NSTL国家科技图书文献中心

1. A Time‐Space Dual Adaptive Uncoupled Method for Supersonic Combustion NSTL国家科技图书文献中心

Junjie Wu | Xun Xu ... - 《International Journal for Numerical Methods in Fluids》 - 2025,97(3) - 378～394 - 共17页

摘要： problem for simulating a supersonic* reactive flow by* | ABSTRACT High computational complexity due to | rapidly increasing numerical stiffness is a difficult | using the uncoupled method. On the basis of our | previous work, this paper proposes a dual adaptive method

关键词： computational efficiency | ignition | robustness | stiffness | stiffness leakage | uncoupled method

2. Steady supersonic combustion flows with a contact discontinuity in two-dimensional finitely long nozzles NSTL国家科技图书文献中心

Gao, Junlei | Huang, Feimin ... - 《Calculus of variations and partial differential equations》 - 2025,64(2) - 共82页

摘要：-dimensional steady supersonic* combustion flows with a* | simplify the two-dimensional steady supersonic combustion | steady combustion* Euler equations with a contact* | are coupled with each other due to the combustion | In this paper, we are concerned with the two

关键词： 35B20 | 35D30 | 35L04 | 76J20 | 76L99 | 76N10

3. Combustion performance of an evaporative flameholder under subsonic-supersonic mixing inflow NSTL国家科技图书文献中心

Huang, Yakun | Zhu, Zhixiang ... - 《Applied thermal engineering》 - 2025,258(Pt.C) - 共11页

摘要：The combustion* process in rocket-assisted* | to improve combustion* performance at altitudes of* | . Investigating the relationship between combustion* performance* | and inlet parameters under subsonic-supersonic | subsonic and supersonic* airflow mixing via a flat-plate*

关键词： Subsonic-supersonic mixing inflow | Vortex structure | Flameholder | Shear layer | Recirculation zone

4. Effects of pulse injection on the flow field structure and combustion performance in a kerosene-fueled supersonic combustor NSTL国家科技图书文献中心

Chen C. | Wang Y.... - 《Acta astronautica》 - 2025,226(Jan. Pt.1) - 479～493 - 共15页

摘要： injection of kerosene fuel in a kerosene-fueled supersonic | frequencies on the wave family and kerosene combustion | ignition, leading to combustion* instability. However, an* | average combustion* intensity of kerosene with pulse* | , the instantaneous combustion* intensity at 143 Hz is*

关键词： Combustion performance | Ignition delay | Pulse injection | Wave family

5. Improvement of the fuel mixing of ramp injector system via 4-lobe nozzle at scramjet engine NSTL国家科技图书文献中心

Wei Fu | N.A. Razak ... - 《Energy》 - 2025,315(Jan..15) - 134327.1～134327.9 - 共9页

摘要： supersonic flow (Mach = 2). The finite volume approach is | selected for the modeling of supersonic* airflow and* | The ramp injection system has been extensively | used for the fuel distribution and mixing inside the | combustor of scramjet engines. This article presents a

关键词： Supersonic combustion | Computational fluid dynamic | Compressible flow | Fuel mixing | Hydrogen

6. Experimental DMD analysis of combustion modes and instabilities in a scramjet combustor NSTL国家科技图书文献中心

Min-Su Kim | Bu-Kyeng Sung ... - 《Aerospace science and technology》 - 2025,157(Feb.) - 109783.1～109783.18 - 共18页

摘要：The combustion* characteristics of a gaseous* | achieved in all cases, combustion* persisted while fuel* | combustion modes according to equivalence ratio, by | within the flow of the combustor. These combustion | hydrogen fueled scramjet combustor were experimentally

关键词： Scramjet engine | Dynamic mode decomposition (DMD) | Supersonic combustion modes | Combustion instability | Shock train

7. Far-field noise measurements of a supersonic jet operating near afterburning conditions NSTL国家科技图书文献中心

Ashwin Kumar | Joseph Meadows ... - 《Aerospace science and technology》 - 2025,157(Feb.) - 109842.1～109842.13 - 共13页

