Aerodynamic database development for the Hyper-X airframe integrated scramjet propulsion experiments

Walter, Carl E.; Scott, D Holland; Cockrell, Jr Charles E.; Robert, D Bittner

doi:10.2514/6.2000-4006

Cited by 14 publications

(4 citation statements)

References 4 publications

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“…For the advanced concept, the aerospike nozzle portion appears as the external nozzle. Note that in this study, the primary thrust direction is different than that of the installation used in the X-43A [27][28]. The primary thruster in this study is inclined toward the center line of the airframe axis, and therefore, the external nozzle (as an aerospike nozzle) plays a role in the compression wall for the primary engine flow.…”

Section: Advanced Airframe-integrated Propulsion Conceptsmentioning

confidence: 96%

“…Unlike this idea, the concept of providing the bypass flow in this study attempts to utilize the large amount of air flow as the virtual boattail flow for thrust augmentation. For this concept, the airframe-integrated propulsion system is critical in the design of the vehicle because the forebody is part of the inlet, whereas the aft section functions as an exhaust nozzle [23,27]. Additionally, the bypass flow concept combined with an aerospike nozzle is expected to have the advantage of causing less acoustic drag because the plug nozzle system [29] caused less acoustic drag than conventional bell-shaped nozzles.…”

Section: Advanced Airframe-integrated Propulsion Conceptsmentioning

confidence: 99%

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Performance Evaluation of Airframe-Integrated Aerospike Propulsion Systems in Off-Design Flight Conditions

Takahashi

Tomita

Tomioka

2015

53rd AIAA Aerospace Sciences Meeting

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The thrust performance of airframe-integrated linear aerospike propulsion systems for high-speed aircraft operated under off-design in-flight conditions was evaluated, based on performance prediction models established for linear aerospike nozzles by accounting for the freestream effect.The airframe configuration, equipped with a boattail appearing to the right upstream of the primary cell nozzle exit, enabled the freestream effect to be utilized for increasing the spike surface pressure.Performances of each thrust component were predicted by using the physics-based models established in separately performed studies. First, a parametric study was conducted on a rocket primary thruster with various design parameters. Then, an advanced concept with an airbreathing primary propulsion system was evaluated for its feasibility by comparing its thrust performance with that of a conventional rocket primary thruster. The benefit of the aerospike nozzle integrated into the airframe was also evaluated by comparing its thrust to a configuration without the aerospike nozzle.Results showed that the employment of the aerospike nozzle offered improved performance from takeoff to cruise phases. The advanced concept using the bypass airbreathing system for the primary thruster followed by the aerospike configuration exhibited further improvement in thrust by compensating for the boattail drag.

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Section: Advanced Airframe-integrated Propulsion Conceptsmentioning

confidence: 96%

Section: Advanced Airframe-integrated Propulsion Conceptsmentioning

confidence: 99%

Performance Evaluation of Airframe-Integrated Aerospike Propulsion Systems in Off-Design Flight Conditions

Takahashi

Tomita

Tomioka

2015

53rd AIAA Aerospace Sciences Meeting

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“…The phenomenon known as creep was initially introduced in Andrade's scholarly publication and has been a subject of study for over a millennium [7]. Currently, there exist three primary categories for the study and implementation of creep calculation.…”

Section: Creep Modelmentioning

confidence: 99%

“…The relationship between plastic deformation and creep has nothing to do with time. The theoretical formula [7] is…”

Section: 11mentioning

confidence: 99%

Review on Creep Phenomenon and Its Model in Aircraft Engines

Yuan,

Chenglong,

Yongchao

et al. 2023

International Journal of Aerospace Engineering

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The aircraft is subjected to high-temperature and high-pressure conditions during flight, which renders it susceptible to the occurrence of creep phenomenon. Several academics have conducted extensive research on this issue. This research paper provides a comprehensive overview of the existing literature on creep phenomena in aircraft engines. First, several classical creep calculation models are enumerated and categorized as creep life calculation, creep-fatigue life calculation, and creep deformation calculation. Studies on creep phenomena are conducted in various components of aircraft engines, such as the engine’s turbine blades, turbine disks, and combustion chambers. The creep behavior of turbine blades in aircraft engines has been extensively researched. Furthermore, the protective measures aimed at mitigating creep are presented. Materials with high creep resistance can be used, and alternative fuels could be implemented. This paper provides an in-depth analysis of the advantages of creep in aircraft, presented in a favorable perspective. Finally, the prospective future research direction is discussed.

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Theoretical Background

2022

Scramjet Propulsion

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Aerodynamic database development for the Hyper-X airframe integrated scramjet propulsion experiments

Abstract: This paper provides an overview of the activities associated with the aerodynamic database which is be-

Cited by 14 publications

References 4 publications

Performance Evaluation of Airframe-Integrated Aerospike Propulsion Systems in Off-Design Flight Conditions

Performance Evaluation of Airframe-Integrated Aerospike Propulsion Systems in Off-Design Flight Conditions

Review on Creep Phenomenon and Its Model in Aircraft Engines

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