Bücher zum Thema „Combustion ratio“

DuBeau, Robert William. An investigation of the effects of fuel composition on combustion characteristics in a T-63 combustor. Monterey, Calif: Naval Postgraduate School, 1985.

Jankowsky, Robert S. Experimental performance of a high-area-ratio rocket nozzle at high combustion chamber pressure. [Cleveland, Ohio]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1996.

Jankovsky, Robert S. High-area-ratio rocket nozzle at high combustion chamber pressure--experimental and analytical validation. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 1999.

Pitts, William M. The global equivalence ratio concept and the prediction of carbon monoxide formation in enclosure fires. Gaithersburg, MD: U.S. Dept. of Commerce, Technology Administration, National Institute of Standards and Technology, 1994.

Perkins, Hugh Douglas. Effects of fuel distribution on detonation tube performance. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2002.

Horler, Greg. The design and use of a digital radio telemetry system for measuring internal combustion engine piston parameters. Leicester: De Montfort University, 1999.

Haugen, Peter. World History for Dummies. New York, USA: Hungry Minds, 2001.

World History For Dummies. New York, USA: Wiley Publishing, 2001.

Haugen, Peter. Historia del mundo. Bogotá: Norma, 2002.

E, Smith C., Holdeman J. D und United States. National Aeronautics and Space Administration., Hrsg. CFD assessment of orifice aspect ratio and mass flow ratio on jet mixing in rectangular ducts. [Washington, DC: National Aeronautics and Space Administration, 1994.

Zoysa, Merrenna Manula De. Neural network estimation of air-fuel ratio in internal combustion engines. 2003.

United States. National Aeronautics and Space Administration., Hrsg. Comparison of high aspect ratio cooling channel designs for a rocket combustion chamber. [Washington, DC]: National Aeronautics and Space Administration, 1997.

D, Smith Timothy, Pavli Albert J und NASA Glenn Research Center, Hrsg. High-area-ratio rocket nozzle at high combustion chamber pressure--experimental and analytical validation. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 1999.

D, Smith Timothy, Pavli Albert J und NASA Glenn Research Center, Hrsg. High-area-ratio rocket nozzle at high combustion chamber pressure--experimental and analytical validation. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 1999.

M, Kazaroff John, Pavli Albert J und United States. National Aeronautics and Space Administration. Scientific and Technical Information Program, Hrsg. Experimental performance of a high-area-ratio rocket nozzle at high combustion chamber pressure. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1996.

D, Smith Timothy, Pavli Albert J und NASA Glenn Research Center, Hrsg. High-area-ratio rocket nozzle at high combustion chamber pressure--experimental and analytical validation. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 1999.

High-area-ratio rocket nozzle at high combustion chamber pressure--experimental and analytical validation. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 1999.

M, Kazaroff John, Pavli Albert J und United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., Hrsg. Experimental performance of a high-area-ratio rocket nozzle at high combustion chamber pressure. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1996.

M, Kazaroff John, Pavli Albert J und United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., Hrsg. Experimental performance of a high-area-ratio rocket nozzle at high combustion chamber pressure. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1996.

Validation of high aspect ratio cooling in a 89 kN (20,000 lb[sub f]) thrust combustion chamber. [Washington, DC]: National Aeronautics and Space Administration, 1996.

K, Mongia Rajiv, Dibble Robert W und NASA Glenn Research Center, Hrsg. Real-time optical fuel-to-air ratio sensor for gas turbine combustors. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 1999.

Real-time optical fuel-to-air ratio sensor for gas turbine combustors. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 1999.

K, Mongia Rajiv, Dibble Robert W und NASA Glenn Research Center, Hrsg. Real-time optical fuel-to-air ratio sensor for gas turbine combustors. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 1999.

K, Mongia Rajiv, Dibble Robert W und NASA Glenn Research Center, Hrsg. Real-time optical fuel-to-air ratio sensor for gas turbine combustors. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 1999.

A, Strehlow Roger, University of Illinois at Urbana-Champaign. Aeronautical and Astronautical Engineering Dept und United States. National Aeronautics and Space Administration, Hrsg. The behavior of fuel-lean premixed flames in a standard flammability limit tube under controlled gravity conditions. Urbana, Ill: Aeronautical and Astronautical Engineering Dept., University of Illinois, 1986.

