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Relevant bibliographies by topics / Combustion ratio / Books

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Books on the topic 'Combustion ratio'

Author: Grafiati

Published: 28 June 2021

Last updated: 29 July 2025

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1

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

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2

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

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3

United States. National Aeronautics and Space Administration., ed. Comparison of high aspect ratio cooling channel designs for a rocket combustion chamber. National Aeronautics and Space Administration, 1997.

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4

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

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5

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

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6

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

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7

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

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8

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

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9

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

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10

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

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11

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

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12

K, Mongia Rajiv, Dibble Robert W, and NASA Glenn Research Center, eds. Real-time optical fuel-to-air ratio sensor for gas turbine combustors. National Aeronautics and Space Administration, Glenn Research Center, 1999.

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13

K, Mongia Rajiv, Dibble Robert W, and NASA Glenn Research Center, eds. Real-time optical fuel-to-air ratio sensor for gas turbine combustors. National Aeronautics and Space Administration, Glenn Research Center, 1999.

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14

K, Mongia Rajiv, Dibble Robert W, and NASA Glenn Research Center, eds. Real-time optical fuel-to-air ratio sensor for gas turbine combustors. National Aeronautics and Space Administration, Glenn Research Center, 1999.

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15

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

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16

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

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17

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

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18

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

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19

Reid, Smith, and Lewis Research Center, eds. Advanced low emissions subsonic combustor study: Final report. National Aeronautics and Space Administration, Lewis Research Center, 1998.

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20

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

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21

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

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22

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

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23

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

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24

United States. National Aeronautics and Space Administration., ed. Structure of a swirl-stabilized combusting spray. National Aeronautics and Space Administration, 1994.

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25

United States. National Aeronautics and Space Administration., ed. Structure of a swirl-stabilized combusting spray. National Aeronautics and Space Administration, 1994.

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26

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

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27

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

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28

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

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29

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

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30

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

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31

Haugen, Peter. World History for Dummies. Hungry Minds, 2001.

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32

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

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33

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

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34

National Aeronautics and Space Administration (NASA) Staff. High-Area-Ratio Rocket Nozzle at High Combustion Chamber Pressure: Experimental and Analytical Validation. Independently Published, 2018.

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35

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

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36

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

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37

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

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38

Structure of a swirl-stabilized combusting spray. National Aeronautics and Space Administration, 1994.

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39

Structure of a swirl-stabilized combusting spray. National Aeronautics and Space Administration, 1994.

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40

Effects of fuel distribution on detonation tube performance. National Aeronautics and Space Administration, Glenn Research Center, 2002.

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41

Relation of Draft Ratios to Combustion Efficiency. Creative Media Partners, LLC, 2023.

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42

Spieth, Benjamin Stephen. Relation of Draft Ratios to Combustion Efficiency. Creative Media Partners, LLC, 2018.

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43

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

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44

The Relation Of Draft Ratios To Combustion Efficiency. Franklin Classics, 2018.

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45

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

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The dynamic, evolving Earth, and the mathematical representation of its geochemical changes are the subject of this timely, helpful handbook. Global warming, changes in the ocean, and the effects of fossil fuel combustion are just a few of the phenomena that make the development of geochemical models critical. But what computational methods will help to accurately carry out this task? This new text teaches the methodology of computational simulation of environmental change. The author presents interesting applications of his methods to describe the response of the ocean and atmosphere to the i

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46

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

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47

Smil, Vaclav. Creating and Transforming the Twentieth Century, Revised and Expanded. Oxford University PressNew York, NY, 2025. https://doi.org/10.1093/9780197784679.001.0001.

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Abstract The greatest technical discontinuity in history took place between 1867 and 1914. This era was distinguished by the most extraordinary concatenation of scientific and technical advances, the synergy of which produced bold and imaginative innovations resulting in profound socioeconomic impacts. Detailed examinations of these epoch-making advances start with electricity (dynamos, steam turbines, transformers, light bulbs, electric motors, power plants, transmission) and internal combustion engines (automotive designs by Otto, Diesel, Daimler, Maybach, Benz, Ford, aeroengines) before loo

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48

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

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49

Haugen, Peter. World History for Dummies. Wiley & Sons, Incorporated, John, 2022.

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50

Haugen, Peter. World History for Dummies. Wiley & Sons, Incorporated, John, 2022.

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