Heat transfer measurements of a nanoscale hot-wire in supersonic flow

Upon its development and initial characterization, the supersonic variant of nanoscale thermal anemometry probe (S-NSTAP) was deployed in a wind tunnel facility, where both freestream boundary layer measurements were obtained at $$M_\infty =2$$ . The low operating stagnation pressures generated reliable data, effects Reynolds number, Mach number overheat ratio on sensor’s heat transfer investigated detail. performance S-NSTAP also compared to that conventional cylindrical hot-wire shown exhibit unparalleled temporal resolution ( $$\sim $$ 300 kHz). mass flux sensitivity coefficient hot-wires further computed appeared vary between probes, yielding twice as large for than S-NSTAP. experimental data from compared, via spectral analysis turbulence statistics, results numerically modelled turbulent layer.