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Low-speed aerodynamic characteristics of airfoil sections with rounded trailing edges in forward and reverse flow
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | McGhee, R. J. Beasley, W. D. |
| Copyright Year | 1974 |
| Description | Low-speed wind-tunnel tests were conducted to determine the two-dimensional aerodynamic characteristics of 6-, 12-, and 18-percent-thick airfoil sections with rounded trailing edges in both forward and reverse flow. The shapes incorporated camber with both the leading and trailing edges rounded to provide reasonable aerodynamic performance with either edge directed toward the free-stream flow. The tests were conducted with the airfoils in both normal and reverse orientations relative to the free stream. The Mach number was varied from 0.16 to 0.36 and the angle of attack was varied from minus 10 to 24 million. Reynolds number, based on the airfoil chord, was varied from about 1.0 to 12.0 million. |
| File Size | 5352710 |
| Page Count | 104 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19740025317 |
| Archival Resource Key | ark:/13960/t7tn20g36 |
| Language | English |
| Publisher Date | 1974-09-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Subsonic Speed Reversed Flow Aerodynamic Configurations Airfoil Profiles Trailing Edges Wind Tunnel Tests Airfoils Two Dimensional Flow Free Flow Aerodynamic Characteristics Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
