Fidelity One level noise calculations for the airframe components.
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| def | SUAVE.Methods.Noise.Fidelity_One.Airframe.noise_airframe_Fink.noise_airframe_Fink (segment, analyses, config, settings, ioprint=0, filename=0) |
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| def | SUAVE.Methods.Noise.Fidelity_One.Airframe.noise_clean_wing.noise_clean_wing (S, b, ND, IsHorz, velocity, viscosity, M, phi, theta, distance, frequency) |
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| def | SUAVE.Methods.Noise.Fidelity_One.Airframe.noise_landing_gear.noise_landing_gear (D, H, wheels, M, velocity, phi, theta, distance, frequency) |
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| def | SUAVE.Methods.Noise.Fidelity_One.Airframe.noise_leading_edge_slat.noise_leading_edge_slat (SPL_wing, Sw, bw, velocity, viscosity, M, phi, theta, distance, frequency) |
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| def | SUAVE.Methods.Noise.Fidelity_One.Airframe.noise_trailing_edge_flap.noise_trailing_edge_flap (Sf, cf, deltaf, slots, velocity, M, phi, theta, distance, frequency) |
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Fidelity One level noise calculations for the airframe components.
◆ noise_airframe_Fink()
| def SUAVE.Methods.Noise.Fidelity_One.Airframe.noise_airframe_Fink.noise_airframe_Fink |
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segment, |
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analyses, |
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config, |
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settings, |
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ioprint = 0, |
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filename = 0 |
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This computes the noise from different sources of the airframe for a given vehicle for a constant altitude flight.
Assumptions:
Correlation based
Source:
Fink, Martin R. Airframe noise prediction method. No. UTRC/R77-912607-11. UNITED
TECHNOLOGIES RESEARCH CENTER EAST HARTFORD CT, 1977.
Inputs:
vehicle - SUAVE type vehicle
includes these fields:
S - Wing Area
bw - Wing Span
Sht - Horizontal tail area
bht - Horizontal tail span
Svt - Vertical tail area
bvt - Vertical tail span
deltaf - Flap deflection
Sf - Flap area
cf - Flap chord
slots - Number of slots (Flap type)
Dp - Main landing gear tyre diameter
Hp - Main lading gear strut length
Dn - Nose landing gear tyre diameter
Hn - Nose landing gear strut length
wheels - Number of wheels
airport - SUAVE type airport data, with followig fields:
atmosphere - Airport atmosphere (SUAVE type)
altitude - Airport altitude
delta_isa - ISA Temperature deviation
noise segment - flight path data, containing:
distance_vector - distance from the source location to observer
angle - polar angle from the source to the observer
phi - azimuthal angle from the source to the observer
Outputs: One Third Octave Band SPL [dB]
SPL_wing - Sound Pressure Level of the clean wing
SPLht - Sound Pressure Level of the horizontal tail
SPLvt - Sound Pressure Level of the vertical tail
SPL_flap - Sound Pressure Level of the flaps trailing edge
SPL_slat - Sound Pressure Level of the slat leading edge
SPL_main_landing_gear - Sound Pressure Level og the main landing gear
SPL_nose_landing_gear - Sound Pressure Level of the nose landing gear
Properties Used:
N/A
◆ noise_clean_wing()
| def SUAVE.Methods.Noise.Fidelity_One.Airframe.noise_clean_wing.noise_clean_wing |
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S, |
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b, |
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ND, |
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IsHorz, |
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velocity, |
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viscosity, |
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M, |
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phi, |
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theta, |
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distance, |
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frequency |
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This computes the 1/3 octave band sound pressure level and the overall sound pressure level from the clean wing,
for a wing with area S (sq.ft) and span b (ft). ND is a constant set to 0 for clean wings and set to 1 for propeller
airplanes, jet transports with numerous large trailing edge flap tracks, flaps extended, or slats extended. ISHORZ must be set to 1.
This function can be used for the horizontal tail by inserting the appropriate tail area and span. For a vertical tail, its appropriate
area and height are used and ISHORZ must be set to 0.
Assumptions:
Correlation based.
