Acoustic flight test of the Piper Lance

Jones, K. E.; United States. Department of Transportation. Federal Aviation Administration. Office of Environment and Energy

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Acoustic flight test of the Piper Lance

1986-12-01
By Jones, K. E.

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English

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Creators:

Jones, K. E.
Corporate Creators:

United States. Department of Transportation. Federal Aviation Administration. Office of Environment and Energy
Corporate Contributors:

John A. Volpe National Transportation Systems Center (U.S.). Acoustics Facility
Subject/TRT Terms:

[+]

Acoustic Measurement Aircraft Noise Airspeed Cavitation Noise Flight Tests Overflights Propeller Blades Propeller Noise Small Aircraft Takeoff
Publication/ Report Number:

DOT/FAA/EE-86/9
Resource Type:

Tech Report
Geographical Coverage:

United States
Corporate Publisher:

United States. Federal Aviation Administration. Office of Environment and Energy
Abstract:

Research is being conducted to refine current noise regulation of propeller-driven small airplanes. Studies are examining the prospect of a substituting a takeoff procedure of equal stringency for the level flyover certification test presently required. It was initially assumed that equivalency could be established between the takeoff and level flyover procedures via adjustment equations involving propeller helical-tip Mach number and noise propagation distance to account for differences in airspeed and altitude repsectively. However, as test results became available, it was found that the propeller helical-tip Mach number adjustment equation did not adequately account for the measured noise level differences between the takeoff and level flyover procedures. After applying the adjustment equations, the takeoff noise levels were 3 to 4 decibels higher than the level flyover noise levels. The effect is believed to result form unsteady propeller blade loading when the aircraft is in a pitch-up position during a takeoff/climbout as opposted to level flight. The test aircraft was a Piper Cherokee Lance (PA-32R-300) equipped with a two-blade constant speed propeller.

The objective required a series of flights ranging from level flyover to a takeoff/climbout performed Vx (speed for best angle climb). Noise level versus propeller inflow angle was addressed by a series-to-series variation of aircraft speed at constant power and RPM. Since airspeed is a component of the helical tip Mach number (Mb), and given the generally strong influence of M on noise levels, additional series of overflights were necessary to empirically relate M to the noise level actually produced by the Lance. The M issue was addressed through a series-to-series variation of propeller RPM at constant power and airspeed.
Format:

PDF
Collection(s):

Volpe Center
Main Document Checksum:

[+]

urn:sha256:2274ff9ca8d565f3caf3afdbdef1ad3366d4d9190540fff40933d82661013af4
Download URL:

https://rosap.ntl.bts.gov/view/dot/10024/dot_10024_DS1.pdf
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Acoustic flight test of the Piper Lance

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