def _alt2ROC(prop, alt):
"""
calculate ROC for an altitude
"""
temp = SA.isa2temp(isa_dev, alt)
calc_pwr = alt2pwr(alt, rpm = rpm, MP_max = MP_max, temp = temp) * pwr_factor
cas = alt2roc_speed(alt, climb_speed = climb_speed)
eas = A.cas2eas(cas, alt)
ROC = roc(prop, alt, eas, weight, calc_pwr, rpm, rv = rv, \
wing_area = wing_area)
return ROC
def _alt2ROC(prop, alt):
"""
calculate ROC for an altitude
"""
temp = SA.isa2temp(isa_dev, alt)
calc_pwr = alt2pwr(alt, rpm=rpm, MP_max=MP_max, temp=temp) * pwr_factor
cas = alt2roc_speed(alt, climb_speed=climb_speed)
eas = A.cas2eas(cas, alt)
ROC = roc(prop, alt, eas, weight, calc_pwr, rpm, rv = rv, \
wing_area = wing_area)
return ROC
def test_03(self):
Value = SA.isa2temp(10, 10000, temp_units='K', alt_units='m')
Truth = 233.15
self.assertTrue(RE(Value, Truth) <= 1e-5)
def test_02(self):
Value = SA.isa2temp(-10, 10000, temp_units='F')
Truth = 13.3384
self.assertTrue(RE(Value, Truth) <= 1e-5)
def test_01(self):
Value = SA.isa2temp(25, 0)
Truth = 40
self.assertTrue(RE(Value, Truth) <= 1e-5)
def test_03(self):
Value = SA.isa2temp(10, 10000, temp_units='K', alt_units='m')
Truth = 233.15
self.failUnless(RE(Value, Truth) <= 1e-5)
def test_02(self):
Value = SA.isa2temp(-10, 10000, temp_units='F')
Truth = 13.3384
self.failUnless(RE(Value, Truth) <= 1e-5)
def test_01(self):
Value = SA.isa2temp(25, 0)
Truth = 40
self.failUnless(RE(Value, Truth) <= 1e-5)
def descent_data(prop, weight=1600., alt_max=20000., fuel_units='USG', \
alt_interval=500., isa_dev=0, temp_units='C', rv='8', wing_area=110., \
tas=180., ROD=-500., angle='', speed_units='kt', rpm=2100., sfc=0.45, output='raw'):
"""
Returns a table of descent performance vs altitude.
The items in each row of the table are altitude, time, fuel burned and distance.
Time is in units of minutes, rounded to the nearest half minute.
Fuel units are selectable, with a default of USG.
Distances are in nm.
The output may be specified as raw, latex (a LaTeX table for the POH), or array.
tas is the TAS in descent (overridden by the angle, if the angle is provided).
angle is the flight path angle in degrees.
"""
tas_fts = U.speed_conv(tas, speed_units, 'ft/s')
if angle:
ROD = tas_fts * 60 * M.sin(angle * M.pi / 180)
rod_fts = ROD / 60
tas = U.speed_conv(tas, speed_units, 'kt')
alt = alt_max + alt_interval
temp = SA.isa2temp(isa_dev, alt, temp_units=temp_units)
time = 0
fuel_used = 0
dist = 0
if output == 'raw':
print S.center('Altitude', 10),
print S.center('ROD', 10),
print S.center('Time', 10),
print S.center('Fuel Used', 10),
print S.center('Dist', 10),
print S.center('Speed', 10)
print S.center('(ft)', 10),
print S.center('(ft/mn)', 10),
print S.center('(mn)', 10),
f_units = '(' + fuel_units + ')'
print S.center(f_units, 10),
print S.center('(nm)', 10),
print S.center('(KCAS)', 10)
# # data for max altitude
# print S.rjust(locale.format('%.0f', alt_max, True), 7),
# print S.rjust(locale.format('%.0f', round(ROD / 10.) * 10, True), 10),
# print S.rjust('%.1f' % (0), 10),
# print S.rjust('%.1f' % (fuel_used), 10),
# print S.rjust('%.1f' % (dist), 10),
# print S.rjust('%3d' % (A.tas2cas(tas, alt_max, temp, temp_units=temp_units)), 10)
# elif output == 'latex':
# # temp = 15 + isa_dev
# MSL_line = []
# MSL_line.append(str(locale.format('%.0f', weight, True)))
# MSL_line.append('0')
# MSL_line.append(str(locale.format('%.0f', temp)))
# MSL_line.append(str(locale.format('%.0f', A.tas2cas(tas, alt, temp, temp_units=temp_units))))
# MSL_line.append(str(locale.format('%.0f', round(ROD / 10.) * 10, True)))
# MSL_line.append('0')
# MSL_line.append(str(fuel_used))
# MSL_line.append(str(dist))
#
# print '&'.join(MSL_line) + '\\\\'
# print '\\hline'
# elif output == 'array':
# # no header rows, but make blank array
# array = [[alt_max,0,0,0]]
alts = []
RODs = []
times_temp = []
CASs = []
dists_temp = []
fuel_useds_temp = []
temps = []
calc_alt = alt_max - alt_interval / 2.
