Effect of Engine Integration on the Aerodynamic Characteristics of a Spaceplane

Fujii, Kozo; Tamura, Yoshiaki

doi:10.1080/10618569708940806

Cited by 6 publications

(4 citation statements)

References 3 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The computational code used in the present study has been used for a wide variety of flow field and validated in the past. [6,7] Although there is no experimental data available for the comparison, the code has been used for the annular aerospike nozzle flow fields and showed good agreement with the experiment. [2] 4 Truncation and the effect on the nozzle performance…”

Section: Methodsmentioning

confidence: 89%

Numerical Analysis of the Clustered Type Aerospike Nozzle Flow: Flow Structures and Thrust Performance

Ito

Fujii

2003

Computational Fluid Dynamics 2002

View full text Add to dashboard Cite

Abstract. Fundamental characteristics of the clustered type aerospike nozzle is analyzed by the computational fluid dynamics approach. The base thrust of the aerospike nozzle plays an important role to maintain the thrust even in high spike-length truncations. The pressure at the tip of the ramp increases and stronger expansion occurs toward the nozzle axis for lower module number nozzles. The stagnation pressure increases and consequently the base pressure increases for lower module number nozzles. The thrust loss at the ramp is the major reason for the performance decrease for the lower module number aerospike nozzles.

show abstract

Section: Methodsmentioning

confidence: 89%

Numerical Analysis of the Clustered Type Aerospike Nozzle Flow: Flow Structures and Thrust Performance

Ito

Fujii

2003

Computational Fluid Dynamics 2002

View full text Add to dashboard Cite

show abstract

“…The Yee‐Harten upwind scheme was used for explicit time‐integration. The computer programs were used for a wide variety of CFD applications and validated by the comparison with experiments 2,7–9. Only two results from explicit time‐integration are shown here.…”

Section: Comparison Between Cfd and The Experimental Resultsmentioning

confidence: 99%

Visualization of Jet Flows over a Plate by Pressure‐Sensitive Paint Experiments and Comparison with CFD

Fujii¹,

Tsuboi²,

Fujimatsu³

2002

Annals of the New York Academy of Sciences

View full text Add to dashboard Cite

Flow fields created by underexpanded sonic jets impinging on an inclined flat plate were studied experimentally using the pressure sensitive paint (PSP) measurement technique. The measurement system and some representative results are presented here. Two binders, thin-layer chromatography (TLC) plates and anodized aluminum (A-A) plates were tested with bathophen ruthenium chloride as a luminophore. The results show that both the binders can be used. TLC plates are preferable because their luminescent intensity is almost twice that of the A-A plates. Quantitative measurements require accurate temperature calibration. A preliminary effort to elucidate the flow structure by combining the PSP results with a computer simulation of the same flow field is presented. Although good agreement is obtained between the experimental and numerical results, future quantitative comparisons are necessary to yield a useful tool in the analysis of the jet-plate interaction flows.

show abstract

“…The computational code used in the present study has been used for a wide variety of flow fields and was validated in the past. 15,16) Although there is no experimental data available for comparison, the code was used for cone-type aerospike nozzle flow fields and showed good agreement with the experiment.…”

Section: Methodsmentioning

confidence: 99%

Flow Field and Performance Analysis of an Annular-Type Aerospike Nozzle with Base Bleeding

Ito

Fujii

2003

Trans. Japan Soc. Aero. S Sci.

View full text Add to dashboard Cite

Aerospike nozzle flow fields are computationally analyzed by Navier-Stokes simulations. The secondary flow from the base surface is induced for the purpose of increasing total thrust. The computed result shows that base pressure efficiently increases when base bleeding is induced from the tip region of the base surface and injected radially inward towards the nozzle axis. The base bleeding induced at the tip of the base and injected horizontally with the axis produces maximum base thrust because the momentum thrust does not produce any divergence loss and the base pressure is kept high. Base bleeding induced against the existing recirculation flow results in lower base pressure distributions. Base bleeding that produces maximum thrust interacts with the exhaust flow and creates shock waves that emanate from the tip of the base. The shear layer is squeezed more towards the nozzle axis when base bleeding is induced and forces the stagnation point to move closer to the base surface.

show abstract

Effect of Engine Integration on the Aerodynamic Characteristics of a Spaceplane

Cited by 6 publications

References 3 publications

Numerical Analysis of the Clustered Type Aerospike Nozzle Flow: Flow Structures and Thrust Performance

Numerical Analysis of the Clustered Type Aerospike Nozzle Flow: Flow Structures and Thrust Performance

Visualization of Jet Flows over a Plate by Pressure‐Sensitive Paint Experiments and Comparison with CFD

Flow Field and Performance Analysis of an Annular-Type Aerospike Nozzle with Base Bleeding

Contact Info

Product

Resources

About