Laser & Optoelectronics Progress, Volume. 61, Issue 13, 1300010(2024)

Advancements in Tunable Diode Laser Absorption Spectroscopy for Hypersonic Wind Tunnel Testing

Hongxin Fang1,2,3, Dong Zhi2,3、*, Xuecheng Wu1, Yunfei Li2,3, Yu Chang2,3, Wei Chen2,3, and Rongzong Kong2,3
Author Affiliations
  • 1Polytechnic Institute, Zhejiang University, Hangzhou 310015, Zhejiang , China
  • 2Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621050, Sichuan , China
  • 3Laboratory of Aerodynamics in Multiple Flow Regimes, China Aerodynamics Research and Development Center, Mianyang 621050, Sichuan , China
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    Figures & Tables(14)
    Schematic diagram of direct absorption spectroscopy
    Flow velocity measurement optical path layout diagram. (a) Single-channel laser reflection method; (b) dual-optical path flow velocity measurement method
    Schematic diagram of wavelength modulation spectroscopy
    Four light-path configurations with protecting structure of TDLAS on 2DSM-B[39]
    Experimental layout for water vapor absorption measurement in the LENS I wind tunnel[22]. (a) Plan view of the water vapor absorption measurement experimental device in the LENS I wind tunnel; (b) schematic layout of the electronic and optical components in the probe and the remote laser control system
    Experimental layout of nitric oxide absorption measurement in LENS I wind tunnel[22]. (a) Physical diagram of temperature and concentration measurement; (b) physical diagram of velocity measurement
    Top-view schematic diagram of the experimental optical workbench setup[19]
    Schematic of T5 facility measurement scheme[62]
    TDLAS schematic diagram of T-ADFA wind tunnel[64-65]
    Layout of TDLAS experiments inside and outside the wind tunnel[71-72]
    3-beam experiment with attenuation tube[73]. (a) Physical picture; (b) optical path diagram
    Layout and the result of the shear layer shielding experiments[74]. (a) Physical picture; (b) experimental result picture
    TDLAS optical path design[74]. (a) Single perpendicular beam; (b) single-angled beam; (c) shear layer shield; (d) double-beam velocity
    • Table 1. Hypersonic wind tunnels conducting TDLAS tests abroad[52-56]

      View table

      Table 1. Hypersonic wind tunnels conducting TDLAS tests abroad[52-56]

      Nomenclature of facilityCompanyPurposeSpecification
      LENS IThe Calspan University at Buffalo Research CenterResearch on fluid dynamics problems of complex turbulent interference under high Reynolds number, high Mach number, and low enthalpy conditions. Advanced interception systems and scramjet engines from Mach 6 to 12. Measurements on a full-scale X43 Scramjet flow path. Perform aero-optic and radiation analysis of optical seeker heads

      Ma 6.5—24,

      Re 1×105—1×109 ft-1

      height 7.6—91 km, total pressure 3.5—150 MPa,

      total temperature <6300 K (helium) & <7780 K (hydrogen), test time 3—24 ms

      LENS IIThe Calspan University at Buffalo Research CenterAero-thermal loads and the propulsion system Performance of a full scale replica of the X-51 Scramjet vehicle. Aerothermal and aero-optical evaluation tests. Shroud separation from the HyFly Scramjet. Shock wave -turbulent boundary layer interaction and high Reynolds number, high enthalpy flows

      Ma 2—12,

      Re 1×105—1×109 ft-1

      height SL-200 kft,

      test time 100 ms (shock tunnel mode) & 320 ms (Ludwig tube mode)

      LENS XXThe Calspan University at Buffalo Research CenterIt is mainly used to study the effects of real gas effects, impact layer chemistry, viscous interactions and ablation on the performance of ultra-high-speed aircraft. Spectroscopic measurements in clean air from NASA’s Planetary Entry Program

      Ma 8—25,

      Re 1×103—1×109 ft-1

      height SL-250 kft,

      Maximum stagnation temperature: 45000 oR

      total enthalpy 120 MJ/kg,

      test time 0.5—4 ms

      T5California Institute of TechnologyAir thermodynamic design, flow field diagnosis, thermal protection materials and physical and chemical reaction research of high-enthalpy air flow

      Ma 4—7,

      total enthalpy 20 MJ/kg,

      total pressure 30 kPa,

      maximum total temperature 2000 K,

      test time about 1 ms

      T-ADFAThe University of New South WalesIt can simulate conditions for entry into Earth and hypersonic air-breathing flight, and has developed state-of-the-art laser-based methods to measure temperature, gas composition and velocity in these extremely fast-flow environments

      Ma 12,

      enthalpy value 13.5 MJ/kg,

      total temperature 354 K,

      total pressure 300 Pa,

      test time 1 ms

      HIESTJAXANon-equilibrium aerothermodynamics. Simulates dissociated gases and higher density free streams. Very effective for scramjet research moderate enthalpy conditions are simulated in HIEST.High Launched Orbiting Plane was experimentally tested in HIEST facility

      Test section size diameter 600 mm,Ma 13,

      enthalpy value 7.5 MJ/kg,

      total temperature 740 K,

      total pressure 2900 psia,

      test time 2 ms

      Longshot piston driven impulse hypervelocity facilityVKIProvides very high Reynolds number hypersonic airflow

      Ma 12, 14, 10—20,

      Re 10×106 m-1

      enthalpy value 3 MJ/kg,

      total pressure 400 MPa,

      total temperature 2500 K,

      test time 20—80 ms

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    Hongxin Fang, Dong Zhi, Xuecheng Wu, Yunfei Li, Yu Chang, Wei Chen, Rongzong Kong. Advancements in Tunable Diode Laser Absorption Spectroscopy for Hypersonic Wind Tunnel Testing[J]. Laser & Optoelectronics Progress, 2024, 61(13): 1300010

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    Paper Information

    Category: Reviews

    Received: Oct. 31, 2023

    Accepted: Nov. 27, 2023

    Published Online: Jul. 17, 2024

    The Author Email: Dong Zhi (zhidong38173103@163.com)

    DOI:10.3788/LOP232396

    CSTR:32186.14.LOP232396

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