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Static internal performance including thrust vectoring and reversing of two-dimensional convergent-divergent nozzles
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Leavitt, L. D. Re, R. J. |
| Copyright Year | 1984 |
| Description | The effects of geometric design parameters on two dimensional convergent-divergent nozzles were investigated at nozzle pressure ratios up to 12 in the static test facility. Forward flight (dry and afterburning power settings), vectored-thrust (afterburning power setting), and reverse-thrust (dry power setting) nozzles were investigated. The nozzles had thrust vector angles from 0 deg to 20.26 deg, throat aspect ratios of 3.696 to 7.612, throat radii from sharp to 2.738 cm, expansion ratios from 1.089 to 1.797, and various sidewall lengths. The results indicate that unvectored two dimensional convergent-divergent nozzles have static internal performance comparable to axisymmetric nozzles with similar expansion ratios. |
| File Size | 7151126 |
| Page Count | 111 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19840010097 |
| Archival Resource Key | ark:/13960/t15n1284w |
| Language | English |
| Publisher Date | 1984-02-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Static Pressure Nozzle Geometry Thrust Vector Control Convergent-divergent Nozzles Pressure Ratio Thrust Reversal Aspect Ratio Static Tests Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