while alt > 0:
temp = SA.isa2temp(isa_dev, alt, temp_units = temp_units)
eas = A.tas2eas(tas, alt)
drag = FT.eas2drag(eas, weight)
pwr_level_flt = tas_fts * drag / 550
thrust_power = pwr_level_flt + FT.Pexcess_vs_roc(weight, ROD)
prop_eff = PM.prop_eff(prop, thrust_power, rpm, tas, alt, temp, temp_units=temp_units)
calc_pwr = thrust_power / prop_eff
#fuel_flow = IO.pwr2ff(calc_pwr, rpm, ff_units = 'lb/hr')
fuel_flow = calc_pwr * sfc
# print "Level flt pwr = %.1f, thrust power = %.1f, prop eff = %.3f, fuel flow = %.3f" % (pwr_level_flt, thrust_power, prop_eff, fuel_flow)
slice_time = alt_interval / rod_fts * -1.
slice_dist = tas_fts * slice_time
slice_fuel = fuel_flow * slice_time / 3600
fuel_used += slice_fuel
fuel_out = (U.avgas_conv(fuel_used, from_units = 'lb', \
to_units = fuel_units))
weight -= slice_fuel
alt -= alt_interval
cas_out = A.tas2cas(tas, alt, temp, temp_units=temp_units)
temp_out = SA.isa2temp(isa_dev, alt)
time += slice_time / 60.
dist += slice_dist / 6076.115
alts.append(alt)
CASs.append(cas_out)
RODs.append(ROD)
times_temp.append(time)
fuel_useds_temp.append(fuel_out)
dists_temp.append(dist)
temps.append(temp_out)
calc_alt += alt_interval
alts.reverse()
CASs.reverse()
RODs.reverse()
temps.reverse()
times = []
fuel_useds = []
dists = []
for n, time in enumerate(times_temp):
times.append(times_temp[-1] - time)
fuel_useds.append(fuel_useds_temp[-1] - fuel_useds_temp[n])
dists.append(dists_temp[-1] - dists_temp[n])
times.reverse()
fuel_useds.reverse()
dists.reverse()
if output == 'raw':
for n, alt in enumerate(alts):
print S.rjust(locale.format('%.0f', alt, True), 7),
# calculate ROC at the displayed altitude
print S.rjust(locale.format('%.0f', RODs[n], True), 10),
print S.rjust('%.1f' % (times[n]), 10),
print S.rjust('%.1f' % (fuel_useds[n]), 10),
print S.rjust('%.1f' % (dists[n]), 10),
print S.rjust('%3d' % (int(CASs[n])), 10)
elif output == 'latex':
for n, alt in enumerate(alts):
line = []
line.append(str(locale.format('%.0f', alt, True)))
line.append(str(locale.format('%.0f', round(temps[n]))))
line.append(str(locale.format('%.0f', CASs[n])))
line.append(str(locale.format('%.0f', round(RODs[n] / 10.) * 10, True)))
line.append(str(locale.format('%.0f', times[n])))
line.append(str(locale.format('%.1f', fuel_useds[n])))
line.append(str(locale.format('%.0f', dists[n])))
print '&' + '&'.join(line) + '\\\\'
print '\\hline'
elif output == 'array':
array = []
for n, alt in enumerate(alts):
array.append([alt, times[n], fuel_useds[n], dists[n]])
return array
def climb_data(prop, weight = 1800., alt_max = 20000., TO_fuel = 0, TO_dist = 0, \
fuel_units = 'USG', alt_interval = 500., isa_dev = 0, temp_units = 'C', \
rv = '8', wing_area = 110., pwr = 'max', pwr_factor=1.0, \
climb_speed = 'max', output = 'raw'):
"""
Returns a table of climb performance vs altitude.
