Effects of Nozzle Roughness on the Streamwise Streaks in Underexpanded Jets -- An Experimental Study

TL;DR

This experimental study examines how nozzle exit roughness influences streamwise streak formation in underexpanded jets, revealing that geometric perturbations significantly affect flow structures and noise patterns.

Contribution

It demonstrates the impact of geometric perturbations at the nozzle exit on streak formation, highlighting the role of perturbation wavenumber in flow pattern development.

Findings

Low-wavenumber perturbations produce smaller streak growth rates.

Streak patterns correlate with geometric perturbations at higher wavenumbers.

Rotating the smooth nozzle yields similar streak patterns, indicating origin from geometric roughness.

Abstract

The present study investigated the formation of streamwise streaks in underexpanded jets from round sonic nozzles, based on direct experimental observation using high-speed schlieren imaging and PLIF methods. The effect of geometric perturbations of the nozzle exit on the streamwise flow structure was examined through a series of comparative experiments. Underexpanded jets were generated in a vacuum chamber using phi-4 mm nozzles of two different configurations: (a) a "smooth" nozzle, shaped and polished by a high-quality commercial lathe machine; and (b) nozzles with artificially introduced sinusoidal perturbation of various wavenumbers on the circular contour of the exit. In the case of the "smooth" nozzle, experiments were repeated following a 60-degree rotation of the nozzle along its axis, and a similar rotation in the streak patterns was observed. This suggests that the streamwise streaks most likely originated from geometric perturbations caused by the minute roughness at the nozzle exit. In the latter case, the effects of modal distribution of geometric perturbation on the streaks were further investigated. The results showed that the low-wavenumber (k < 5) perturbations exhibited much smaller growth rates of streamwise streaks - likely dominated by residual roughness similar to the "smooth" case - compared to higher-wavenumber (k = 6 and 7) perturbations, where the streak patterns were observed to correlate geometrically with the perturbed nozzle exit contour. Results from the present study should prove useful in enhancing the current understanding of noise patterns in supersonic wind tunnel tests, where nozzles are critical components.