The influence of temperature on shock-free supersonic jet noise

Parametric Testing of Chevrons on Single Flow Hot Jets

“…For consistency with the growing NASA jet noise database, data were acquired on a subset of flow conditions defined by Tanna 4 for hot jets. For brevity, only two conditions, setpoints 7 and 46, approximately M ∞ = U j /c j = 0.9 at static temperature ratio T s /T ∞ = 0.86 and 2.7 respectively are presented here.…”

Simulation of Flow Control with Microjets for Subsonic Jet Noise Reduction

“…The effect of temperature on jet noise has been widely investigated experimentally (Tanna, 1977;Tanna et al, 1975;Viswanathan, 2004). It has been observed that, for a fixed acoustic Mach number M a = U j /c 0 , where c 0 is the sound velocity at ambient temperature, the radiated noise directly depends on the jet temperature.…”

Toward Active Control of Noise from Hot Supersonic Jets

“…These have comprised a plethora of conditions including temperature effects, perfectly and imperfectly expanded flows, circular, elliptical and faceted geometries, as well as multi-stream nozzle assemblies. Restricting one's attention to shock-free, unheated supersonic jet flows, the more relevant stacks of literature reduce to the laboratory-scale jet studies of McLaughlin et al (1975), Tanna & Dean (1975), the full-scale flight tests of Morfey & Howell (1981) or the numerical studies of Howell & Morfey (1987), Morris (1977) and Seiner et al (1994). The aforementioned work comprised spectral analysis of the far-field acoustic waveform produced by jets with supersonic exit speeds based on the gas dynamic Mach number (Mj = Uj/aj > 1).…”