def noise_leading_edge_slat(SPL_wing, Sw, bw, velocity, deltaw, viscosity, M,
phi, theta, distance, frequency):
""" SUAVE.Methods.Noise.Fidelity_One.noise_leading_edge_slat(SPL_wing,Sw,bw,velocity,deltaw,viscosity,phi,theta,distance,frequency):
Calculates the noise from the slat leading edge as a 1/3 octave band sound pressure level.
Inputs:
SPL_wing - Sound Pressure Level of the clean wing [dB]
Sw - Wing Area [sq.ft]
bw - Wing Span [ft]
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 slat leading edge [dB]
Assumptions:
Correlation based."""
#Process
SPLslat1 = SPL_wing + 3.0
SPLslat2 = noise_clean_wing(0.15 * Sw, bw, 1, 1, deltaw, velocity,
viscosity, M, phi, theta, distance, frequency)
peakfactor = 3 + max(SPL_wing) - max(SPLslat2)
SPLslat2 = SPLslat2 + peakfactor
SPL = 10. * np.log10(10.0**(0.1 * SPLslat1) + 10.0**(0.1 * SPLslat2))
return (SPL)
def noise_leading_edge_slat (SPL_wing,Sw,bw,velocity,deltaw,viscosity,M,phi,theta,distance,frequency):
""" SUAVE.Methods.Noise.Fidelity_One.noise_leading_edge_slat(SPL_wing,Sw,bw,velocity,deltaw,viscosity,phi,theta,distance,frequency):
Calculates the noise from the slat leading edge as a 1/3 octave band sound pressure level.
Inputs:
SPL_wing - Sound Pressure Level of the clean wing [dB]
Sw - Wing Area [sq.ft]
bw - Wing Span [ft]
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 slat leading edge [dB]
Assumptions:
Correlation based."""
#Process
SPLslat1 = SPL_wing+3.0
SPLslat2 = noise_clean_wing(0.15*Sw,bw,1,1,deltaw,velocity,viscosity,M,phi,theta,distance,frequency)
peakfactor = 3+max(SPL_wing)-max(SPLslat2)
SPLslat2 = SPLslat2+peakfactor
SPL = 10.*np.log10(10.0**(0.1*SPLslat1)+10.0**(0.1*SPLslat2))
return (SPL)
def noise_airframe_Fink(config, analyses, noise_segment,ioprint = 0, filename=0):
""" SUAVE.Methods.Noise.Fidelity_One.noise_fidelity_one(config, analyses, noise_segment):
Computes the noise from different sources of the airframe for a given vehicle for a constant altitude flight.
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
Assumptions:
Correlation based."""
# ==============================================
# Unpack
# ==============================================
wing = config.wings
Sw = wing.main_wing.areas.reference / (Units.ft)**2 #wing area, sq.ft
bw = wing.main_wing.spans.projected / Units.ft #wing span, ft
Sht = wing.horizontal_stabilizer.areas.reference / (Units.ft)**2 #horizontal tail area, sq.ft
bht = wing.horizontal_stabilizer.spans.projected / Units.ft #horizontal tail span, ft
Svt = wing.vertical_stabilizer.areas.reference / (Units.ft)**2 #vertical tail area, sq.ft
bvt = wing.vertical_stabilizer.spans.projected / Units.ft #vertical tail span, ft
deltaf = wing.main_wing.flaps.angle #flap delection, rad
Sf = wing.main_wing.flaps.area / (Units.ft)**2 #flap area, sq.ft
cf = wing.main_wing.flaps.chord_dimensional / Units.ft #flap chord, ft
Dp = config.landing_gear.main_tire_diameter / Units.ft #MLG tyre diameter, ft
Hp = config.landing_gear.nose_tire_diameter / Units.ft #MLG strut length, ft