The items in each row of the table are altitude, time, fuel burned and distance.
Time is in units of minutes, rounded to the nearest half minute.
Fuel units are selectable, with a default of USG.
Distances are in nm.
The output may be specified as raw, latex (a LaTeX table for the POH), or array.
pwr may be 'max', 'cc' (cruise climb = 2500 rpm and 25") or 2500 (2500 rpm and full throttle)
climb_speed may be 'max' (Vy), 'cc' (120 kt to 10,000 ft, then reducing by 4 kt/1000 ft) or
'norm' (100 kt to 10,000 ft, then reducing by 2 kt/1000 ft)
Note: compared cruise range for all climb speed and power. The predicted results are all
within 1.5 nm of range. Thus there is no advantage to using anything but Vy and max
power.
"""
def _alt2ROC(prop, alt):
"""
calculate ROC for an altitude
"""
temp = SA.isa2temp(isa_dev, alt)
calc_pwr = alt2pwr(alt, rpm = rpm, MP_max = MP_max, temp = temp) * pwr_factor
cas = alt2roc_speed(alt, climb_speed = climb_speed)
eas = A.cas2eas(cas, alt)
ROC = roc(prop, alt, eas, weight, calc_pwr, rpm, rv = rv, \
wing_area = wing_area)
return ROC
alt = 0
time = 0
fuel_used = U.avgas_conv(TO_fuel, from_units = fuel_units, to_units = 'lb')
weight = weight - fuel_used
dist = TO_dist
if pwr == 'max':
# rpm = 2700
rpm = 2650
MP_max = 30
elif pwr == 'cc':
rpm = 2500
MP_max = 25
elif pwr == 2500:
rpm = 2500
MP_max = 30
else:
raise ValueError, "pwr must be one of 'max', 'cc', or 2500"
if output == 'raw':
print S.center('Altitude', 10),
print S.center('ROC', 10),
print S.center('Time', 10),
print S.center('Fuel Used', 10),
print S.center('Dist', 10),
print S.center('Speed', 10)
print S.center('(ft)', 10),
print S.center('(ft/mn)', 10),
print S.center('(mn)', 10),
f_units = '(' + fuel_units + ')'
print S.center(f_units, 10),
print S.center('(nm)', 10),
print S.center('(KCAS)', 10)
# data for MSL
print S.rjust(locale.format('%.0f', 0, True), 7),
# calculate ROC at MSL
print S.rjust(locale.format('%.0f', round(_alt2ROC(prop, 0) / 10.) * 10, \
True), 10),
print S.rjust('%.1f' % (0), 10),
print S.rjust('%.1f' % (TO_fuel), 10),
print S.rjust('%.1f' % (TO_dist), 10),
print S.rjust('%3d' % (alt2roc_speed(0, climb_speed = climb_speed)), 10)
elif output == 'latex':
temp = 15 + isa_dev
MSL_line = []
MSL_line.append(str(locale.format('%.0f', weight, True)))
MSL_line.append('0')
MSL_line.append(str(locale.format('%.0f', temp)))
MSL_line.append(str(locale.format('%.0f', alt2roc_speed(0, \
climb_speed = climb_speed))))
MSL_line.append(str(locale.format('%.0f', round(_alt2ROC(prop, 0) / 10.)\
* 10, True)))
MSL_line.append('0')
MSL_line.append(str(TO_fuel))
MSL_line.append(str(TO_dist))
print '&'.join(MSL_line) + '\\\\'
print '\\hline'
elif output == 'array':
# no header rows, but make blank array
array = [[0,0,TO_fuel,0]]
calc_alt = alt_interval / 2.