The behavior of fuel-lean premixed flames in a standard flammability limit tube under controlled gravity conditions. Urbana, Ill: Aeronautical and Astronautical Engineering Dept., University of Illinois, 1986.

A, Strehlow Roger, University of Illinois at Urbana-Champaign. Aeronautical and Astronautical Engineering Dept. und United States. National Aeronautics and Space Administration., Hrsg. The behavior of fuel-lean premixed flames in a standard flammability limit tube under controlled gravity conditions. Urbana, Ill: Aeronautical and Astronautical Engineering Dept., University of Illinois, 1986.

A, Strehlow Roger, University of Illinois at Urbana-Champaign. Aeronautical and Astronautical Engineering Dept und United States. National Aeronautics and Space Administration, Hrsg. The behavior of fuel-lean premixed flames in a standard flammability limit tube under controlled gravity conditions. Urbana, Ill: Aeronautical and Astronautical Engineering Dept., University of Illinois, 1986.

United States. National Aeronautics and Space Administration., Hrsg. COMPARISON OF HIGH ASPECT RATIO COOLING CHANNEL DESIGNS FOR A ROCKET COMBUSTION CHAMBER WITH DEVELOPMENT OF AN... NASA/TM-1998-206313... APR. [S.l: s.n., 1999.

Reid, Smith, und Lewis Research Center, Hrsg. Advanced low emissions subsonic combustor study: Final report. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1998.

United States. National Aeronautics and Space Administration., Hrsg. Structure of a swirl-stabilized combusting spray. Washington, DC: American Institute of Aeronautics and Astronautics, Inc., 1995.

United States. National Aeronautics and Space Administration., Hrsg. Structure of a swirl-stabilized combusting spray. Washington, DC: American Institute of Aeronautics and Astronautics, Inc., 1995.

Structure of a swirl-stabilized combusting spray. [Washington, DC]: National Aeronautics and Space Administration, 1994.

United States. National Aeronautics and Space Administration., Hrsg. Structure of a swirl-stabilized combusting spray. [Washington, DC]: National Aeronautics and Space Administration, 1994.

Structure of a swirl-stabilized combusting spray. [Washington, DC]: National Aeronautics and Space Administration, 1994.

United States. National Aeronautics and Space Administration., Hrsg. Structure of a swirl-stabilized combusting spray. Washington, DC: American Institute of Aeronautics and Astronautics, Inc., 1995.

United States. National Aeronautics and Space Administration., Hrsg. Structure of a swirl-stabilized combusting spray. Washington, DC: American Institute of Aeronautics and Astronautics, Inc., 1995.

United States. National Aeronautics and Space Administration., Hrsg. Structure of a swirl-stabilized combusting spray. [Washington, DC]: National Aeronautics and Space Administration, 1994.

Effects of fuel distribution on detonation tube performance. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2002.

Fuel-rich catalytic combustion of jet-A fuel: Equivalence ratios 5.0 to 8.0. [Washington, DC]: National Aeronautics and Space Administration, 1989.

M, Gracia-Salcedo Carmen, United States. Army Aviation Research and Technology Activity. und United States. National Aeronautics and Space Administration., Hrsg. Fuel-rich catalytic combustion of jet-A fuel: Equivalence ratios 5.0 to 8.0. [Washington, DC]: National Aeronautics and Space Administration, 1989.

Walker, James C. G. Numerical Adventures with Geochemical Cycles. Oxford University Press, 1991. http://dx.doi.org/10.1093/oso/9780195045208.001.0001.

Effect of Equivalence Ratio and G-Loading on In-Situ Measurements of Chemiluminescence in an Ultra Compact Combustor. Storming Media, 2004.

Haugen, Peter. Historia Del Mundo Para Dummies. Grupo Editorial Norma, 2005.

World History for Dummies. 2. Aufl. Hoboken, N.J., USA: Wiley Publishing, 2009.

World History For Dummies. New York: John Wiley & Sons, Ltd., 2009.