Dn = config.landing_gear.main_strut_length / Units.ft #NLG tyre diameter, ft
Hn = config.landing_gear.nose_strut_length / Units.ft #NLG strut length, ft
gear = config.landing_gear.gear_condition #Gear up or gear down
nose_wheels = config.landing_gear.nose_wheels #Number of wheels
main_wheels = config.landing_gear.main_wheels #Number of wheels
main_units = config.landing_gear.main_units #Number of main units
velocity = np.float(noise_segment.conditions.freestream.velocity[0,0]) #aircraft velocity
altitude = noise_segment.conditions.freestream.altitude[:,0] #aircraft altitude
time = noise_segment.conditions.frames.inertial.time[:,0] #time discretization
noise_time = np.arange(0.,time[-1],.5)
altitude = np.interp(noise_time,time,altitude)
# determining flap slot number
if wing.main_wing.flaps.type == 'single_slotted':
slots = 1
elif wing.main_wing.flaps.type == 'double_slotted':
slots = 2
elif wing.main_wing.flaps.type == 'triple_slotted':
slots = 3
# Geometric information from the source to observer position
distance_vector = noise_segment.dist
angle = noise_segment.theta
phi = noise_segment.phi
distance_vector = np.interp(noise_time,time,distance_vector)
angle = np.interp(noise_time,time,angle)
phi = np.interp(noise_time,time,phi)
# Number of points on the discretize segment
nsteps=len(noise_time)
# Preparing matrix for noise calculation
sound_speed = np.zeros(nsteps)
density = np.zeros(nsteps)
viscosity = np.zeros(nsteps)
temperature = np.zeros(nsteps)
M = np.zeros(nsteps)
deltaw = np.zeros(nsteps)
# ==============================================
# Computing atmospheric conditions
# ==============================================
for id in range (0,nsteps):
atmo_data = analyses.atmosphere.compute_values(altitude[id])
#unpack
sound_speed[id] = np.float(atmo_data.speed_of_sound)
density[id] = np.float(atmo_data.density)
viscosity[id] = np.float(atmo_data.dynamic_viscosity*10.7639) #units converstion - m2 to ft2
temperature[id] = np.float(atmo_data.temperature)
#Mach number
M[id] = velocity/np.sqrt(1.4*287*temperature[id])
#Wing Turbulent Boundary Layer thickness, ft
deltaw[id] = 0.37*(Sw/bw)*((velocity/Units.ft)*Sw/(bw*viscosity[id]))**(-0.2)
#Units conversion - knots to ft/s
kt2fts = 1.6878098571
#Generate array with the One Third Octave Band Center Frequencies
frequency = np.array((50, 63, 80, 100, 125, 160, 200, 250, 315, 400, 500, 630, 800, 1000, 1250, 1600, \
2000, 2500, 3150, 4000, 5000, 6300, 8000, 10000))
# Velocity in fts
velocity_fst = velocity * Units.knot
#number of positions of the aircraft to calculate the noise
nrange = len(angle)
i=0
SPL_wing_history = np.zeros((nrange,24))
SPLht_history = np.zeros((nrange,24))
SPLvt_history = np.zeros((nrange,24))
SPL_flap_history = np.zeros((nrange,24))
SPL_slat_history = np.zeros((nrange,24))
SPL_main_landing_gear_history = np.zeros((nrange,24))
SPL_nose_landing_gear_history = np.zeros((nrange,24))
SPL_total_history = np.zeros((nrange,24))
#Noise history in dBA
SPLt_dBA_history = np.zeros((nrange,24))
SPLt_dBA_max = np.zeros(nrange)
#START LOOP FOR EACH POSITION OF AIRCRAFT
for i in range(0,nrange-1):
