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00 Comparison 1-revolution sample 1/4-scale model 40-revolution average 7-Meter Tunnel 80 knots fig acoustic data Advanced blade advanced main rotor advanced rotor blades advanced rotor system advancing-blade-tip Mach number amplitude average from microphone axis presents blade design blade planform Comparison of pressure-time decrease dynes/cm Effect of rotor far-field microphones Figure 12 Figure A7 forward speed fraction free-stream velocity high-speed impulsive noise histories for microphone HSI noise HSI-noise pressure spike HSI-noise spike Hz f I I I I I lower frequencies main rotor system Narrow-band spectrum negative pressure pulse noise signature noise-spike OASPL curve overall sound pressure plots pressure-time histories revolution 65 75 rotor hub rotor revolution 65 rotor thrust sample from microphone sound pressure level spectrum for advanced spectrum for standard SRS data Standard blade standard rotor system system for microphone system on noise system were tested Tunnel background noise UH-1H helicopter model UH-lH upstream waveform