Abstract
Experimental acoustic data are presented to illustrate, at model scale, the effect of varying the nozzle-wing installation on jet shock associated noise, statically and with airspeed. The variation in installations included nozzle only, nozzle under the wing (with and without flaps deflected), and nozzle over the wing (unattached flow). The nozzles used were a conical and a six-tube mixer nozzle with a cold-flow nozzle pressure ratio of 2.1. A 33-cm diameter free jet was used to simulate airspeed. With the nozzle only, shock-wave noise dominated the spectra in the forward quadrant, while jet-mixing noise dominated in the rearward quadrant. Similar trends were observed when a wing (flaps retracted) was included. Shock noise was attenuated with an over-the-wing configuration and increased with an under-the-wing configuration (due to reflection from the wing surface). With increasing flap deflection (under-the-wing) configuration, the jet-flap interaction noise exceeded the shock noise and became dominant in both quadrants. The free-jet results showed that airspeed had no effect on shock noise. The free-jet noise data were corrected for convective amplification to approximate flight and comparisons between the various configurations are made.
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