#Emission angle theta
theta = angle[i]
#Distance from airplane to observer, evaluated at retarded time
distance = distance_vector[i]
#Atmospheric attenuation
delta_atmo=atmospheric_attenuation(distance)
#Call each noise source model
SPL_wing = noise_clean_wing(Sw,bw,0,1,deltaw[i],velocity,viscosity[i],M[i],phi[i],theta,distance,frequency) - delta_atmo #Wing Noise
SPLht = noise_clean_wing(Sht,bht,0,1,deltaw[i],velocity,viscosity[i],M[i],phi[i],theta,distance,frequency) -delta_atmo #Horizontal Tail Noise
SPLvt = noise_clean_wing(Svt,bvt,0,0,deltaw[i],velocity,viscosity[i],M[i],phi[i],theta,distance,frequency) -delta_atmo #Vertical Tail Noise
SPL_slat = noise_leading_edge_slat(SPL_wing,Sw,bw,velocity,deltaw[i],viscosity[i],M[i],phi[i],theta,distance,frequency) -delta_atmo #Slat leading edge
if (deltaf==0):
SPL_flap = np.zeros(24)
else:
SPL_flap = noise_trailing_edge_flap(Sf,cf,deltaf,slots,velocity,M[i],phi[i],theta,distance,frequency) - delta_atmo #Trailing Edge Flaps Noise
if gear=='up': #0
SPL_main_landing_gear = np.zeros(24)
SPL_nose_landing_gear = np.zeros(24)
else:
SPL_main_landing_gear = noise_landing_gear(Dp,Hp,main_wheels,M[i],velocity,phi[i],theta,distance,frequency) - delta_atmo #Main Landing Gear Noise
SPL_nose_landing_gear = noise_landing_gear(Dn,Hn,nose_wheels,M[i],velocity,phi[i],theta,distance,frequency) - delta_atmo #Nose Landing Gear Noise
if main_units>1: #Incoherent summation of each main landing gear unit
SPL_main_landing_gear = SPL_main_landing_gear+3*(main_units-1)
#Total Airframe Noise
SPL_total = 10.*np.log10(10.0**(0.1*SPL_wing)+10.0**(0.1*SPLht)+10**(0.1*SPL_flap)+ \
10.0**(0.1*SPL_slat)+10.0**(0.1*SPL_main_landing_gear)+10.0**(0.1*SPL_nose_landing_gear))
SPL_total_history[i][:] = SPL_total[:]
SPL_wing_history[i][:] = SPL_wing[:]
SPLvt_history[i][:] = SPLvt[:]
SPLht_history[i][:] = SPLht[:]
SPL_flap_history[i][:] = SPL_flap[:]
SPL_slat_history[i][:] = SPL_slat[:]
SPL_nose_landing_gear_history[i][:] = SPL_nose_landing_gear[:]
SPL_main_landing_gear_history[i][:] = SPL_main_landing_gear[:]
#Calculation of dBA based on the sound pressure time history
SPLt_dBA = dbA_noise(SPL_total)
SPLt_dBA_history[i][:] = SPLt_dBA[:]
SPLt_dBA_max[i] = max(SPLt_dBA)
#Calculation of dBA based on the sound pressure time history
dbA_total = np.max(SPLt_dBA_history) #(Not used to certification point)
#Calculation of the Perceived Noise Level EPNL based on the sound time history
PNL_total = pnl_noise(SPL_total_history)
PNL_wing = pnl_noise(SPL_wing_history)
PNL_ht = pnl_noise(SPLht_history)
PNL_vt = pnl_noise(SPLvt_history)
PNL_nose_landing_gear = pnl_noise(SPL_nose_landing_gear_history)
PNL_main_landing_gear = pnl_noise(SPL_main_landing_gear_history)
PNL_slat = pnl_noise(SPL_slat_history)
PNL_flap = pnl_noise(SPL_flap_history)
#Calculation of the tones corrections on the SPL for each component and total
tone_correction_total = noise_tone_correction(SPL_total_history)
tone_correction_wing = noise_tone_correction(SPL_wing_history)
tone_correction_ht = noise_tone_correction(SPLht_history)
