This thesis presents the use of an unsteady total pressure measurement to detect laminar-to-turbulent transition. A miniature dynamic pressure transducer, Kulite model XCS-062-5D, was utilized to measure the total pressure fluctuations, and was integrated with an autonomous boundary layer measurement device that can withstand flight test conditions. Various sensor-probe configurations of the Kulite pressure transducer were first examined in a wind tunnel with a 0.610 m (2.0 ft) square test section with a maximum operational velocity of 49.2 m/s (110 mph), corresponding dynamic pressure of 1.44 kPa (30 psf). The Kulite sensor was placed on an elliptical nose flat plate where the flow was known to be turbulent. The Kulite sensor was then evaluated to measure total pressure fluctuations in laminar, turbulent, and transition of boundary layers developed on the flat plate in the same wind tunnel. The root-mean-square value of total pressure fluctuations was less than 1 % of the local free-stream dynamic pressure in the laminar boundary layer, but was about 2 % in the turbulent boundary layer. The value increased to 4 % in transition, indicating that the total pressure fluctuation measurements can be used not only to distinguish the laminar boundary layer from the turbulent boundary layer, but also to identify the transition region. The unsteady total pressure measurement was also conducted in a with a 2.13 m (7.0 ft) by 3.05 m (10.0 ft) section with similar operational velocity range as the previous wind tunnel. The Kulite sensor was placed on a wing model under laminar and transition conditions. The testing yielded similar results, demonstrating the usefulness of total pressure measurement for identifying the laminar-to-turbulent transition.

An experimental investigation of the use low-cost microphones for unsteady total pressure measurement to detect transition from laminar to turbulent boundary layer flow has been conducted. Two small electret condenser microphones, the Knowles FG-23629 and the FG-23742, were used to measure the pressure fluctuations and considered for possible integration with an autonomous boundary layer measurement system. Procedures to determine the microphones’ maximum sound pressure levels and frequency response using an acoustic source provided by a speaker and a reference microphone. These studies showed that both microphones possess a very flat frequency response and that the max SPL of the FG-23629 is 10 Pa and the max SPL of the FG-23742 is greater than 23 Pa. Several sensor-probe configurations were developed, and the three best were evaluated in wind tunnel tests. Measurements of the total pressure spectrum, time signal, and the root-mean-square were taken in the boundary layer on a sharp-nose flat plate in the Cal Poly 2 foot by 2 foot wind tunnel at dynamic pressures ranging between 135 Pa and 1350 Pa, corresponding to freestream velocities of 15 m/s to 47 m/s. The pressure spectra were collected to assess the impact of the probe on the microphone frequency response. The two configurations with long probes showed peaks in the pressure spectra corresponding to the resonant frequencies of the probe. The root-mean-square of the pressure fluctuations did not vary much between the different probes. The root-mean-square of the pressure fluctuations collected in turbulent boundary layers were found to be 10% of the local freestream dynamic pressure and decreased to 3.5% as the freestream dynamic pressure was increased. The RMS of the pressure fluctuations taken in both laminar boundary layers and in the freestream varied between 0.5% and 2.5% of the local freestream dynamic pressure. The large difference between the RMS of the pressure fluctuations in laminar and turbulent boundary layers taken at low dynamic pressures suggests that this system is indeed capable of distinguishing between laminar and turbulent flow. The drop in the RMS of the pressure fluctuations as dynamic pressure increased is indicative of insufficient maximum sound pressure level of the microphone resulting in clipping of the pressure fluctuation; this is confirmed through inspection of the pressure time signal and spectrum. Thus, a microphone with higher maximum sound pressure level is needed for turbulence detection at higher dynamic pressures. Alternatively, it may be possible to attenuate the total pressure fluctuation signal.