Loading...
Please wait, while we are loading the content...
Similar Documents
Hot-gas-side heat transfer with and without film cooling on a simulated nuclear rocket thrust chamber using h2-o2
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Jones, W. L. Schacht, R. L. Quentmeyer, R. J. |
| Copyright Year | 1972 |
| Description | Heat-transfer coefficients were obtained on a thrust chamber which simulated the geometry of the NERVA nuclear rocket. The tests were performed with and without peripheral film cooling over a chamber pressure range of 1.05 million to 5.84 million newtons per square meter (153 to 847 psia). With no film cooling, the overall axial variation in the value of the correlation coefficient C of the equation (Stanton)* (Prandtl)* to the 0.7ths power = C(Reynolds)* to the -0.2ths power, where * indicates the reference enthalpy condition, was reduced 66 percent when the local diameter in the Reynolds number was replaced by the axial distance from the injector face. The average peak values of C were reduced 25 percent with 2 and 3.75 percent cooling and 50 percent with 7.5 percent cooling. |
| File Size | 1827374 |
| Page Count | 39 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19720009286 |
| Archival Resource Key | ark:/13960/t92853b84 |
| Language | English |
| Publisher Date | 1972-02-01 |
| Access Restriction | Open |
| Subject Keyword | Thermodynamics And Combustion Convective Heat Transfer Simulation Reynolds Number Nuclear Engine for Rocket Vehicles Thrust Chambers Mathematical Models Hydrogen Oxygen Engines Film Cooling Heat Transfer Coefficients 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 |