tone_correction_vt = noise_tone_correction(SPLvt_history)
tone_correction_flap = noise_tone_correction(SPL_flap_history)
tone_correction_slat = noise_tone_correction(SPL_slat_history)
tone_correction_nose_landing_gear = noise_tone_correction(SPL_nose_landing_gear_history)
tone_correction_main_landing_gear = noise_tone_correction(SPL_main_landing_gear_history)
#Calculation of the PLNT for each component and total
PNLT_total = PNL_total+tone_correction_total
PNLT_wing = PNL_wing+tone_correction_wing
PNLT_ht = PNL_ht+tone_correction_ht
PNLT_vt = PNL_vt+tone_correction_vt
PNLT_nose_landing_gear = PNL_nose_landing_gear+tone_correction_nose_landing_gear
PNLT_main_landing_gear = PNL_main_landing_gear+tone_correction_main_landing_gear
PNLT_slat = PNL_slat+tone_correction_slat
PNLT_flap = PNL_flap+tone_correction_flap
#Calculation of the EPNL for each component and total
EPNL_total = epnl_noise(PNLT_total)
EPNL_wing = epnl_noise(PNLT_wing)
EPNL_ht = epnl_noise(PNLT_ht)
EPNL_vt = epnl_noise(PNLT_vt)
EPNL_nose_landing_gear = epnl_noise(PNLT_nose_landing_gear)
EPNL_main_landing_gear = epnl_noise(PNLT_main_landing_gear)
EPNL_slat = epnl_noise(PNLT_slat)
EPNL_flap = epnl_noise(PNLT_flap)
#Calculation of the SENEL total
SENEL_total = senel_noise(SPLt_dBA_max)
if ioprint:
# write header of file
if not filename:
filename = ('Noise_' + str(config.tag) + '.dat')
fid = open(filename,'w') # Open output file
fid.write('Reference speed = ')
fid.write(str('%2.2f' % (velocity/Units.kts))+' kts')
fid.write('\n')
fid.write('PNLT history')
fid.write('\n')
fid.write('time altitude Mach Polar_angle Azim_angle distance wing ht vt flap slat nose main total dBA')
fid.write('\n')
for id in range (0,nsteps):
fid.write(str('%2.2f' % time[id])+' ')
fid.write(str('%2.2f' % altitude[id])+' ')
fid.write(str('%2.2f' % M[id])+' ')
fid.write(str('%2.2f' % (angle[id]*180/np.pi))+' ')
fid.write(str('%2.2f' % (phi[id]*180/np.pi))+' ')
fid.write(str('%2.2f' % distance_vector[id])+' ')
fid.write(str('%2.2f' % PNLT_wing[id])+' ')
fid.write(str('%2.2f' % PNLT_ht[id])+' ')
fid.write(str('%2.2f' % PNLT_vt[id])+' ')
fid.write(str('%2.2f' % PNLT_flap[id])+' ')
fid.write(str('%2.2f' % PNLT_slat[id])+' ')
fid.write(str('%2.2f' % PNLT_nose_landing_gear[id])+' ')
fid.write(str('%2.2f' % PNLT_main_landing_gear[id])+' ')
fid.write(str('%2.2f' % PNLT_total[id])+' ')
fid.write(str('%2.2f' % SPLt_dBA_max[id])+' ')
fid.write('\n')
fid.write('\n')
fid.write('PNLT max = ')
fid.write(str('%2.2f' % (np.max(PNLT_total)))+' dB')
fid.write('\n')
fid.write('dBA max = ')
fid.write(str('%2.2f' % (np.max(SPLt_dBA_max)))+' dBA')
fid.write('\n')
fid.write('\n')
fid.write('EPNdB')
fid.write('\n')
fid.write('wing ht vt flap slat nose main total')
fid.write('\n')
fid.write(str('%2.2f' % EPNL_wing)+' ')
fid.write(str('%2.2f' % EPNL_ht)+' ')
fid.write(str('%2.2f' % EPNL_vt)+' ')
fid.write(str('%2.2f' % EPNL_flap)+' ')
fid.write(str('%2.2f' % EPNL_slat)+' ')
fid.write(str('%2.2f' % EPNL_nose_landing_gear)+' ')
fid.write(str('%2.2f' % EPNL_main_landing_gear)+' ')
fid.write(str('%2.2f' % EPNL_total)+' ')
