1. Date of download: 6/27/2016 Copyright © ASME. All rights reserved. From: Numerical Modeling of Regenerative Cooling System for Large Expansion Ratio Rocket Engines J. Thermal Sci. Eng. Appl. 2015;7(1):011012-011012-8. doi:10.1115/1.4028979 Schematic diagram of rocket nozzle with regenerative cooling system Figure Legend:

2. Date of download: 6/27/2016 Copyright © ASME. All rights reserved. From: Numerical Modeling of Regenerative Cooling System for Large Expansion Ratio Rocket Engines J. Thermal Sci. Eng. Appl. 2015;7(1):011012-011012-8. doi:10.1115/1.4028979 Variation of gas-side wall temperature for various mesh sizes Figure Legend:

3. Date of download: 6/27/2016 Copyright © ASME. All rights reserved. From: Numerical Modeling of Regenerative Cooling System for Large Expansion Ratio Rocket Engines J. Thermal Sci. Eng. Appl. 2015;7(1):011012-011012-8. doi:10.1115/1.4028979 Grid employed for the simulation shown in midplane Figure Legend:

4. Date of download: 6/27/2016 Copyright © ASME. All rights reserved. From: Numerical Modeling of Regenerative Cooling System for Large Expansion Ratio Rocket Engines J. Thermal Sci. Eng. Appl. 2015;7(1):011012-011012-8. doi:10.1115/1.4028979 Axial variation of static temperature and velocity in uncooled nozzle Figure Legend:

5. Date of download: 6/27/2016 Copyright © ASME. All rights reserved. From: Numerical Modeling of Regenerative Cooling System for Large Expansion Ratio Rocket Engines J. Thermal Sci. Eng. Appl. 2015;7(1):011012-011012-8. doi:10.1115/1.4028979 Axial variation of Mach number in uncooled nozzle Figure Legend:

6. Date of download: 6/27/2016 Copyright © ASME. All rights reserved. From: Numerical Modeling of Regenerative Cooling System for Large Expansion Ratio Rocket Engines J. Thermal Sci. Eng. Appl. 2015;7(1):011012-011012-8. doi:10.1115/1.4028979 Axial variation of static temperature in uncooled nozzle Figure Legend:

7. Date of download: 6/27/2016 Copyright © ASME. All rights reserved. From: Numerical Modeling of Regenerative Cooling System for Large Expansion Ratio Rocket Engines J. Thermal Sci. Eng. Appl. 2015;7(1):011012-011012-8. doi:10.1115/1.4028979 Variation of static temperature along the wall of cooled nozzle Figure Legend:

8. Date of download: 6/27/2016 Copyright © ASME. All rights reserved. From: Numerical Modeling of Regenerative Cooling System for Large Expansion Ratio Rocket Engines J. Thermal Sci. Eng. Appl. 2015;7(1):011012-011012-8. doi:10.1115/1.4028979 Variation of gas-side wall temperature for different coolant flow rates Figure Legend:

9. Date of download: 6/27/2016 Copyright © ASME. All rights reserved. From: Numerical Modeling of Regenerative Cooling System for Large Expansion Ratio Rocket Engines J. Thermal Sci. Eng. Appl. 2015;7(1):011012-011012-8. doi:10.1115/1.4028979 Variation of gas-side wall temperature for cooled and uncooled cases Figure Legend:

10. Date of download: 6/27/2016 Copyright © ASME. All rights reserved. From: Numerical Modeling of Regenerative Cooling System for Large Expansion Ratio Rocket Engines J. Thermal Sci. Eng. Appl. 2015;7(1):011012-011012-8. doi:10.1115/1.4028979 Variation of gas-side and coolant-side wall temperatures Figure Legend:

11. Date of download: 6/27/2016 Copyright © ASME. All rights reserved. From: Numerical Modeling of Regenerative Cooling System for Large Expansion Ratio Rocket Engines J. Thermal Sci. Eng. Appl. 2015;7(1):011012-011012-8. doi:10.1115/1.4028979 Variation of gas-side wall temperature for different cooling media Figure Legend:

12. Date of download: 6/27/2016 Copyright © ASME. All rights reserved. From: Numerical Modeling of Regenerative Cooling System for Large Expansion Ratio Rocket Engines J. Thermal Sci. Eng. Appl. 2015;7(1):011012-011012-8. doi:10.1115/1.4028979 Heat flux variation along the rocket nozzle wall Figure Legend:

13. Date of download: 6/27/2016 Copyright © ASME. All rights reserved. From: Numerical Modeling of Regenerative Cooling System for Large Expansion Ratio Rocket Engines J. Thermal Sci. Eng. Appl. 2015;7(1):011012-011012-8. doi:10.1115/1.4028979 Variation of gas-side wall temperature for different wall materials Figure Legend:

14. Date of download: 6/27/2016 Copyright © ASME. All rights reserved. From: Numerical Modeling of Regenerative Cooling System for Large Expansion Ratio Rocket Engines J. Thermal Sci. Eng. Appl. 2015;7(1):011012-011012-8. doi:10.1115/1.4028979 Variation of gas-side wall temperature for different wall thickness Figure Legend:

15. Date of download: 6/27/2016 Copyright © ASME. All rights reserved. From: Numerical Modeling of Regenerative Cooling System for Large Expansion Ratio Rocket Engines J. Thermal Sci. Eng. Appl. 2015;7(1):011012-011012-8. doi:10.1115/1.4028979 Variation of heat flux for different wall thickness Figure Legend:

16. Date of download: 6/27/2016 Copyright © ASME. All rights reserved. From: Numerical Modeling of Regenerative Cooling System for Large Expansion Ratio Rocket Engines J. Thermal Sci. Eng. Appl. 2015;7(1):011012-011012-8. doi:10.1115/1.4028979 Variation of gas-side wall temperature for convection and radiation Figure Legend:

17. Date of download: 6/27/2016 Copyright © ASME. All rights reserved. From: Numerical Modeling of Regenerative Cooling System for Large Expansion Ratio Rocket Engines J. Thermal Sci. Eng. Appl. 2015;7(1):011012-011012-8. doi:10.1115/1.4028979 Variation of gas-side wall temperature for different viscous models Figure Legend:

18. Date of download: 6/27/2016 Copyright © ASME. All rights reserved. From: Numerical Modeling of Regenerative Cooling System for Large Expansion Ratio Rocket Engines J. Thermal Sci. Eng. Appl. 2015;7(1):011012-011012-8. doi:10.1115/1.4028979 Comparison of predicted gas-side wall temperature with published data [4] Figure Legend: