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Effect of leading-edge contour and vertical-tail configuration on the low-speed stability characteristics of a supersonic transport model having a highly-swept arrow wing
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Lockwood, V. E. |
| Copyright Year | 1978 |
| Description | A low-speed investigation was made on a highly-swept arrow-wing model to determine the effect of wing leading-edge contour and vertical-tail configuration on the aerodynamic characteristics in pitch and sideslip. The investigation was made with the trailing-edge flaps deflected over a range of angles of attack from 8 deg to 32 deg. The tests were made at a Mach number of 0.13, which corresponds to a Reynolds number of about 3,000,000 based on the wing reference chord. |
| File Size | 90613361 |
| Page Count | 58 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19780013108 |
| Archival Resource Key | ark:/13960/t97708v7r |
| Language | English |
| Publisher Date | 1978-03-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Tail Assemblies Arrow Wings Swept Wings Scale Models Leading Edge Slats Angle of Attack Aerodynamic Stability Supersonic Transports Trailing Edge Flaps Aerodynamic Characteristics Pitch Inclination Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
