The experimental measurements of gaseous pressure and temperature histories at the end of the resonance cavities of three types of resonance tubes

i. e.

cylindrical

cone and cone-cylinder shaped tubes were carried out by employing high frequency heat - resistant pressure transducers and thermocouples. The experimental results confirm that the intense oscillating shock wave accumulating dissipation is surely the major heating mechanism of the resonance tube. The gas in the tube is irreversibly compressed to a high time-averaged temperature over the stagnation temperature of the jet. The results also show that resonance tube heating effects are related to the pressure oscillations in the tubes

whereas the pressure oscillations are related to the pressure of the driving gas

and further

different types of resonance tubes have significantly different heating properties. The results are useful for actual designing of resonance tube igniters of liquid rocket engines and can be used as typical data for verifying correctness of numerical simulation.