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Experimental surface pressure data obtained on 65 deg delta wing across reynolds number and mach number ranges. vol. 4: large-radius leading edge
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Chu, Julio Luckring, James M. |
| Copyright Year | 1996 |
| Description | An experimental wind tunnel test of a 65 deg delta wing model with interchangeable leading edges was conducted in the Langley National Transonic Facility (NTF). The objective was to investigate the effects of Reynolds and Mach numbers on slender-wing leading-edge vortex flows with four values of wing leading-edge bluntness. Experimentally obtained pressure data are presented without analysis in tabulated and graphical formats across a Reynolds number range of 6 x 10(exp 6) to 120 x 10(exp 6) at a Mach number of 0.85 and across a Mach number range of 0.4 to 0.9 at Reynolds numbers of 6 x 10(exp 6) and 60 x 10(exp 6). Normal-force and pitching-moment coefficient plots for these Reynolds number and Mach number ranges are also presented. |
| File Size | 13611064 |
| Page Count | 599 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19960020459 |
| Archival Resource Key | ark:/13960/t82k1cc29 |
| Language | English |
| Publisher Date | 1996-02-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Static Pressure Pitching Moments Subsonic Speed Radii Transonic Wind Tunnels Reynolds Number Pressure Distribution Strain Gages Aerodynamic Coefficients Aerodynamic Forces Slender Wings Vortices Delta Wings Cryogenics Wind Tunnel Tests Pressure Measurement Angle of Attack Blunt Leading Edges Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
