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Effects of forward contour modification on the aerodynamic characteristics of the NACA 641-212 airfoil section
- Publication Year :
- 1975
- Publisher :
- United States: NASA Center for Aerospace Information (CASI), 1975.
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Abstract
- Two different forward contour modifications designed to increase the maximum lift coefficient of the NACA 64 sub 1-212 airfoil section were evaluated experimentally at low speeds. One modification consisted of a slight droop of the leading edge with an increased leading-edge radius; the other modification incorporated increased thickness over the forward 35 percent of the upper surface of the profile. Both modified airfoil sections were found to provide substantially higher maximum lift coefficients than the 64 sub 1-212 section. The drooped leading-edge modification incurred a drag penalty of approximately 10 percent at low and moderate lift coefficients and exhibited a greater nosedown pitching moment than the 64 sub 1-212 profile. The upper surface modification produced about the same drag level as the 64 sub 1-212 section at low and moderate lift coefficients and less nosedown pitching moment than the 64 sub 1-212 profile. Both modified airfoil sections had lower drag coefficients than the 64 sub 1-212 section at high lift coefficients.
- Subjects :
- Aerodynamics
Subjects
Details
- Language :
- English
- Database :
- NASA Technical Reports
- Notes :
- RTOP 505-10-12
- Publication Type :
- Report
- Accession number :
- edsnas.19750022938
- Document Type :
- Report