general, changes in angle of attack, flap deflection, flap span, and spanwise location produced trends in lift, drag, pitching moment, and flap hinge moment that were similar to but of different magnitudes from those for unswept wings. Existing empirical and theoretical methods for predicting the lift effectiveness of flaps of various spans gave very good agreement with the experimental results. Because of the increase in the drag coefficients and the associated decrease in the lift-drag ratio with increasing flap deflection, an advantage may be gained by limiting the flap deflection to moderate angles (about 30 deg), even though the lift coefficients increase slightly with further increases in flap deflection. Flap deflections greater than 30 deg may be desirable, however, when steeper glide-path angles are required.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1950
- Accession Number
- ADA380496
Entities
People
- Harold S. Johnson
- John R. Hagerman
Organizations
- National Aeronautics and Space Administration