ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Experimental verification of PIV-based measurement for reconstructing thrust performance of supersonic nozzles
Received date: 2024-08-28
Revised date: 2024-09-13
Accepted date: 2024-10-10
Online published: 2024-10-29
Supported by
National Natural Science Foundation of China(12332018)
The conventional force measurement system using the balance has the problem of only being able to measure the overall load but unable to decouple the contribution of individual components， which limits the exploration of the flow mechanism behind aerodynamic load. With the development of Particle Image Velocimetry （PIV） technology， the PIV-based aerodynamic load measurement technology was developed， which can indirectly measure aerodynamic load by reconstructing multiple physical fields such as pressure and density. However， the performances of conventional pressure reconstruction methods were severely deteriorated when applied to supersonic flow fields. This drawback limits the application of reconstruction measurement methods in supersonic nozzles. To resolve this issue， a method for reconstructing the supersonic pressure field based on the Flux Vector Splitting （FVS） technique was proposed， and a thrust performance measurement scheme for supersonic nozzles based on PIV was established. PIV experiments on the Single Expansion Ramp Nozzle （SERN） were conducted using the direct-connect wind tunnel. Multiple physical fields and aerodynamic performance parameters such as flow rate， thrust， and lift were reconstructed under typical operating conditions. The evaluation results show that the data reconstructed by the FVS method possessed higher accuracy and better self-consistency， satisfying the laws of mass and momentum conservation. The relative errors of thrust and lift under overexpansion conditions were only -1.70% and 0.60%， respectively. The local errors of wall pressure after shock wave were lower than 3%. The performance of the proposed method is shown to be better than that of the conventional Poisson method and Spatial Integration（SI） method. Therefore， the experimental results verify the feasibility and high accuracy of the PIV-based thrust performance reconstruction measurement method when applied in supersonic nozzles， which can provide effective data supplementation to force measurement with the balance.
Jie TIAN , Jinglei XU , Junfei ZHOU , Le CAI , Shun LIU . Experimental verification of PIV-based measurement for reconstructing thrust performance of supersonic nozzles[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2025 , 46(17) : 131114 -131114 . DOI: 10.7527/S1000-6893.2024.31114
| [1] | TROPEA C， YARIN A L， FOSS J F. Springer handbook of experimental fluid mechanics［M］. Cham： Springer， 2007： 564-596. |
| [2] | RIVAL D E， VAN OUDHEUSDEN B. Load-estimation techniques for unsteady incompressible flows［J］. Experiments in Fluids， 2017， 58（3）： 20. |
| [3] | 金捷， 陈敏. 涡轮冲压组合动力装置特点及研究进展［J］. 航空制造技术， 2014， 57（9）： 32-35. |
| JIN J， CHEN M. Brief introduction on technology development of turbine based combined cycle engine［J］. Aeronautical Manufacturing Technology， 2014， 57（9）： 32-35 （in Chinese）. | |
| [4] | 蔡国飙， 徐大军. 高超声速飞行器技术［M］. 北京： 科学出版社， 2012： 102-115. |
| CAI G B， XU D J. Hypersonic aircraft technology［M］. Beijing： Science Press， 2012： 102-115 （in Chinese）. | |
| [5] | CHEN K S， XU J L， QIN Q H， et al. Modular design framework of an axisymmetric wrap-around thrust-optimized combined nozzle［J］. Aerospace Science and Technology， 2022， 127： 107690. |
