Abstract
Scramjet propulsion is a hypersonic airbreathing technology that offers the great potential for economical and flexible access to space and high-speed atmospheric transport. This paper presents the results and physical insight obtained in a design optimization study conducted for axisymmetric scramjet engines. A single-objective optimization has been performed to maximize the performance of a full flow-path scramjet configuration in the presence of nonuniform upstream fuel injection represented by a set of geometric parameters and injection scaling factors. Use is made of a state-of-the-art design methodology coupling a high-fidelity CFD code with an advanced optimization capability based on evolutionary algorithms assisted by surrogate modeling. The flowfields have been investigated to identify key factors and gain insight into underlying physics particularly in comparison with premixed fuel/air flowfields. The optimum flowfield with fuel injection is characterized by a mixed supersonic/subsonic flow regime similar to a transitional mode. The optimum design has been achieved by maximizing the nozzle thrust while reducing skin friction drag by boundary-layer combustion, although it represents a sensitive flowfield due to the delicate mechanism upon which it relies.
| Original language | English |
|---|---|
| Title of host publication | 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011 |
| DOIs | |
| Publication status | Published - Dec 1 2011 |
| Externally published | Yes |
| Event | 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011 - San Francisco, CA, United States Duration: Apr 11 2011 → Apr 14 2011 |
Publication series
| Name | 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011 |
|---|
Conference
| Conference | 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011 |
|---|---|
| Country | United States |
| City | San Francisco, CA |
| Period | 4/11/11 → 4/14/11 |
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All Science Journal Classification (ASJC) codes
- Space and Planetary Science
- Aerospace Engineering
- Control and Systems Engineering
Cite this
Full flow-path optimization of axisymmetric scramjet engines. / Ogawa, H.; Alazet, Y.; Pudsey, A.; Boyce, R. R.; Isaacs, A.; Ray, T.
17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011. 2011. (17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011).Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Full flow-path optimization of axisymmetric scramjet engines
AU - Ogawa, H.
AU - Alazet, Y.
AU - Pudsey, A.
AU - Boyce, R. R.
AU - Isaacs, A.
AU - Ray, T.
PY - 2011/12/1
Y1 - 2011/12/1
N2 - Scramjet propulsion is a hypersonic airbreathing technology that offers the great potential for economical and flexible access to space and high-speed atmospheric transport. This paper presents the results and physical insight obtained in a design optimization study conducted for axisymmetric scramjet engines. A single-objective optimization has been performed to maximize the performance of a full flow-path scramjet configuration in the presence of nonuniform upstream fuel injection represented by a set of geometric parameters and injection scaling factors. Use is made of a state-of-the-art design methodology coupling a high-fidelity CFD code with an advanced optimization capability based on evolutionary algorithms assisted by surrogate modeling. The flowfields have been investigated to identify key factors and gain insight into underlying physics particularly in comparison with premixed fuel/air flowfields. The optimum flowfield with fuel injection is characterized by a mixed supersonic/subsonic flow regime similar to a transitional mode. The optimum design has been achieved by maximizing the nozzle thrust while reducing skin friction drag by boundary-layer combustion, although it represents a sensitive flowfield due to the delicate mechanism upon which it relies.
AB - Scramjet propulsion is a hypersonic airbreathing technology that offers the great potential for economical and flexible access to space and high-speed atmospheric transport. This paper presents the results and physical insight obtained in a design optimization study conducted for axisymmetric scramjet engines. A single-objective optimization has been performed to maximize the performance of a full flow-path scramjet configuration in the presence of nonuniform upstream fuel injection represented by a set of geometric parameters and injection scaling factors. Use is made of a state-of-the-art design methodology coupling a high-fidelity CFD code with an advanced optimization capability based on evolutionary algorithms assisted by surrogate modeling. The flowfields have been investigated to identify key factors and gain insight into underlying physics particularly in comparison with premixed fuel/air flowfields. The optimum flowfield with fuel injection is characterized by a mixed supersonic/subsonic flow regime similar to a transitional mode. The optimum design has been achieved by maximizing the nozzle thrust while reducing skin friction drag by boundary-layer combustion, although it represents a sensitive flowfield due to the delicate mechanism upon which it relies.
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UR - http://www.scopus.com/inward/citedby.url?scp=84881287857&partnerID=8YFLogxK
U2 - 10.2514/6.2011-2347
DO - 10.2514/6.2011-2347
M3 - Conference contribution
AN - SCOPUS:84881287857
SN - 9781600869426
T3 - 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011
BT - 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011
ER -