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Determination of aerodynamic stability and drag of the titan 3 c srm during entry
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Ramsey, P. E. |
| Copyright Year | 1974 |
| Description | An experimental aerodynamic investigation was conducted in the NASA/MSFC 14-inch Trisonic Wind Tunnel on a 0.00736 scale model of Titan 3 C Solid Rocket Motor (SRM). Static stability and drag data were obtained for Mach numbers of 0.6 to 4.96, angles of attack of minus 10 deg to 190 deg, and roll angles of 0 to 360 deg. The resulting data will be used to predict the dynamic motions of the SRM during entry which will then be compared to flight data. This comparison will improve and lend credibility to methods for predicting the entry dynamics of the space shuttle Solid Rocket Booster (SRB), which is needed for recovery studies and design of the parachute recovery system. |
| File Size | 26451201 |
| Page Count | 401 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19740024302 |
| Archival Resource Key | ark:/13960/t1hj1976c |
| Language | English |
| Publisher Date | 1974-07-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Missile Configurations Titan Icbm Subsonic Speed Supersonic Speed Data Acquisition Wind Tunnel Stability Tests Performance Prediction Transonic Speed Aerodynamic Characteristics Stability Derivatives Space Shuttle Boosters Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
