INVESTIGATION OF PROPELLER SLIPSTREAM EFFECTS ON WING PERFORMANCE
Abstract
A theoretical and experimental study was conducted to determine the effects of propeller slipstream on wing performance. Previously developed theoretical analyses were expanded and modified to account for radial variation of the propeller slipstream velocity. The experimental program consisted of wind tunnel tests conducted with a motor-propeller system mounted on a semispan wing model. The wing model utilized has a chord to propeller diameter of 0.46, an aspect ratio of 6.37 (3.18 for semispan), a taper ratio of 1.0, and a NACA 0015 airfoil section. The wing model has eight floating wing segments with and without a 45-degree simulated split flap. Located within each floating wing segment is a three-component strain gage balance to provide measurements of lift, drag, and pitching moment. The measurements of total wing lift, drag, and pitching moment were obtained with the six-component main wind tunnel balance. The test data obtained included the effects of the variation of propeller slipstream velocity by utilizing two propellers of different geometries. Propeller rotation for all tests was down at the wing tip. The experimental and theoretical results are compared; in general, good correlation is observed.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1967
- Accession Number
- AD0666247
Entities
People
- E. Kisielowski
- M. George