M. Salikuddin

Scale model tests were conducted to measure the aerodynamic performance and internal surface unsteady pressures of rectangular convergent-divergent (2D-CD) nozzles with a fixed throat area. Straight divergent flaps were used in these nozzles. The area ratio (i.e., exit area/throat area) was varied by altering the flap divergence angle. Static and unsteady pressure data were acquired simultaneously along the centerline and at various transverse locations on one of the nozzle flaps. Tests were conducted for each configuration over a range of nozzle pressure ratios, including over-expansion conditions which generated shocks inside the nozzles. Data from these tests are utilized in developing empirical correlations between the nozzle interior wall unsteady pressure and the mean flow parameters for different flow regimes. Using these empirical correlations, both overall and spectral unsteady pressure levels for attached subsonic/supersonic turbulent boundary layers, as well as, separated turbulent boundary layers including shock/boundary-layer interactions can be predicted.

DGLR/AIAA 14th Aeroacoustics Conference, 1992

Conference Paper

englisch

21,0 x 29,7 cm, 9 Seiten

DGLR-Bericht, 1992, 1992-03, DGLR/AIAA 14th Aeroacoustics Conference - Proceedings; S.873-881; 1992; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroacoustics

Bibliothek

1992