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Aerodynamics of an axisymmetric missile concept having cruciform strakes and in-line tail fins from mach 0.60 to 4.63
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Allen, Jerry M. |
| Copyright Year | 2005 |
| Description | An experimental study has been performed to develop a large force and moment aerodynamic data set on a slender axisymmetric missile configuration having cruciform strakes and in-line control tail fins. The data include six-component balance measurements of the configuration aerodynamics and three-component measurements on all four tail fins. The test variables include angle of attack, roll angle, Mach number, model buildup, strake length, nose size, and tail fin deflection angles to provide pitch, yaw, and roll control. Test Mach numbers ranged from 0.60 to 4.63. The entire data set is presented on a CD-ROM that is attached to this paper. The CD-ROM also includes extensive plots of both the six-component configuration data and the three-component tail fin data. Selected samples of these plots are presented in this paper to illustrate the features of the data and to investigate the effects of the test variables. |
| File Size | 5498950 |
| Page Count | 115 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20050160470 |
| Archival Resource Key | ark:/13960/t72v7hg3j |
| Language | English |
| Publisher Date | 2005-03-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Noses Forebodies Tail Assemblies Strakes Subsonic Speed Deflection Missile Control Fins Transonic Speed Yaw Missile Configurations Cruciform Wings Supersonic Speed Wind Tunnel Tests Roll Angle of Attack 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 |