while calc_alt < alt_max:
temp = SA.isa2temp(isa_dev, calc_alt)
pwr = alt2pwr(calc_alt, rpm = rpm, MP_max = MP_max, temp = temp)
calc_pwr = pwr * pwr_factor
cas = alt2roc_speed(calc_alt, climb_speed = climb_speed)
eas = A.cas2eas(cas, calc_alt)
tas = A.cas2tas(cas, calc_alt, temp = temp, temp_units = temp_units)
tas_fts = U.speed_conv(tas, from_units = 'kt', to_units = 'ft/s')
ROC = roc(prop, calc_alt, eas, weight, calc_pwr, rpm, rv = rv, \
wing_area = wing_area)
roc_fts = ROC / 60
fuel_flow = IO.pwr2ff(pwr, rpm, ff_units = 'lb/hr')
slice_time = alt_interval / roc_fts
slice_dist = tas_fts * slice_time
slice_fuel = fuel_flow * slice_time / 3600
fuel_used += slice_fuel
fuel_out = (U.avgas_conv(fuel_used, from_units = 'lb', \
to_units = fuel_units))
weight -= slice_fuel
alt += alt_interval
cas_out = alt2roc_speed(alt, climb_speed = climb_speed)
temp_out = SA.isa2temp(isa_dev, alt)
ROC = _alt2ROC(prop, alt)
time += slice_time / 60
dist += slice_dist / 6076.115
if output == 'raw':
print S.rjust(locale.format('%.0f', alt, True), 7),
# calculate ROC at the displayed altitude
print S.rjust(locale.format('%.0f', ROC, True), 10),
print S.rjust('%.1f' % (time), 10),
print S.rjust('%.1f' % (fuel_out), 10),
print S.rjust('%.1f' % (dist), 10),
print S.rjust('%3d' % (int(cas_out)), 10)
elif output == 'latex':
line = []
line.append(str(locale.format('%.0f', alt, True)))
line.append(str(locale.format('%.0f', round(temp_out))))
line.append(str(locale.format('%.0f', cas_out)))
line.append(str(locale.format('%.0f', round(ROC / 10.) * 10, True)))
line.append(str(locale.format('%.0f', time)))
line.append(str(locale.format('%.1f', fuel_out)))
line.append(str(locale.format('%.0f', dist)))
print '&' + '&'.join(line) + '\\\\'
print '\\hline'
elif output == 'array':
array.append([alt, time, fuel_out, dist])
calc_alt += alt_interval
if output == 'array':
return array
def descent_data(prop, weight=1600., alt_max=20000., fuel_units='USG', \
alt_interval=500., isa_dev=0, temp_units='C', rv='8', wing_area=110., \
tas=180., ROD=-500., angle='', speed_units='kt', rpm=2100., sfc=0.45, output='raw'):
"""
Returns a table of descent performance vs altitude.
The items in each row of the table are altitude, time, fuel burned and distance.
Time is in units of minutes, rounded to the nearest half minute.
Fuel units are selectable, with a default of USG.
Distances are in nm.
The output may be specified as raw, latex (a LaTeX table for the POH), or array.
tas is the TAS in descent (overridden by the angle, if the angle is provided).
angle is the flight path angle in degrees.
