No AccessEffect of Nozzle Geometry on Turbofan Shock Cell Noise at CruiseDean LongDean LongAero Systems EngineeringSearch for more papers by this authorSession: AA-9: Jet Noise ReductionPublished Online:21 Jun 2012https://doi.org/10.2514/6.2005-998SectionsRead Now ToolsAdd to favoritesDownload citationTrack citations ShareShare onFacebookTwitterLinked InRedditEmail About Previous chapter Next chapter FiguresReferencesRelatedDetailsSee PDF for referencesCited byMeasurements in the annular shear layer of high subsonic and under-expanded round jets15 December 2015 | Experiments in Fluids, Vol. 57, No. 1Broadband shock-cell noise from dual stream jetsJournal of Sound and Vibration, Vol. 324, No. 3-5Understanding and Reduction of Cruise Jet Noise at Model and Full ScaleJerome Huber, Kevin Britchford, Estelle Laurendeau, Vincent Fleury, Jean Bulté, Amadou Sylla and Dean Long4 November 2012Computation of Shock Cell Structure of Dual-Stream Jets for Noise Prediction Christopher K. W. Tam , Nikolai N. Pastouchenko and K. Viswanathan 2 May 2012 | AIAA Journal, Vol. 46, No. 11Forward Flight Effects on Chevron Noise ReductionEric Nesbitt and Russell Young4 November 2012Computation of Shock Cell Structure of Dual Stream Jets for Noise PredictionChristopher Tam, Nikolai Pastouchenko and Krishna Viswanathan19 June 2012 What's Popular 43rd AIAA Aerospace Sciences Meeting and Exhibit 10 January 2005 - 13 January 2005Reno, Nevadahttps://doi.org/10.2514/6.2005-998 Crossmark TopicsAerodynamicsAerospace SciencesAirbreathing Jet EngineAircraft EnginesBoundary LayersComputational Fluid DynamicsFlow RegimesFluid DynamicsNozzlesNumerical AnalysisPropulsion and PowerVortex DynamicsWind Tunnels KeywordsChevron NozzlesTurbofan EnginesBoundary Layer FluctuationsTransonic Wind TunnelAirframesNumerical IntegrationSpectral DensityTakeoff and LandingFreestream Mach NumberQuiet Flow FacilityDigital Topics Aerospace Systems, Operations and Life Cycle