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That is a a very simplistic question of a very complicated flow process. Was some part of the combustion process supersonic? Most assuredly yes. How much, that takes data. If you don't understand how complicated a question you have really posed, might I suggest you take a look at Thermodynamic Analysis of Dual-Mode Scramjet Engine Operation and Performance by Riggins, TackettTaylor and Auslender, AIAA Paper 2006-805. http://hdl.handle.net/2060/20070000536Abstract: Recent analytical advances in understanding the performance continuum (the thermodynamic spectrum) for air-breathing engines based on fundamental second-law considerations have clarified scramjet and ramjet operation, performance, and characteristics. Second-law based analysis is extended specifically in this work to clarify and describe the performance characteristics for dual-mode scramjet operation in the mid-speed range of flight Mach 4 to 7. This is done by a fundamental investigation of the complex but predictable interplay between heat release and irreversibilities in such an engine; results demonstrate the flow and performance character of the dual mode regime and of dual mode transition behavior. Both analytical and computational (multi-dimensional CFD) studies of sample dual-mode flow-fields are performed in order to demonstrate the second-law capability and performance and operability issues. The impact of the dual-mode regime is found to be characterized by decreasing overall irreversibility with increasing heat release, within the operability limits of the system.
That is a a very simplistic question of a very complicated flow process. Was some part of the combustion process supersonic? Most assuredly yes. How much, that takes data. If you don't understand how complicated a question you have really posed, might I suggest you take a look at Thermodynamic Analysis of Dual-Mode Scramjet Engine Operation and Performance by Riggins, TackettTaylor and Auslender, AIAA Paper 2006-805. http://hdl.handle.net/2060/20070000536
Abstract:
Recent analytical advances in understanding the performance continuum (the thermodynamic spectrum) for air-breathing engines based on fundamental second-law considerations have clarified scramjet and ramjet operation, performance, and characteristics. Second-law based analysis is extended specifically in this work to clarify and describe the performance characteristics for dual-mode scramjet operation in the mid-speed range of flight Mach 4 to 7. This is done by a fundamental investigation of the complex but predictable interplay between heat release and irreversibilities in such an engine; results demonstrate the flow and performance character of the dual mode regime and of dual mode transition behavior. Both analytical and computational (multi-dimensional CFD) studies of sample dual-mode flow-fields are performed in order to demonstrate the second-law capability and performance and operability issues. The impact of the dual-mode regime is found to be characterized by decreasing overall irreversibility with increasing heat release, within the operability limits of the system.