fid.write('\n')
fid.write('SENEL = ')
fid.write(str('%2.2f' % SENEL_total)+' ')
fid.close
filename1 = ('History_Noise_' + str(config.tag) + '.dat')
fid = open(filename1,'w') # Open output file
fid.write('Reference speed = ')
fid.write(str('%2.2f' % (velocity/Units.kts))+' kts')
fid.write('\n')
fid.write('Sound Pressure Level for the Total Aircraft Noise')
fid.write('\n')
for nid in range (0,nrange):
fid.write('Polar angle = ' + str('%2.2f' % (angle[nid]*(180/np.pi))) + ' degrees' + '\n')
fid.write('f total SPL(dB) total SPL(dBA)' + '\n')
for id in range(0,24):
fid.write(str((frequency[id])) + ' ')
fid.write(str('%3.2f' % SPL_total_history[nid][id]) + ' ')
fid.write(str('%3.2f' % SPLt_dBA_history[nid][id]))
fid.write('\n')
fid.write('SPLmax (dB) = ')
fid.write(str('%3.2f' % (np.max(SPL_total_history[nid][:])))+' dB' + '\n')
fid.write('SPLmax (dBA) = ')
fid.write(str('%3.2f' % (np.max(SPLt_dBA_history[nid][:])))+' dB')
fid.write('\n')
fid.close
return (EPNL_total,SPL_total_history,SENEL_total)
def noise_airframe_Fink(config, analyses, noise_segment,ioprint = 0, filename=0):
""" SUAVE.Methods.Noise.Fidelity_One.noise_fidelity_one(config, analyses, noise_segment):
Computes the noise from different sources of the airframe for a given vehicle for a constant altitude flight.
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
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
Assumptions:
Correlation based."""
# ==============================================
# Unpack
# ==============================================
wing = config.wings
Sw = wing.main_wing.areas.reference / (Units.ft)**2 #wing area, sq.ft
bw = wing.main_wing.spans.projected / Units.ft #wing span, ft
Sht = wing.horizontal_stabilizer.areas.reference / (Units.ft)**2 #horizontal tail area, sq.ft
bht = wing.horizontal_stabilizer.spans.projected / Units.ft #horizontal tail span, ft
Svt = wing.vertical_stabilizer.areas.reference / (Units.ft)**2 #vertical tail area, sq.ft
bvt = wing.vertical_stabilizer.spans.projected / Units.ft #vertical tail span, ft
deltaf = wing.main_wing.flaps.angle #flap delection, rad
Sf = wing.main_wing.flaps.area / (Units.ft)**2 #flap area, sq.ft
cf = wing.main_wing.flaps.chord_dimensional / Units.ft #flap chord, ft
Dp = config.landing_gear.main_tire_diameter / Units.ft #MLG tyre diameter, ft
Hp = config.landing_gear.nose_tire_diameter / Units.ft #MLG strut length, ft
Dn = config.landing_gear.main_strut_length / Units.ft #NLG tyre diameter, ft
Hn = config.landing_gear.nose_strut_length / Units.ft #NLG strut length, ft
gear = config.landing_gear.gear_condition #Gear up or gear down
nose_wheels = config.landing_gear.nose_wheels #Number of wheels
main_wheels = config.landing_gear.main_wheels #Number of wheels
main_units = config.landing_gear.main_units #Number of main units
velocity = np.float(noise_segment.conditions.freestream.velocity[0,0])
altitude = noise_segment.conditions.freestream.altitude[:,0]
time = noise_segment.conditions.frames.inertial.time[:,0]
noise_time = np.arange(0.,time[-1],.5)
altitude = np.interp(noise_time,time,altitude)
