Loading...
Please wait, while we are loading the content...
Off-design reynolds number effects for a supersonic transport
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Owens, Lewis R. Rivers, S. Melissa Wahls, Richard A. |
| Copyright Year | 2005 |
| Description | A high Reynolds number wind tunnel test was conducted to assess Reynolds number effects on the aerodynamic performance characteristics of a realistic, second-generation supersonic transport concept. The tests included longitudinal studies at transonic and low-speed, high-lift conditions across a range of chord Reynolds numbers (8 million to 120 million). Results presented focus on Reynolds number and static aeroelastic sensitivities at Mach 0.30 and 0.90 for a configuration without a tail. Static aeroelastic effects, which mask Reynolds number effects, were observed. Reynolds number effects were generally small and the drag data followed established trends of skin friction as a function of Reynolds number. A more nose-down pitching moment was produced as Reynolds number increased because of an outward movement of the inboard leading-edge separation at constant angles of attack. This study extends the existing Reynolds number database for supersonic transports operating at off-design conditions. |
| File Size | 7025066 |
| Page Count | 38 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20080001722 |
| Archival Resource Key | ark:/13960/t4gn35m6z |
| Language | English |
| Publisher Date | 2005-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Pitching Moments Drag Reynolds Number Wind Tunnel Tests Angle of Attack Supersonic Transports Aeroelasticity 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 | Article |