"""
tas_fts = U.speed_conv(tas, speed_units, 'ft/s')
if angle:
ROD = tas_fts * 60 * M.sin(angle * M.pi / 180)
rod_fts = ROD / 60
tas = U.speed_conv(tas, speed_units, 'kt')
alt = alt_max + alt_interval
temp = SA.isa2temp(isa_dev, alt, temp_units=temp_units)
time = 0
fuel_used = 0
dist = 0
if output == 'raw':
print(S.center('Altitude', 10), end=' ')
print(S.center('ROD', 10), end=' ')
print(S.center('Time', 10), end=' ')
print(S.center('Fuel Used', 10), end=' ')
print(S.center('Dist', 10), end=' ')
print(S.center('Speed', 10))
print(S.center('(ft)', 10), end=' ')
print(S.center('(ft/mn)', 10), end=' ')
print(S.center('(mn)', 10), end=' ')
f_units = '(' + fuel_units + ')'
print(S.center(f_units, 10), end=' ')
print(S.center('(nm)', 10), end=' ')
print(S.center('(KCAS)', 10))
# # data for max altitude
# print S.rjust(locale.format('%.0f', alt_max, True), 7),
# print S.rjust(locale.format('%.0f', round(ROD / 10.) * 10, True), 10),
# print S.rjust('%.1f' % (0), 10),
# print S.rjust('%.1f' % (fuel_used), 10),
# print S.rjust('%.1f' % (dist), 10),
# print S.rjust('%3d' % (A.tas2cas(tas, alt_max, temp, temp_units=temp_units)), 10)
# elif output == 'latex':
# # temp = 15 + isa_dev
# MSL_line = []
# MSL_line.append(str(locale.format('%.0f', weight, True)))
# MSL_line.append('0')
# MSL_line.append(str(locale.format('%.0f', temp)))
# MSL_line.append(str(locale.format('%.0f', A.tas2cas(tas, alt, temp, temp_units=temp_units))))
# MSL_line.append(str(locale.format('%.0f', round(ROD / 10.) * 10, True)))
# MSL_line.append('0')
# MSL_line.append(str(fuel_used))
# MSL_line.append(str(dist))
#
# print '&'.join(MSL_line) + '\\\\'
# print '\\hline'
# elif output == 'array':
# # no header rows, but make blank array
# array = [[alt_max,0,0,0]]
alts = []
RODs = []
times_temp = []
CASs = []
dists_temp = []
fuel_useds_temp = []
temps = []
calc_alt = alt_max - alt_interval / 2.
while alt > 0:
temp = SA.isa2temp(isa_dev, alt, temp_units=temp_units)
eas = A.tas2eas(tas, alt)
drag = FT.eas2drag(eas, weight)
pwr_level_flt = tas_fts * drag / 550
thrust_power = pwr_level_flt + FT.Pexcess_vs_roc(weight, ROD)
prop_eff = PM.prop_eff(prop,
thrust_power,
rpm,
tas,
alt,
temp,
temp_units=temp_units)
calc_pwr = thrust_power / prop_eff
#fuel_flow = IO.pwr2ff(calc_pwr, rpm, ff_units = 'lb/hr')
fuel_flow = calc_pwr * sfc
# print "Level flt pwr = %.1f, thrust power = %.1f, prop eff = %.3f, fuel flow = %.3f" % (pwr_level_flt, thrust_power, prop_eff, fuel_flow)
slice_time = alt_interval / rod_fts * -1.
slice_dist = tas_fts * slice_time
slice_fuel = fuel_flow * slice_time / 3600
fuel_used += slice_fuel
fuel_out = (U.avgas_conv(fuel_used, from_units = 'lb', \
to_units = fuel_units))
weight -= slice_fuel
alt -= alt_interval
cas_out = A.tas2cas(tas, alt, temp, temp_units=temp_units)
temp_out = SA.isa2temp(isa_dev, alt)
time += slice_time / 60.
