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A low speed wind tunnel investigation of reynolds number effects on a 60-deg swept wing configuration with leading and trailing edge flaps
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Hoffler, Keith D. Rao, Dhanvada M. |
| Copyright Year | 1988 |
| Description | A low-speed wind tunnel test was performed to investigate Reynolds number effects on the aerodynamic characteristics of a supersonic cruise wing concept model with a 60-deg swept wing incorporating leading-edge and trailing-edge flap deflections. The Reynolds number ranged from 0.3 to 1.6 x 10 to the 6th, and corresponding Mach numbers from .05 to 0.3. The objective was to define a threshold Reynolds number above which the flap aerodynamics basically remained unchanged, and also to generate a data base useful for validating theoretical predictions for the Reynolds number effects on flap performance. This report documents the test procedures used and the basic data acquired in the investigation. |
| File Size | 1746624 |
| Page Count | 69 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19880016057 |
| Archival Resource Key | ark:/13960/t1gj4cw0n |
| Language | English |
| Publisher Date | 1988-08-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Aerodynamic Configurations Swept Wings Leading Edge Flaps Deflection Reynolds Number Low Speed Wind Tunnels Trailing Edge Flaps Aerodynamic Characteristics 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 |