摘要： discharged through a scaled-down GE F-404 supersonic* nozzle* | engine combustion* instabilities can convect downstream* | This paper presents a comprehensive overview | of the operation and spectral performance of a | novel lab-scale afterburning jet noise rig at Virginia

关键词： Aeroacoustics | Afterburner | Combustion | Supersonic et noise | Total temperature ratio | Nozzle pressure ratio | Acoustic efficiency | Convective Mach number

8. Instability of isolator shocks to fuel flow rate modulations in a strut-stabilised scramjet combustor NSTL国家科技图书文献中心

R. Kumar | A. Ghosh - 《The Aeronautical journal》 - 2025,129(Jan. TN.1331) - 42～62 - 共21页

摘要： inside a strut-stabilised supersonic* combustion ramjet* | investigate supersonic, chemically reacting, flow fields | rates. Fully supersonic, fully subsonic and mixed | detail. For certain modes of combustion* characterised* | modes of combustion, characterised by the presence of

关键词： mode transition | thermal choking | dual-mode scramjet | strut | supersonic | shockwaves

9. Investigating and simulating the process of mixing fuel and air cavity-based in the combustion chamber of scramjet engines NSTL国家科技图书文献中心

Bazazzadeh M. | Tahooneh A.G.... - 《International journal of hydrogen energy》 - 2025,99(Jan.) - 177～188 - 共12页

摘要： efficiency and stability of supersonic* combustion, paving* | process of fuel and air mixing within the combustion | combustion chamber, is approximately equal to 100%, 78% and | beginning of the combustion* chamber, the mixing efficiency* | © 2024This study delves into the intricate

关键词： Cavity | Combustion chamber | Mixing efficiency | Scramjet engines | Stagnation pressure drop | Vortices

10. Study on heat release characteristics of the dual composite flame stabilizers for the dual-mode scramjet NSTL国家科技图书文献中心

Xingliang Chen | Shaohua Zhu ... - 《Aerospace science and technology》 - 2025,157(Feb.) - 109703.1～109703.14 - 共14页

摘要：-dimensional distribution of subsonic/supersonic* HR, local* | combustion modes, and the variations in HR during the ram | the ejection effect of the supersonic* flow, causing* | that the mainstream subsonic-diffusion combustion | combustion efficiency at different equivalence ratios. In

摘要： problem for simulating a supersonic* reactive flow by* | ABSTRACT High computational complexity due to | rapidly increasing numerical stiffness is a difficult | using the uncoupled method. On the basis of our | previous work, this paper proposes a dual adaptive method

关键词： computational efficiency | ignition | robustness | stiffness | stiffness leakage | uncoupled method

摘要：-dimensional steady supersonic* combustion flows with a* | simplify the two-dimensional steady supersonic combustion | steady combustion* Euler equations with a contact* | are coupled with each other due to the combustion | In this paper, we are concerned with the two

关键词： 35B20 | 35D30 | 35L04 | 76J20 | 76L99 | 76N10

摘要：The combustion* process in rocket-assisted* | to improve combustion* performance at altitudes of* | . Investigating the relationship between combustion* performance* | and inlet parameters under subsonic-supersonic | subsonic and supersonic* airflow mixing via a flat-plate*

关键词： Subsonic-supersonic mixing inflow | Vortex structure | Flameholder | Shear layer | Recirculation zone

摘要： injection of kerosene fuel in a kerosene-fueled supersonic | frequencies on the wave family and kerosene combustion | ignition, leading to combustion* instability. However, an* | average combustion* intensity of kerosene with pulse* | , the instantaneous combustion* intensity at 143 Hz is*

关键词： Combustion performance | Ignition delay | Pulse injection | Wave family

摘要： supersonic flow (Mach = 2). The finite volume approach is | selected for the modeling of supersonic* airflow and* | The ramp injection system has been extensively | used for the fuel distribution and mixing inside the | combustor of scramjet engines. This article presents a

