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The effect of canard relative size and vertical location on the subsonic longitudinal and lateral-directional static aerodynamic characteristics for a model with a swept forward wing. [in the langley 7x10 ft high speed tunnel
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Huffman, J. K. Fox Jr., C. H. |
| Copyright Year | 1979 |
| Description | A general research fighter model was tested in the Langley 7- by 10-foot high speed tunnel at a Mach number of 0.3. The model was tested with a 32 deg swept forward wing mounted in mid-, low-, and high-wing positions. For the mid-wing configuration, the model was tested with a 51.7 deg swept back canard mounted in mid-, low-, and high-canard positions. For the mid-wing mid-canard and the mid-wing high-canard configurations, canards of similar planform having two different areas were tested. The angle-of-attack range was from approximately -4 deg to 48 deg at sideslip angles of 0 deg, -5 deg, and 5 deg. |
| File Size | 39923638 |
| Page Count | 112 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19790019967 |
| Archival Resource Key | ark:/13960/t51g5h85d |
| Language | English |
| Publisher Date | 1979-07-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Static Aerodynamic Characteristics Subsonic Speed Canard Configurations Wind Tunnel Tests Pressure Distribution Swept Forward Wings Wind Tunnel Models Wing Profiles Angle of Attack Fighter Aircraft Sideslip Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
