scholarly journals Influence of multitube mixer nozzle geometry on CTOL‐OTW jet noise shielding

1975 ◽  
Vol 57 (S1) ◽  
pp. S31-S32
Author(s):  
U. von Glahn ◽  
D. Groesbeck
Keyword(s):  
Jet Noise ◽  
Nozzle Geometry ◽  
Noise Shielding

Twin jet noise shielding for a supersonic cruise vehicle

1979 ◽  
Author(s):  
J. CLAUSS, JR. ◽  
B. WRIGHT ◽  
G. BOWIE
Keyword(s):  
Jet Noise ◽  
Noise Shielding

Analysis of nozzle geometry effect on supersonic jet noise using Schlieren

2016 ◽  
Vol 140 (4) ◽  
pp. 3043-3043
Author(s):  
Yuta Ozawa ◽  
Akira Oyama ◽  
Masayuki Anyoji ◽  
Akira Oyama ◽  
Hiroya Mamori ◽  
...  
Keyword(s):  
Supersonic Jet ◽  
Jet Noise ◽  
Nozzle Geometry ◽  
Geometry Effect ◽  
Supersonic Jet Noise

scholarly journals Jet Noise Shielding Provided by a Hybrid Wing Body Aircraft

2014 ◽  
Author(s):  
Michael J. Doty ◽  
Thomas F. Brooks ◽  
Casey L. Burley ◽  
Christopher J. Bahr ◽  
Dennis S. Pope
Keyword(s):  
Jet Noise ◽  
Noise Shielding

S0505-3-2 Noise Reduction Effect of Nozzle Geometry of an Aerodynamic Tab on Jet Noise from a Rectangular Plug Nozzle

2009 ◽  
Vol 2009.2 (0) ◽  
pp. 263-264
Author(s):  
Masayuki FUKUDA ◽  
Takayuki SANO ◽  
Mikiya ARAKI ◽  
Takayuki KOJIMA ◽  
Hideyuki TAGUCHI ◽  
...  
Keyword(s):  
Noise Reduction ◽  
Jet Noise ◽  
Nozzle Geometry ◽  
Plug Nozzle ◽  
Reduction Effect

scholarly journals Effects of Nozzle Geometry and Intermittent Injection of Aerodynamic Tab on Supersonic Jet Noise

2008 ◽  
Vol 56 (659) ◽  
pp. 590-595 ◽  
Author(s):  
Mikiya ARAKI ◽  
Takayuki SANO ◽  
Masayuki FUKUDA ◽  
Takayuki KOJIMA ◽  
Hideyuki TAGUCHI ◽  
...  
Keyword(s):  
Supersonic Jet ◽  
Jet Noise ◽  
Nozzle Geometry ◽  
Supersonic Jet Noise

scholarly journals Jet noise shielding provided by a hybrid wing body aircraft

2018 ◽  
Vol 17 (1-2) ◽  
pp. 135-158 ◽  
Author(s):  
Michael J Doty ◽  
Thomas F Brooks ◽  
Casey L Burley ◽  
Christopher J Bahr ◽  
Dennis S Pope
Keyword(s):  
High Frequency ◽  
Jet Noise ◽  
Low Noise ◽  
Shielding Effectiveness ◽  
Axisymmetric Nozzle ◽  
Jet Engine ◽  
Stage 4 ◽  
Noise Shielding ◽  
Noise Measurements ◽  
Chevron Nozzle

One approach toward achieving NASA's aggressive N+2 noise goal of 42 EPNdB cumulative margin below Stage 4 is through the use of novel vehicle configurations like the hybrid wing body. Jet noise measurements from a hybrid wing body acoustic test in the NASA Langley 14- by 22-Foot Subsonic Tunnel are described. Two dual-stream, heated Compact Jet Engine Simulator units are mounted underneath the inverted hybrid wing body model on a traversable support to permit measurement of varying levels of shielding provided by the fuselage. Both an axisymmetric and low noise chevron nozzle set are investigated in the context of shielding. The unshielded chevron nozzle set shows 1–2 dB of source noise reduction (relative to the unshielded axisymmetric nozzle set) with some penalties at higher frequencies. Shielding of the axisymmetric nozzles shows up to 6.5 dB of reduction at high frequency. The combination of shielding and low noise chevrons shows benefits beyond the expected additive benefits of the two, up to 10 dB, due to the effective migration of the jet source peak noise location upstream for increased shielding effectiveness. Jet noise source maps from phased array results processed with the deconvolution approach for the mapping of acoustic sources algorithm reinforce these observations.

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