Theoretical prediction of nonlinear propagation effects on noise signatures generated by subconic or supersonic propeller - or rotor-blade tips
Raymond L. Barger, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, Langley Research Center
National Aeronautics and Space Administration, Scientific and Technical Information Office, 1980 - Technology & Engineering - 16 pages
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abscissas according to equation amplitude and impulse angle better than linear cancellation effect computed examples indicate constant-speed blade tip correlates with experimental cylindrical diam domain analysis equal-area rule ref equation 9a equations for sound experimental results better F-function far-field Harmonic number helicopter instantaneous plane Langley Research Center large-amplitude leading expansion large-amplitude waves leading edge swept linear source theory linear theory linear-theory calculation Mach number multivalued NASA near-field signature nonlinear distortion nonlinear effects nonlinear propagation equations nonlinear theory correlates nonlinear theory predicts occur at supersonic osculating plane Performing Organization plane of tip predicts a cancellation pressure signature propeller or rotor ray-tube area relative overpressure ROTOR-BLADE TIPS Security Classif shape function shock waves significant reduction Spectrum for figure spherical SR-2 blade subsonic tip supersonic speeds supersonic tip swept tips term in equation theory for large-amplitude tip are presented tip is treated tip motion tip noise trajectory wave with large-amplitude