Extension of PCBoom to Over-The-Top Booms, Ellipsoidal Earch, and Full 3-D Ray Tracing

Plotkin, Kenneth J.; Haering, Edward A.; Dryden, Nasa

doi:10.2514/6.2007-3677

Cited by 6 publications

(2 citation statements)

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“…5) uses the total A e from CFD propagated using sBOOM. The highest fidelity option uses the mid field pressure distribution from Cart3D or USM3D and propagates the signature using either PCBOOM 51 or sBOOM. The integrated analysis process uses the resulting signature from each code to calculate a perceived loudness based on the method of Stevens Mark VII 52 and the subjective loudness tests of Shepherd and Sullivan 53 .…”

Section: Sonic Boom Analysis Assemblymentioning

confidence: 99%

Integration of Multifidelity Multidisciplinary Computer Codes for Design and Analysis of Supersonic Aircraft

Geiselhart

Ozoroski

Fenbert

et al. 2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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This paper documents the development of a conceptual level integrated process for design and analysis of efficient and environmentally acceptable supersonic aircraft. To overcome the technical challenges to achieve this goal, a conceptual design capability which provides users with the ability to examine the integrated solution between all disciplines and facilitates the application of multidiscipline design, analysis, and optimization on a scale greater than previously achieved, is needed. The described capability is both an interactive design environment as well as a high powered optimization system with a unique blend of low, mixed and high-fidelity engineering tools combined together in the software integration framework, ModelCenter. The various modules are described and capabilities of the system are demonstrated. The current limitations and proposed future enhancements are also discussed. = equivalent area C L = lift coefficient dp/p = (the calculated pressure -the ambient pressure)/(the ambient pressure) EXTR = extraction ratio FPR = fan pressure ratio L/D = lift to drag ratio nmi = nautical miles OPR = overall pressure ratio OML = outer mold line SFC = specific fuel consumption T 3 = compressor exit temperature, °R T 4 = combustor exit temperature, °R TTR = throttle ratio V app = approach velocity, kts V jet = jet velocity, ft/s

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Section: Sonic Boom Analysis Assemblymentioning

confidence: 99%

Integration of Multifidelity Multidisciplinary Computer Codes for Design and Analysis of Supersonic Aircraft

Geiselhart

Ozoroski

Fenbert

et al. 2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

View full text Add to dashboard Cite

show abstract

“…Plotkin, Page, and Haering laid down a ray tracing methodology applicable to an ellipsoidal Earth [11] that builds on Schulten's equations for sound propagation in a Cartesian coordinate system [12] and Sofair's method for converting Cartesian to Geodetic coordinates and vice versa [13,14].…”

Section: Theory and Modeling Of Sonic Boom Propagationmentioning

confidence: 99%