<p>The growing demand for hypersonic vehicle development requires accurate ground testing under appropriate thermal and pressure conditions. This study introduces a novel integrated probe capable of simultaneously measuring heat flux and stagnation pressure for arcjet testing. The apparatus incorporates a water-cooled Gardon gauge and dual stagnation pressure ports in a compact design compliant with ESA standards by Guelhan et al. (AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies, 2005). Three experimental campaigns were conducted in the PWK4 arcjet facility at IRS, Germany by Loehle et al. (32nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference, Washington, 2016), under both low- and high-enthalpy conditions. Key findings include: (1) a 2 mm pressure port is sufficient for stable stagnation pressure measurement; (2) graphite paste on the Gardon gauge significantly influences heat flux readings, with paste depletion increasing measured flux due to reduced emissivity; (3) the exposed constantan surface exhibits a higher catalytic effect than oxidized copper, leading to elevated heat flux values compared with calorimeter references; and (4) both the pressure and heat flux profiles decrease with radial distance from the center, consistent with the arc heater configuration in which the arc is concentrated along the central axis. The subsequent expansion of the high-enthalpy core flow through the nozzle further enhances this radial gradient, resulting in higher values at the centerline. The integrated probe demonstrated durability, repeatability, and sensitivity to surface conditions, providing a reliable tool for pinpoint heat flux measurements in high-enthalpy arcjet testing.</p>