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Abstract <p>High-speed applications, particularly those involving hypersonic flow conditions, pose significant challenges for measurement systems due to the rapid variations in the measurand. Measurement devices must respond quickly and settle within a short time frame to provide accurate data. Hypersonic test facilities, which simulate high Mach number flows, are characterized by extremely short test durations, further complicating the measurement process. Heat flux measurement in such environments is particularly difficult due to the limited time available for data collection. This study presents the development of a fast-response transient heat flux sensor designed to operate effectively in ultra-short test times. The sensor, a lab-developed co-axial K-type thermocouple, has been optimized for use in hypersonic testing scenarios. A numerical simulation was conducted using ANSYS to determine the optimal dimensions for the sensor, ensuring that it can capture rapid thermal transients with high accuracy. The sensor performance was evaluated in a hypersonic wind tunnel, where it demonstrated quick thermal response, making it suitable for transient heat flux measurements in high-speed testing environments.</p>

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Transient Heat Flux Measurement Sensor for High-speed Applications

  • 期刊论文

  • 发表日期：

    2026年2月1日

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  • Shamim Pathan,
  • Omkar Patil,
  • Kaustubh Patil,
  • Shreyash Parab,
  • Rupesh Chaudhari,
  • Nilaj Deshmukh

摘要

Abstract

High-speed applications, particularly those involving hypersonic flow conditions, pose significant challenges for measurement systems due to the rapid variations in the measurand. Measurement devices must respond quickly and settle within a short time frame to provide accurate data. Hypersonic test facilities, which simulate high Mach number flows, are characterized by extremely short test durations, further complicating the measurement process. Heat flux measurement in such environments is particularly difficult due to the limited time available for data collection. This study presents the development of a fast-response transient heat flux sensor designed to operate effectively in ultra-short test times. The sensor, a lab-developed co-axial K-type thermocouple, has been optimized for use in hypersonic testing scenarios. A numerical simulation was conducted using ANSYS to determine the optimal dimensions for the sensor, ensuring that it can capture rapid thermal transients with high accuracy. The sensor performance was evaluated in a hypersonic wind tunnel, where it demonstrated quick thermal response, making it suitable for transient heat flux measurements in high-speed testing environments.