dist += slice_dist / 6076.115
alts.append(alt)
CASs.append(cas_out)
RODs.append(ROD)
times_temp.append(time)
fuel_useds_temp.append(fuel_out)
dists_temp.append(dist)
temps.append(temp_out)
calc_alt += alt_interval
alts.reverse()
CASs.reverse()
RODs.reverse()
temps.reverse()
times = []
fuel_useds = []
dists = []
for n, time in enumerate(times_temp):
times.append(times_temp[-1] - time)
fuel_useds.append(fuel_useds_temp[-1] - fuel_useds_temp[n])
dists.append(dists_temp[-1] - dists_temp[n])
times.reverse()
fuel_useds.reverse()
dists.reverse()
if output == 'raw':
for n, alt in enumerate(alts):
print(S.rjust(locale.format('%.0f', alt, True), 7), end=' ')
# calculate ROC at the displayed altitude
print(S.rjust(locale.format('%.0f', RODs[n], True), 10), end=' ')
print(S.rjust('%.1f' % (times[n]), 10), end=' ')
print(S.rjust('%.1f' % (fuel_useds[n]), 10), end=' ')
print(S.rjust('%.1f' % (dists[n]), 10), end=' ')
print(S.rjust('%3d' % (int(CASs[n])), 10))
elif output == 'latex':
for n, alt in enumerate(alts):
line = []
line.append(str(locale.format('%.0f', alt, True)))
line.append(str(locale.format('%.0f', round(temps[n]))))
line.append(str(locale.format('%.0f', CASs[n])))
line.append(
str(locale.format('%.0f',
round(RODs[n] / 10.) * 10, True)))
line.append(str(locale.format('%.0f', times[n])))
line.append(str(locale.format('%.1f', fuel_useds[n])))
line.append(str(locale.format('%.0f', dists[n])))
print('&' + '&'.join(line) + '\\\\')
print('\\hline')
elif output == 'array':
array = []
for n, alt in enumerate(alts):
array.append([alt, times[n], fuel_useds[n], dists[n]])
return array
def climb_data(prop, weight = 1800., alt_max = 20000., TO_fuel = 0, TO_dist = 0, \
fuel_units = 'USG', alt_interval = 500., isa_dev = 0, temp_units = 'C', \
rv = '8', wing_area = 110., pwr = 'max', pwr_factor=1.0, \
climb_speed = 'max', output = 'raw'):
"""
Returns a table of climb performance vs altitude.
The items in each row of the table are altitude, time, fuel burned and distance.
Time is in units of minutes, rounded to the nearest half minute.
Fuel units are selectable, with a default of USG.
Distances are in nm.
The output may be specified as raw, latex (a LaTeX table for the POH), or array.
pwr may be 'max', 'cc' (cruise climb = 2500 rpm and 25") or 2500 (2500 rpm and full throttle)
climb_speed may be 'max' (Vy), 'cc' (120 kt to 10,000 ft, then reducing by 4 kt/1000 ft) or
'norm' (100 kt to 10,000 ft, then reducing by 2 kt/1000 ft)
Note: compared cruise range for all climb speed and power. The predicted results are all
within 1.5 nm of range. Thus there is no advantage to using anything but Vy and max
power.
"""
def _alt2ROC(prop, alt):
"""
calculate ROC for an altitude
"""
temp = SA.isa2temp(isa_dev, alt)
calc_pwr = alt2pwr(alt, rpm=rpm, MP_max=MP_max, temp=temp) * pwr_factor
cas = alt2roc_speed(alt, climb_speed=climb_speed)
eas = A.cas2eas(cas, alt)
ROC = roc(prop, alt, eas, weight, calc_pwr, rpm, rv = rv, \
wing_area = wing_area)
return ROC
alt = 0
time = 0
fuel_used = U.avgas_conv(TO_fuel, from_units=fuel_units, to_units='lb')
weight = weight - fuel_used
dist = TO_dist
if pwr == 'max':
# rpm = 2700
rpm = 2650
MP_max = 30
elif pwr == 'cc':
rpm = 2500
MP_max = 25
elif pwr == 2500:
rpm = 2500
MP_max = 30
else:
raise ValueError("pwr must be one of 'max', 'cc', or 2500")
if output == 'raw':
print(S.center('Altitude', 10), end=' ')
