The Sonic Throat Method And Real Gas One Dimensional Flow
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Author | : Richard L. Humphrey |
Publisher | : |
Total Pages | : 52 |
Release | : 1971 |
Genre | : Hypersonic wind tunnels |
ISBN | : |
The one-dimensional flow equation for mass flow through the throat of a supersonic nozzle has been modified for use with real gas values of gamma and compressibility. Curve fits for gamma and Z and a simple iteration scheme have been developed for use with air and nitrogen over a temperature range of 300 to 6000 deg. K and a pressure of 10 to 100 atm. With this approach the sonic throat method can be used with the most recent gas tables to determine high temperature wind tunnel supply temperatures or enthalpies. (Author).
Author | : Richard L. Humphrey |
Publisher | : |
Total Pages | : 30 |
Release | : 1971 |
Genre | : |
ISBN | : |
The one-dimensional flow equation for mass flow through the throat of a supersonic nozzle has been modified for use with real gas values of gamma and compressibility. Curve fits for gamma and Z and a simple iteration scheme have been developed for use with air and nitrogen over a temperature range of 300 to 6000 deg. K and a pressure of 10 to 100 atm. With this approach the sonic throat method can be used with the most recent gas tables to determine high temperature wind tunnel supply temperatures or enthalpies. (Author).
Author | : Warren Winovich |
Publisher | : |
Total Pages | : 48 |
Release | : 1964 |
Genre | : Air heaters |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 992 |
Release | : 1974 |
Genre | : Aeronautics |
ISBN | : |
Author | : John David Anderson (Jr.) |
Publisher | : |
Total Pages | : 80 |
Release | : 1971 |
Genre | : Expansion of gases |
ISBN | : |
It is well established that population inversions between the (001) and (100) vibrational energy levels of CO2 can be created by rapid expansions of CO2-N2-H2O or He mixtures through supersonic nozzles. New experimental results are presented for such inversions. These experiments were conducted in both the 3-Megawatt Arc Tunnel and the 12.7 cm Shock Tunnel at the Naval Ordnance Laboratory. The results support previously published theoretical predictions obtained with a numerical, time-dependent, nonequilibrium nozzle flow analysis employing a simplified vibrational kinetic model. This theory is also compared with experimental data obtained by other investigators. (Author).
Author | : |
Publisher | : |
Total Pages | : 68 |
Release | : 1980 |
Genre | : Aeronautics |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 628 |
Release | : 1974 |
Genre | : Mechanics, Applied |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 516 |
Release | : 1974 |
Genre | : |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 1896 |
Release | : 1971 |
Genre | : Government publications |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 444 |
Release | : 1987 |
Genre | : Computer software |
ISBN | : |