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High speed turboprop aeroacoustic study (counterrotation) Volume 1, Model development
U.S. Government
Paperback. Books LLC, Reference Series 2011-10-03.
ISBN 9781234357009
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Förlagets beskrivning
Original publisher: [Washington, DC] : National Aeronautics and Space Administration ; [Springfield, Va.? : National Technical Information Service, distributor, 1990] OCLC Number: (OCoLC)68906035 Subject: Propellers, Aerial -- Noise. Excerpt: ... List of Illustrations Page Figure 55. Four-Bladed SR-2, 745 fps Tip Speed, 100 fps Forward Flight Speed, Funda-mental Blade Passing Frequency Noise. Acoustic Data Source is Reference 15, Symbols are Measured Data, and Full Line is Theoretical Prediction. Increase / Decrease of Noise Due to 9 * Angle-of-Attack ( Relative to Zero Angle--of-Attack ) versus 0, ¢ = 90 *. 76 56. Four-Bladed SR-2, 745 fps Tip Speed, 100 fps Forward Flight Speed, Funda-mental Blade Passing Frequency Noise. Acoustic Data Source is Reference 15, Symbols are Measured Data, and Full Line is Theoretical Prediction. Increase / Decrease of Noise Due to 9 * Angle--of-Attack ( Relative to Zero Angle-of-Attack ) versus 0, ¢ = 270 °. 77 57. Four-Bladed SR-2, 745 f-ps Tip Speed, 100 fps Forward Flight Speed, Funda-mental Blade Passing Frequency Noise. Acoustic Data Source is Reference 15, Symbols are Measured Data, and Full Line is Theoretical Prediction. Increase / Decrease of Noise Due to 9 * Angle.of-Attack ( Relative to Zero Angle-of-Attack ) versus 0, 0 = 90 *. 77 11 x 9 Bladed 2-Foot-Diameter CRP; 75 % Radius Pitch Angles 41.1 " / 39.4 "; 58. rpm 7614 / 7674; Axial Flow Mach Number 0.2; 16 " Angle-of-Attack; Symbols are Measured Data and Solid Line is Prediction; 104 " 100 °; 0measured--and 0predicted--Front Rotor BPF; Data Source is Reference 16; Increase / Decrease of Noise Due to Angle--of-Attack. 78 11 x 9 Bladed 2-Foot-Diameter CRP; 75 % Radius Pitch Angles 41.1 ° / 39.4 °; rpm 59. 7614 / 7674; Axial Flow Mach Number 0.2; 16 ° Angle-of-Attack; Symbols are 0measured = 0predicted = Measured Data and Solid Line is Prediction; 104 ° and 110 ° Front Rotor BPF; Data Source is Reference 16; Increase / Decrease of Noise Due to Angle-of-Attack. 78 11 x
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High speed turboprop aeroacoustic study
Bokrecensioner » High speed turboprop aeroacoustic study (counterrotation) Volume 1, Model development
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