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Low-speed aerodynamic characteristics of a 9.3-percent-thick supercritical airfoil section
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | McGhee, R. J. Noonan, K. W. |
| Copyright Year | 1982 |
| Description | An investigation was conducted in the Langley low turbulence pressure tunnel to determine the low-speed, two dimensional characteristics of a 9.3 percent-thick supercritical airfoil. The airfoil was tested at Reynolds numbers (based on chord) from 2.9 million to 16.8 million, at Mach numbers from 0.10 to 0.36, and at geometric angles of attack from -8 degrees to 14 degrees. |
| File Size | 37006019 |
| Page Count | 51 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19830002798 |
| Archival Resource Key | ark:/13960/t3hx65m3f |
| Language | English |
| Publisher Date | 1982-08-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Reynolds Number Wind Tunnel Tests Supercritical Wings Aerodynamic Coefficients Angle of Attack Aerodynamic Characteristics Mach Number Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |