Design method with controllable velocity direction at throat for inward-turning inlets

Qiao, Wenyou; Yu, Anyuan; Gao, Wei; Wang, Weixing

doi:10.1016/j.cja.2019.04.012

Cited by 15 publications

(5 citation statements)

References 19 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…δ l ρ is defined as the first-order derivative of the density in the direction of velocity; the relevant calculation results have been proven to be highly reliable (Post et al, 2003). The sign of δ l ρ also has physical meaning.…”

Section: Influence Of Different Incoming Flow Conditions On the Flow ...mentioning

confidence: 99%

“…In the design stage of the inward-turning inlet, a flowthrough flow field without backpressure can be directly obtained , Wang et al, 2017, Wenyou et al, 2019, Xiong et al 2019). To improve the design method, several studies have been conducted in which the characteristics of the flow-through flow field of the inward-turning inlet have been examined.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Development and evolution mechanism of streamwise vortex in an inward-turning inlet

Wang,

Xin,

Chen

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

The three-dimensional flows in an inward-turning inlet were numerically investigated at different incoming flow conditions. When the incoming flow conditions change, the shock angle and the shock interaction form of the external compression wave change, and the development of the near-wall low-energy fluid and the streamwise vortex is also affected. The impingement of the shock wave leads to a sharp increase in the vorticity of the low kinetic energy fluid. Under the pressure gradient caused by the shock wave, the high-vorticity fluid migrates from the cowl to the ramp and entrains the mainstream fluid to form a streamwise vortex, for which the velocity gradient ( ∂v/ ∂y + ∂w/ ∂z) along the vortex axis can accurately determine the rotation direction and the Hopf bifurcation position. By considering high Reynolds number flows, the pressure gradient along the vortex axis is developed to estimate the simplified dilation term (velocity gradient) due to its ease of measurement. However, the pressure gradient ( ∂p/ ∂x) along the vortex axis can lead to bias when evaluating the cross-flow state of the streamwise vortex, with the shock wave structure and high-vorticity fluid leading to under- and overestimation, respectively. This study provides a theoretical basis for an accurate determination of the flow state of a streamwise vortex in an inward-turning inlet and thus lays the foundation for effective vortex control.

show abstract

Section: Influence Of Different Incoming Flow Conditions On the Flow ...mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Development and evolution mechanism of streamwise vortex in an inward-turning inlet

Wang,

Xin,

Chen

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…The two-dimensional supersonic inlet is divided into conventional multi-stage wedge compression inlet and curved surface compression [13][14][15] inlet according to the external compression forms. Here we call them Case A and Case B, respectively.…”

Section: External Compression Configuration and Diffuser Designmentioning

confidence: 99%

Experimental and numerical investigation on a supersonic inlet with large bleed window

et al. 2021

View full text Add to dashboard Cite

The design of a two-dimensional supersonic inlet with large bleed window at low Mach number was developed. Numerical simulation and wind tunnel experiments were carried out to investigate the aerodynamic performance and variable geometric rules of the inlet. The result indicates that the single-degree-of-freedom variable geometry scheme adopted in this paper guarantees the steady work of the inlet over a wide speed range. The large bleed window caused by rotation of the compression ramp appears near the throat at low Mach number. Low-pressure airflow near the bleed window neutralises the original high-pressure airflow behind the shock train, which decreases the overall pressure of the downstream region of the internal contraction section. To match the lower pressure, the structure of the shock train changes from strong $\lambda$ -type to weak $\lambda$ -type, and finally to a normal shock wave as backpressure increases at Mach number 2.5. Herein, the total pressure recovery coefficient of the inlet near the critical condition improves by 8.5% as the backpressure ratio (Pe/P0) adds from 13 to 14.6 at Mach number 2.5. It proves that the scheme is effective on terminal shock wave control and inlet performance improvement. In addition, due to the background wave and the bleed window, two kinds of shock wave oscillation occur when the backpressure ratio is 13.1.

show abstract

“…5 To give consideration to the practicability, more and more design appeared, such as the truncated Busemann flowfield, 6 the merged ICFA/ Busemann flowfield, 7 the inverted isentropic nozzle flowfield, 8 and the flowfield with controllable wall pressure 9 /Mach number distribution 10 /throat velocity direction. 11 Axisymmetric flow configurations with incident/reflected shock waves are the common characteristic of almost all of the current inward-turning flowfields.…”

Section: Introductionmentioning

confidence: 99%

Design studies on NAGIC flowfield with application to integrated irregular-shaped supersonic inlet

Zhou

Zhi-guang

Deng

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

Fighters have increasingly demanding performance on both aerodynamic and stealth. To adapt the design requirement of various irregular-shaped supersonic inlets integrated with flat fuselages, a design method for non-axisymmetric generalized internal conical (NAGIC) flowfield is discussed and then developed. By osculating axisymmetric flow concept and method of characteristics, the developed supersonic NAGIC flowfield can be inversely designed with arbitrary capture curves, controllable incident/terminal shock wave geometries, and post terminal shock wave pressure. Employing the streamline tracing technique, a set of external-compression inward-turning inlets with triangle-like flat capture shapes for supersonic stealth fighters are obtained to verify the design method. The study find that the internal contraction ratio and flow distortion of the inlet are reduced significantly by replacing the weak reflected shock wave in the original hypersonic NAGIC flowfield with a strong one. Thus, the compatibility between inlet and engine is improved in a relatively wide range. In addition, the irregular-shaped curved-compression inlet has high mass ratio and total pressure recovery ratio with negligible cross flow and uniform flow at throat. The performance of inlets with complex configurations can be further improved by matching the entrance geometries of basic flowfields and inlets.

show abstract

Design method with controllable velocity direction at throat for inward-turning inlets

Cited by 15 publications

References 19 publications

Development and evolution mechanism of streamwise vortex in an inward-turning inlet

Development and evolution mechanism of streamwise vortex in an inward-turning inlet

Experimental and numerical investigation on a supersonic inlet with large bleed window

Design studies on NAGIC flowfield with application to integrated irregular-shaped supersonic inlet

Contact Info

Product

Resources

About