关键词： Supersonic combustion | Computational fluid dynamic | Compressible flow | Fuel mixing | Hydrogen

摘要：The combustion* characteristics of a gaseous* | achieved in all cases, combustion* persisted while fuel* | combustion modes according to equivalence ratio, by | within the flow of the combustor. These combustion | hydrogen fueled scramjet combustor were experimentally

关键词： Scramjet engine | Dynamic mode decomposition (DMD) | Supersonic combustion modes | Combustion instability | Shock train

摘要： discharged through a scaled-down GE F-404 supersonic* nozzle* | engine combustion* instabilities can convect downstream* | This paper presents a comprehensive overview | of the operation and spectral performance of a | novel lab-scale afterburning jet noise rig at Virginia

关键词： Aeroacoustics | Afterburner | Combustion | Supersonic et noise | Total temperature ratio | Nozzle pressure ratio | Acoustic efficiency | Convective Mach number

摘要： inside a strut-stabilised supersonic* combustion ramjet* | investigate supersonic, chemically reacting, flow fields | rates. Fully supersonic, fully subsonic and mixed | detail. For certain modes of combustion* characterised* | modes of combustion, characterised by the presence of

关键词： mode transition | thermal choking | dual-mode scramjet | strut | supersonic | shockwaves

摘要： efficiency and stability of supersonic* combustion, paving* | process of fuel and air mixing within the combustion | combustion chamber, is approximately equal to 100%, 78% and | beginning of the combustion* chamber, the mixing efficiency* | © 2024This study delves into the intricate

关键词： Cavity | Combustion chamber | Mixing efficiency | Scramjet engines | Stagnation pressure drop | Vortices

摘要：-dimensional distribution of subsonic/supersonic* HR, local* | combustion modes, and the variations in HR during the ram | the ejection effect of the supersonic* flow, causing* | that the mainstream subsonic-diffusion combustion | combustion efficiency at different equivalence ratios. In

关键词： Dual-mode scramjet | Dual composite flame stabilizers | Mode transition | Heat release | Injection schemes

4008-161-200 800-990-8900

国家科技图书文献中心

摘要： problem for simulating a supersonic reactive flow by | ABSTRACT High computational complexity due to | rapidly increasing numerical stiffness is a difficult | using the uncoupled method. On the basis of our | previous work, this paper proposes a dual adaptive method

关键词： computational efficiency | ignition | robustness | stiffness | stiffness leakage | uncoupled method

摘要：-dimensional steady supersonic combustion flows with a | simplify the two-dimensional steady supersonic combustion | steady combustion Euler equations with a contact | are coupled with each other due to the combustion | In this paper, we are concerned with the two

关键词： 35B20 | 35D30 | 35L04 | 76J20 | 76L99 | 76N10

摘要：The combustion process in rocket-assisted | to improve combustion performance at altitudes of | . Investigating the relationship between combustion performance | and inlet parameters under subsonic-supersonic | subsonic and supersonic airflow mixing via a flat-plate

关键词： Subsonic-supersonic mixing inflow | Vortex structure | Flameholder | Shear layer | Recirculation zone

摘要： injection of kerosene fuel in a kerosene-fueled supersonic | frequencies on the wave family and kerosene combustion | ignition, leading to combustion instability. However, an | average combustion intensity of kerosene with pulse | , the instantaneous combustion intensity at 143 Hz is

关键词： Combustion performance | Ignition delay | Pulse injection | Wave family

摘要： supersonic flow (Mach = 2). The finite volume approach is | selected for the modeling of supersonic airflow and | The ramp injection system has been extensively | used for the fuel distribution and mixing inside the | combustor of scramjet engines. This article presents a

关键词： Supersonic combustion | Computational fluid dynamic | Compressible flow | Fuel mixing | Hydrogen

摘要：The combustion characteristics of a gaseous | achieved in all cases, combustion persisted while fuel | combustion modes according to equivalence ratio, by | within the flow of the combustor. These combustion | hydrogen fueled scramjet combustor were experimentally

