Loading...
Please wait, while we are loading the content...
Calibration of lewis hypersonic tunnel facility at mach 5, 6, and 7
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Cullon, R. R. Lezberg, E. A. |
| Copyright Year | 1972 |
| Description | Results of the initial calibration tests and a description of this true simulation facility are presented. Facility nozzles were calibrated over a range of stagnation pressure and temperature from 140 to 700 newtons per square centimeter and 1100 to 1750 K. The Reynolds number varied from 1.77 million to 7.44 million per meter. Mach numbers in the inviscid core of the three nozzles were 5.17 plus or minus 0.03, 6.05 plus or minus 0.02, and 7.25 plus or minus 0.08. Usable core diameters at the nozzle exit plane varied from 69 to 86 centimeters. True simulation with these performance capabilities and the test section size presently make this a unique operating facility. |
| File Size | 5881400 |
| Page Count | 33 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19730002510 |
| Archival Resource Key | ark:/13960/t76t5f55s |
| Language | English |
| Publisher Date | 1972-11-01 |
| Access Restriction | Open |
| Subject Keyword | Stagnation Pressure Performance Tests Stagnation Temperature Reynolds Number Hypersonic Flow Hypervelocity Wind Tunnels Wind Tunnel Calibration 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 |