print(S.center('ROC', 10), end=' ')
print(S.center('Time', 10), end=' ')
print(S.center('Fuel Used', 10), end=' ')
print(S.center('Dist', 10), end=' ')
print(S.center('Speed', 10))
print(S.center('(ft)', 10), end=' ')
print(S.center('(ft/mn)', 10), end=' ')
print(S.center('(mn)', 10), end=' ')
f_units = '(' + fuel_units + ')'
print(S.center(f_units, 10), end=' ')
print(S.center('(nm)', 10), end=' ')
print(S.center('(KCAS)', 10))
# data for MSL
print(S.rjust(locale.format('%.0f', 0, True), 7), end=' ')
# calculate ROC at MSL
print(S.rjust(locale.format('%.0f', round(_alt2ROC(prop, 0) / 10.) * 10, \
True), 10), end=' ')
print(S.rjust('%.1f' % (0), 10), end=' ')
print(S.rjust('%.1f' % (TO_fuel), 10), end=' ')
print(S.rjust('%.1f' % (TO_dist), 10), end=' ')
print(S.rjust('%3d' % (alt2roc_speed(0, climb_speed=climb_speed)), 10))
elif output == 'latex':
temp = 15 + isa_dev
MSL_line = []
MSL_line.append(str(locale.format('%.0f', weight, True)))
MSL_line.append('0')
MSL_line.append(str(locale.format('%.0f', temp)))
MSL_line.append(str(locale.format('%.0f', alt2roc_speed(0, \
climb_speed = climb_speed))))
MSL_line.append(str(locale.format('%.0f', round(_alt2ROC(prop, 0) / 10.)\
* 10, True)))
MSL_line.append('0')
MSL_line.append(str(TO_fuel))
MSL_line.append(str(TO_dist))
print('&'.join(MSL_line) + '\\\\')
print('\\hline')
elif output == 'array':
# no header rows, but make blank array
array = [[0, 0, TO_fuel, 0]]
calc_alt = alt_interval / 2.
while calc_alt < alt_max:
temp = SA.isa2temp(isa_dev, calc_alt)
pwr = alt2pwr(calc_alt, rpm=rpm, MP_max=MP_max, temp=temp)
calc_pwr = pwr * pwr_factor
cas = alt2roc_speed(calc_alt, climb_speed=climb_speed)
eas = A.cas2eas(cas, calc_alt)
tas = A.cas2tas(cas, calc_alt, temp=temp, temp_units=temp_units)
tas_fts = U.speed_conv(tas, from_units='kt', to_units='ft/s')
ROC = roc(prop, calc_alt, eas, weight, calc_pwr, rpm, rv = rv, \
wing_area = wing_area)
roc_fts = ROC / 60
fuel_flow = IO.pwr2ff(pwr, rpm, ff_units='lb/hr')
slice_time = alt_interval / roc_fts
slice_dist = tas_fts * slice_time
slice_fuel = fuel_flow * slice_time / 3600
fuel_used += slice_fuel
fuel_out = (U.avgas_conv(fuel_used, from_units = 'lb', \
to_units = fuel_units))
weight -= slice_fuel
alt += alt_interval
cas_out = alt2roc_speed(alt, climb_speed=climb_speed)
temp_out = SA.isa2temp(isa_dev, alt)
ROC = _alt2ROC(prop, alt)
time += slice_time / 60
dist += slice_dist / 6076.115
if output == 'raw':
print(S.rjust(locale.format('%.0f', alt, True), 7), end=' ')
# calculate ROC at the displayed altitude
print(S.rjust(locale.format('%.0f', ROC, True), 10), end=' ')
print(S.rjust('%.1f' % (time), 10), end=' ')
print(S.rjust('%.1f' % (fuel_out), 10), end=' ')
print(S.rjust('%.1f' % (dist), 10), end=' ')
print(S.rjust('%3d' % (int(cas_out)), 10))
elif output == 'latex':
line = []
line.append(str(locale.format('%.0f', alt, True)))
line.append(str(locale.format('%.0f', round(temp_out))))
line.append(str(locale.format('%.0f', cas_out)))
line.append(str(locale.format('%.0f',
round(ROC / 10.) * 10, True)))
line.append(str(locale.format('%.0f', time)))
line.append(str(locale.format('%.1f', fuel_out)))
line.append(str(locale.format('%.0f', dist)))
print('&' + '&'.join(line) + '\\\\')
print('\\hline')
elif output == 'array':
array.append([alt, time, fuel_out, dist])
calc_alt += alt_interval
if output == 'array':
return array