| [6] | JONES B M. Profile drag［J］. The Aeronautical Journal， 1937， 41（317）： 339-368. |
| [7] | RAFFEL M， WILLERT C E， SCARANO F， et al. Particle image velocimetry： A practical guide［M］. 3rd ed. Cham： Springer， 2018： 15-29. |
| [8] | ADRIAN R J. Twenty years of particle image velocimetry［J］. Experiments in Fluids， 2005， 39（2）： 159-169. |
| [9] | UNAL M F， LIN J C， ROCKWELL D. Force prediction by PIV imaging： A momentum-based approach［J］. Journal of Fluids and Structures， 1997， 11（8）： 965-971. |
| [10] | NOCA F， SHIELS D， JEON D. A comparison of methods for evaluating time-dependent fluid dynamic forces on bodies， using only velocity fields and their derivatives［J］. Journal of Fluids and Structures， 1999， 13（5）： 551-578. |
| [11] | VAN OUDHEUSDEN B W， SCARANO F， CASIMIRI E W F. Non-intrusive load characterization of an airfoil using PIV［J］. Experiments in Fluids， 2006， 40（6）： 988-992. |
| [12] | RAGNI D， VAN OUDHEUSDEN B W， SCARANO F. Drag coefficient accuracy improvement by means of particle image velocimetry for a transonic NACA0012 airfoil［J］. Measurement Science and Technology， 2011， 22（1）： 017003. |
| [13] | VAN OUDHEUSDEN B W. Principles and application of velocimetry-based planar pressure imaging in compressible flows with shocks［J］. Experiments in Fluids， 2008， 45（4）： 657-674. |
| [14] | VAN OUDHEUSDEN B W. PIV-based pressure measurement［J］. Measurement Science and Technology， 2013， 24（3）： 032001. |
| [15] | ZACHOS P K， FRASCELLA M， MACMANUS D G， et al. Pressure flowfield and inlet flow distortion metrics reconstruction from velocity data［J］. AIAA Journal， 2017， 55（9）： 2929-2941. |
| [16] | LIU S， XU J L， YU K K. MacCormack’s technique-based pressure reconstruction approach for PIV data in compressible flows with shocks［J］. Experiments in Fluids， 2017， 58（6）： 64. |
| [17] | LIU S， XU J L. Assessment of pressure field and performance parameter reconstruction from velocity data for ramjet inlet［J］. Aerospace Science and Technology， 2021， 110： 106454. |
| [18] | 刘顺， 孔祥瑞， 徐惊雷， 等. 基于PIV的冲压发动机喷管推力的重构测量方法［J/OL］. 北京航空航天大学学报， （2023-11-07）［2024-08-28］. . |
| LIU S， KONG X R， XU J L， et al. Reconstruction measurement method for ramjet nozzle thrust based on PIV［J/OL］. Journal of Beijing University of Aeronautics and Astronautics， （2023-11-07）［2024-08-28］. （in Chinese）. | |
| [19] | LV Z， XU J L， MO J W. Numerical investigation of improving the performance of a single expansion ramp nozzle at off-design conditions by secondary injection［J］. Acta Astronautica， 2017， 133： 233-243. |
| [20] | ANDERSON J D Jr.， Computational fluid dynamics： The basics with applications［M］. New York： McGraw-Hill Higher Education， 1995： 53-67. |
| [21] | STEGER J L， WARMING R F. Flux vector splitting of the inviscid gasdynamic equations with application to finite-difference methods［J］. Journal of Computational Physics， 1981， 40（2）： 263-293. |
| [22] | VAN LEER B. Flux-vector splitting for the Euler equations［C］∥Eighth International Conference on Numerical Methods in Fluid Dynamics. Berlin： Springer， 1982： 507-512. |
| [23] | YU K K， XU J L， ZHANG X F， et al. Inverse design of shock wave distortion for a direct-connect facility［J］. Aerospace Science and Technology， 2016， 55： 220-226. |
| [24] | 齐伟呈， 徐惊雷， 范志鹏， 等. 马赫数2~4连续可调风洞数值模拟及静态标定试验［J］. 航空学报， 2017， 38（1）： 120155. |
| QI W C， XU J L， FAN Z P， et al. Numerical simulation and experimental calibration of continuously adjustable wind tunnel with Mach number 2 to 4［J］. Acta Aeronautica et Astronautica Sinica， 2017， 38（1）： 120155 （in Chinese）. |
/
| 〈 |
|
〉 |
CJA