# determining flap slot number
if wing.main_wing.flaps.type == 'single_sloted':
slots = 1
elif wing.main_wing.flaps.type == 'double_sloted':
slots = 2
elif wing.main_wing.flaps.type == 'triple_sloted':
slots = 3
# Calls the function noise_geometric to calculate all the distance and emission angles
geometric = noise_geometric(noise_segment,analyses,config)
distance_vector = geometric[:][0]
angle = geometric[:][1]
phi = geometric[:][2]
distance_vector = np.interp(noise_time,time,distance_vector)
angle = np.interp(noise_time,time,angle)
phi = np.interp(noise_time,time,phi)
# Number of points on the discretize segment
nsteps=len(noise_time)
# Preparing matrix for noise calculation
sound_speed = np.zeros(nsteps)
density = np.zeros(nsteps)
viscosity = np.zeros(nsteps)
temperature = np.zeros(nsteps)
M = np.zeros(nsteps)
deltaw = np.zeros(nsteps)
# ==============================================
# Computing atmospheric conditions
# ==============================================
for id in range (0,nsteps):
atmo_data = analyses.atmosphere.compute_values(altitude[id])
#unpack
sound_speed[id] = np.float(atmo_data.speed_of_sound)
density[id] = np.float(atmo_data.density)
viscosity[id] = np.float(atmo_data.dynamic_viscosity*10.7639) #units converstion - m2 to ft2
temperature[id] = np.float(atmo_data.temperature)
#Mach number
M[id] = velocity/np.sqrt(1.4*287*temperature[id])
#Wing Turbulent Boundary Layer thickness, ft
deltaw[id] = 0.37*(Sw/bw)*((velocity/Units.ft)*Sw/(bw*viscosity[id]))**(-0.2)
#Units conversion - knots to ft/s
kt2fts = 1.6878098571
#Generate array with the One Third Octave Band Center Frequencies
frequency = np.array((50, 63, 80, 100, 125, 160, 200, 250, 315, 400, 500, 630, 800, 1000, 1250, 1600, \
2000, 2500, 3150, 4000, 5000, 6300, 8000, 10000))
# Velocity in fts
velocity_fst = velocity * Units.knot
#number of positions of the aircraft to calculate the noise
nrange = len(angle)
i=0
SPL_wing_history = np.zeros((nrange,24))
SPLht_history = np.zeros((nrange,24))
SPLvt_history = np.zeros((nrange,24))
SPL_flap_history = np.zeros((nrange,24))
SPL_slat_history = np.zeros((nrange,24))
SPL_main_landing_gear_history = np.zeros((nrange,24))
SPL_nose_landing_gear_history = np.zeros((nrange,24))
SPL_total_history = np.zeros((nrange,24))
#Noise history in dBA
SPLt_dBA_history = np.zeros((nrange,24))
#START LOOP FOR EACH POSITION OF AIRCRAFT
for i in range(0,nrange-1):
#Emission angle theta
theta = angle[i]
#Distance from airplane to observer, evaluated at retarded time
distance = distance_vector[i]
#Atmospheric attenuation
delta_atmo=atmospheric_attenuation(distance)
#Call each noise source model
SPL_wing = noise_clean_wing(Sw,bw,0,1,deltaw[i],velocity,viscosity[i],M[i],phi[i],theta,distance,frequency) - delta_atmo #Wing Noise
SPLht = noise_clean_wing(Sht,bht,0,1,deltaw[i],velocity,viscosity[i],M[i],phi[i],theta,distance,frequency) -delta_atmo #Horizontal Tail Noise
SPLvt = noise_clean_wing(Svt,bvt,0,0,deltaw[i],velocity,viscosity[i],M[i],phi[i],theta,distance,frequency) -delta_atmo #Vertical Tail Noise
