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Effect of nose bluntness and afterbody shape on aerodynamic characteristics of a monoplanar missile concept with bodies of circular and elliptical cross sections at a mach number of 2.50
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Graves, E. B. Fournier, R. H. |
| Copyright Year | 1979 |
| Description | The tests were performed at a Mach number of 2.50 and at angles of attack from about -4 deg to 32 deg. The results indicate that increasing nose bluntness increases zero lift drag and decreases both the maximum lift-drag ratio and the level of directional stability. The center of pressure generally moves forward with increasing nose size; however, small nose radii on the modified elliptical configurations move the center of pressure rearward. The circular bodied configurations exhibit the greatest longitudinal stability and the least directional stability. Concepts with the variable geometry afterbody contour display the most directional stability and the greatest zero lift drag. |
| File Size | 5185683 |
| Page Count | 88 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19790017852 |
| Archival Resource Key | ark:/13960/t1jh8c361 |
| Language | English |
| Publisher Date | 1979-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Missile Configurations Directional Stability Lift Drag Ratio Afterbodies Wind Tunnel Tests Body-wing and Tail Configurations Pressure Distribution Nose Cones Blunt Bodies Angle of Attack Aerodynamic Characteristics Longitudinal Stability Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
