Loading...
Please wait, while we are loading the content...
Similar Documents
Stability and control characteristics of a monoplane missile with large delta wings and various tail controls at mach 1.90 to 2.86
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Jernell, L. S. |
| Copyright Year | 1974 |
| Description | Wind tunnel tests were conducted to determine the stability and control characteristics of a monoplane missile with large delta wings and various tail configurations. The tests were conducted at angles of attack of approximately 24 degrees and angles of sideslip of about 22 degrees. Tail control configurations were the cruciform, conventional airplane type, and an inverted airplane configuration. Control effectiveness was measured for pitch, yaw, and roll. |
| File Size | 46160975 |
| Page Count | 42 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19740021178 |
| Archival Resource Key | ark:/13960/t6zw67402 |
| Language | English |
| Publisher Date | 1974-07-01 |
| Access Restriction | Open |
| Subject Keyword | Space Vehicles Missile Configurations Body-wing Configurations Guidance Motion Delta Wings Control Surfaces Wind Tunnel Tests Aerodynamic Characteristics Tail Surfaces Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