SPL_slat = noise_leading_edge_slat(SPL_wing,Sw,bw,velocity,deltaw[i],viscosity[i],M[i],phi[i],theta,distance,frequency) -delta_atmo #Slat leading edge
if (deltaf==0):
SPL_flap = np.zeros(24)
else:
SPL_flap = noise_trailing_edge_flap(Sf,cf,deltaf,slots,velocity,M[i],phi[i],theta,distance,frequency) - delta_atmo #Trailing Edge Flaps Noise
if gear=='up': #0
SPL_main_landing_gear = np.zeros(24)
SPL_nose_landing_gear = np.zeros(24)
else:
SPL_main_landing_gear = noise_landing_gear(Dp,Hp,main_wheels,M[i],velocity,phi[i],theta,distance,frequency) - delta_atmo #Main Landing Gear Noise
SPL_nose_landing_gear = noise_landing_gear(Dn,Hn,nose_wheels,M[i],velocity,phi[i],theta,distance,frequency) - delta_atmo #Nose Landing Gear Noise
if main_units>1: #Incoherent summation of each main landing gear unit
SPL_main_landing_gear = SPL_main_landing_gear+3*(main_units-1)
#Total Airframe Noise
SPL_total = 10.*np.log10(10.0**(0.1*SPL_wing)+10.0**(0.1*SPLht)+10**(0.1*SPL_flap)+ \
10.0**(0.1*SPL_slat)+10.0**(0.1*SPL_main_landing_gear)+10.0**(0.1*SPL_nose_landing_gear)) - delta_atmo
#Included 02nd September 2015
SPLt_dBA = dbA_noise(SPL_total)
SPLt_dBA_history[i][:] = SPLt_dBA[:]
SPL_total_history[i][:] = SPL_total[:]
SPL_wing_history[i][:] = SPL_wing[:]
SPLvt_history[i][:] = SPLvt[:]
SPLht_history[i][:] = SPLht[:]
SPL_flap_history[i][:] = SPL_flap[:]
SPL_slat_history[i][:] = SPL_slat[:]
SPL_nose_landing_gear_history[i][:] = SPL_nose_landing_gear[:]
SPL_main_landing_gear_history[i][:] = SPL_main_landing_gear[:]
#Calculation of dBA based on the sound pressure time history
# dbA_total = dbA_noise(SPL_total_history) #(Not used to certification point)
#Calculation of the Perceived Noise Level EPNL based on the sound time history
PNL_total = pnl_noise(SPL_total_history)
PNL_wing = pnl_noise(SPL_wing_history)
PNL_ht = pnl_noise(SPLht_history)
PNL_vt = pnl_noise(SPLvt_history)
PNL_nose_landing_gear = pnl_noise(SPL_nose_landing_gear_history)
PNL_main_landing_gear = pnl_noise(SPL_main_landing_gear_history)
PNL_slat = pnl_noise(SPL_slat_history)
PNL_flap = pnl_noise(SPL_flap_history)
#Calculation of the tones corrections on the SPL for each component and total
tone_correction_total = noise_tone_correction(SPL_total_history)
tone_correction_wing = noise_tone_correction(SPL_wing_history)
tone_correction_ht = noise_tone_correction(SPLht_history)
tone_correction_vt = noise_tone_correction(SPLvt_history)
tone_correction_flap = noise_tone_correction(SPL_flap_history)
tone_correction_slat = noise_tone_correction(SPL_slat_history)
tone_correction_nose_landing_gear = noise_tone_correction(SPL_nose_landing_gear_history)
tone_correction_main_landing_gear = noise_tone_correction(SPL_main_landing_gear_history)
#Calculation of the PLNT for each component and total
PNLT_total = PNL_total+tone_correction_total
PNLT_wing = PNL_wing+tone_correction_wing
PNLT_ht = PNL_ht+tone_correction_ht
PNLT_vt = PNL_vt+tone_correction_vt
PNLT_nose_landing_gear = PNL_nose_landing_gear+tone_correction_nose_landing_gear
PNLT_main_landing_gear = PNL_main_landing_gear+tone_correction_main_landing_gear