Source:
SAE Model
Inputs:
S - Wing Area [sq.ft]
b - Wing Span [ft]
ND - Costant from the method
IsHoriz - Costant from the method
deltaw - Wing Turbulent Boundary Layer thickness [ft]
velocity - Aircraft speed [kts]
viscosity - Dynamic viscosity
M - Mach number
phi - Azimuthal angle [rad]
theta - Polar angle [rad]
distance - Distance from airplane to observer, evaluated at retarded time [ft]
frequency - Frequency array [Hz]
Outputs: One Third Octave Band SPL [dB]
SPL - Sound Pressure Level of the clean wing [dB]
OASPL - Overall Sound Pressure Level of the clean wing [dB]
Properties Used:
None
◆ noise_landing_gear()
| def SUAVE.Methods.Noise.Fidelity_One.Airframe.noise_landing_gear.noise_landing_gear |
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D, |
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H, |
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wheels, |
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M, |
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velocity, |
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phi, |
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theta, |
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distance, |
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frequency |
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) |
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This calculates the Landing gear 1/3 octave band sound pressure level and overall sound pressure level
for a tyre diameter D, a strut length H and WHEELS number of wheels per unit.
Assumptions:
Correlation based.
Source:
None
Inputs:
D - Landing gear tyre diameter [ft]
H - Lading gear strut length [ft]
wheels - Number of wheels per unit [-]
M - Mach number [-]
velocity - Aircraft speed [kts]
phi - Azimuthal angle [rad]
theta - Polar angle [rad]
distance - Distance from airplane to observer, evaluated at retarded time [ft]
frequemcy - Frequency array [Hz]
Outputs: One Third Octave Band SPL [dB]
SPL - Sound Pressure Level of the landing gear [dB]
OASPL - Overall Sound Pressure Level of the landing gear [dB]
Source:
SAE ARP 876D
Inputs:
Ce = wing chord length at the engine location - as figure 7.3 of the SAE ARP 876D [m]
Xe = fan exit location downstream of the leading edge (Xe<Ce) - as figure 7.3 of the SAE ARP 876D [m]
Ye = separation distance from the wing chord line to nozzle lip - as figure 7.3 of the SAE ARP 876D [m]
theta_s [rad]
Diameter_mixed [m]
Outputs:
INST_s [-]
Properties Used:
N/A
◆ noise_leading_edge_slat()
| def SUAVE.Methods.Noise.Fidelity_One.Airframe.noise_leading_edge_slat.noise_leading_edge_slat |
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SPL_wing, |
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Sw, |
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bw, |
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velocity, |
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viscosity, |
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M, |
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phi, |
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theta, |
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distance, |
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frequency |
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) |
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This calculates the noise from the slat leading edge as a 1/3 octave band sound pressure level.
Assumptions:
Correlation based.
Inputs:
SPL_wing - Sound Pressure Level of the clean wing [dB]
Sw - Wing Area [sq.ft]
bw - Wing Span [ft]
velocity - Aircraft speed [kts]
viscosity - Dynamic viscosity [kg m^-1s^-1]
M - Mach number [unitless]
phi - Azimuthal angle [rad]
theta - Polar angle [rad]
distance - Distance from airplane to observer, evaluated at retarded time [ft]
frequency - Frequency array [Hz]
Outputs: One Third Octave Band SPL [dB]
SPL - Sound Pressure Level of the slat leading edge [dB]
Properties Used:
None
◆ noise_trailing_edge_flap()
| def SUAVE.Methods.Noise.Fidelity_One.Airframe.noise_trailing_edge_flap.noise_trailing_edge_flap |
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Sf, |
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cf, |
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deltaf, |
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slots, |
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velocity, |
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M, |
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phi, |
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theta, |
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distance, |
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frequency |
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This calculates the noise from the flap trailing edge as a 1/3 octave band sound pressure level.
Assumptions:
Correlation based.
Inputs:
Sf - Flap area [sq.ft]
cf - Flap chord [ft]
deltaf - Flap deflection [rad]
slots - Number of slots (Flap type)
velocity - Aircraft speed [kts]
M - Mach number [Unitless]
phi - Azimuthal angle [rad]
theta - Polar angle [rad]
distance - Distance from airplane to observer, evaluated at retarded time [ft]
frequency - Frequency array [Hz]
Outputs: One Third Octave Band SPL [dB]
SPL
Properties Used:
N/A
1.8.15