关键词： Scramjet engine | Dynamic mode decomposition (DMD) | Supersonic combustion modes | Combustion instability | Shock train

摘要： discharged through a scaled-down GE F-404 supersonic nozzle | engine combustion instabilities can convect downstream | This paper presents a comprehensive overview | of the operation and spectral performance of a | novel lab-scale afterburning jet noise rig at Virginia

关键词： Aeroacoustics | Afterburner | Combustion | Supersonic et noise | Total temperature ratio | Nozzle pressure ratio | Acoustic efficiency | Convective Mach number

摘要： inside a strut-stabilised supersonic combustion ramjet | investigate supersonic, chemically reacting, flow fields | rates. Fully supersonic, fully subsonic and mixed | detail. For certain modes of combustion characterised | modes of combustion, characterised by the presence of

关键词： mode transition | thermal choking | dual-mode scramjet | strut | supersonic | shockwaves

摘要： efficiency and stability of supersonic combustion, paving | process of fuel and air mixing within the combustion | combustion chamber, is approximately equal to 100%, 78% and | beginning of the combustion chamber, the mixing efficiency | © 2024This study delves into the intricate

关键词： Cavity | Combustion chamber | Mixing efficiency | Scramjet engines | Stagnation pressure drop | Vortices

摘要：-dimensional distribution of subsonic/supersonic HR, local | combustion modes, and the variations in HR during the ram | the ejection effect of the supersonic flow, causing | that the mainstream subsonic-diffusion combustion | combustion efficiency at different equivalence ratios. In

关键词： Dual-mode scramjet | Dual composite flame stabilizers | Mode transition | Heat release | Injection schemes

4008-161-200 800-990-8900

国家科技图书文献中心

摘要： problem for simulating a supersonic* reactive flow by* | ABSTRACT High computational complexity due to | rapidly increasing numerical stiffness is a difficult | using the uncoupled method. On the basis of our | previous work, this paper proposes a dual adaptive method

摘要：-dimensional steady supersonic* combustion flows with a* | simplify the two-dimensional steady supersonic combustion | steady combustion* Euler equations with a contact* | are coupled with each other due to the combustion | In this paper, we are concerned with the two

摘要：The combustion* process in rocket-assisted* | to improve combustion* performance at altitudes of* | . Investigating the relationship between combustion* performance* | and inlet parameters under subsonic-supersonic | subsonic and supersonic* airflow mixing via a flat-plate*

摘要： supersonic flow (Mach = 2). The finite volume approach is | selected for the modeling of supersonic* airflow and* | The ramp injection system has been extensively | used for the fuel distribution and mixing inside the | combustor of scramjet engines. This article presents a

摘要：The combustion* characteristics of a gaseous* | achieved in all cases, combustion* persisted while fuel* | combustion modes according to equivalence ratio, by | within the flow of the combustor. These combustion | hydrogen fueled scramjet combustor were experimentally

摘要： discharged through a scaled-down GE F-404 supersonic* nozzle* | engine combustion* instabilities can convect downstream* | This paper presents a comprehensive overview | of the operation and spectral performance of a | novel lab-scale afterburning jet noise rig at Virginia

摘要： inside a strut-stabilised supersonic* combustion ramjet* | investigate supersonic, chemically reacting, flow fields | rates. Fully supersonic, fully subsonic and mixed | detail. For certain modes of combustion* characterised* | modes of combustion, characterised by the presence of

摘要： efficiency and stability of supersonic* combustion, paving* | process of fuel and air mixing within the combustion | combustion chamber, is approximately equal to 100%, 78% and | beginning of the combustion* chamber, the mixing efficiency* | © 2024This study delves into the intricate

摘要：-dimensional distribution of subsonic/supersonic* HR, local* | combustion modes, and the variations in HR during the ram | the ejection effect of the supersonic* flow, causing* | that the mainstream subsonic-diffusion combustion | combustion efficiency at different equivalence ratios. In