PNLT_slat = PNL_slat+tone_correction_slat
PNLT_flap = PNL_flap+tone_correction_flap
#Calculation of the EPNL for each component and total
EPNL_total = epnl_noise(PNLT_total)
EPNL_wing = epnl_noise(PNLT_wing)
EPNL_ht = epnl_noise(PNLT_ht)
EPNL_vt = epnl_noise(PNLT_vt)
EPNL_nose_landing_gear = epnl_noise(PNLT_nose_landing_gear)
EPNL_main_landing_gear = epnl_noise(PNLT_main_landing_gear)
EPNL_slat = epnl_noise(PNLT_slat)
EPNL_flap = epnl_noise(PNLT_flap)
if ioprint:
# write header of file
if not filename:
filename = ('Noise_' + str(config.tag) + '.dat')
fid = open(filename,'w') # Open output file
fid.write('Reference speed = ')
fid.write(str('%2.2f' % (velocity/Units.kts))+' kts')
fid.write('\n')
fid.write('PNLT history')
fid.write('\n')
fid.write('time altitude Mach Polar angle Azim angle distance wing ht vt flap slat nose main total')
fid.write('\n')
for id in range (0,nsteps):
fid.write(str('%2.2f' % time[id])+' ')
fid.write(str('%2.2f' % altitude[id])+' ')
fid.write(str('%2.2f' % M[id])+' ')
fid.write(str('%2.2f' % (angle[id]*180/np.pi))+' ')
fid.write(str('%2.2f' % (phi[id]*180/np.pi))+' ')
fid.write(str('%2.2f' % distance_vector[id])+' ')
fid.write(str('%2.2f' % PNLT_wing[id])+' ')
fid.write(str('%2.2f' % PNLT_ht[id])+' ')
fid.write(str('%2.2f' % PNLT_vt[id])+' ')
fid.write(str('%2.2f' % PNLT_flap[id])+' ')
fid.write(str('%2.2f' % PNLT_slat[id])+' ')
fid.write(str('%2.2f' % PNLT_nose_landing_gear[id])+' ')
fid.write(str('%2.2f' % PNLT_main_landing_gear[id])+' ')
fid.write(str('%2.2f' % PNLT_total[id])+' ')
fid.write('\n')
fid.write('\n')
fid.write('PNLT max = ')
fid.write(str('%2.2f' % (np.max(PNLT_total)))+' dB')
fid.write('\n')
fid.write('\n')
fid.write('EPNdB')
fid.write('\n')
fid.write('wing ht vt flap slat nose main total')
fid.write('\n')
fid.write(str('%2.2f' % EPNL_wing)+' ')
fid.write(str('%2.2f' % EPNL_ht)+' ')
fid.write(str('%2.2f' % EPNL_vt)+' ')
fid.write(str('%2.2f' % EPNL_flap)+' ')
fid.write(str('%2.2f' % EPNL_slat)+' ')
fid.write(str('%2.2f' % EPNL_nose_landing_gear)+' ')
fid.write(str('%2.2f' % EPNL_main_landing_gear)+' ')
fid.write(str('%2.2f' % EPNL_total)+' ')
fid.close
filename1 = ('History_Noise_' + str(config.tag) + '.dat')
fid = open(filename1,'w') # Open output file
fid.write('Reference speed = ')
fid.write(str('%2.2f' % (velocity/Units.kts))+' kts')
fid.write('\n')
fid.write('Sound Pressure Level for the Total Aircraft Noise')
fid.write('\n')
for nid in range (0,nrange):
fid.write('Polar angle = ' + str('%2.2f' % (angle[nid]*(180/np.pi))) + ' degrees' + '\n')
fid.write('f total SPL(dB) total SPL(dBA)' + '\n')
for id in range(0,24):
fid.write(str((frequency[id])) + ' ')
fid.write(str('%3.2f' % SPL_total_history[nid][id]) + ' ')
fid.write(str('%3.2f' % SPLt_dBA_history[nid][id]))
fid.write('\n')
fid.write('SPLmax (dB) = ')
fid.write(str('%3.2f' % (np.max(SPL_total_history[nid][:])))+' dB' + '\n')
fid.write('SPLmax (dBA) = ')
fid.write(str('%3.2f' % (np.max(SPLt_dBA_history[nid][:])))+' dB')
fid.write('\n')
fid.close
return (EPNL_total,SPL_total_history)