コード例 #1
0
    def test_02(self):

        # Truth values from NASA RP 1046

        Value = SA.alt2density_ratio(8000)
        Truth = 0.06011 / 0.076474
        self.assertTrue(RE(Value, Truth) <= 1e-5)
コード例 #2
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    def test_02(self):

        # Truth values from NASA RP 1046

        Value = SA.alt2density_ratio(8000)
        Truth = 0.06011 / 0.076474
        self.failUnless(RE(Value, Truth) <= 1e-5)
コード例 #3
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    def test_03(self):

        # truth value calculated from program at:
        # http://www.sworld.com.au/steven/space/atmosphere/

        Value = SA.alt2density_ratio(1999, alt_units='m')
        Truth = .82168
        self.assertTrue(RE(Value, Truth) <= 5e-5)
コード例 #4
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    def test_03(self):

        # truth value calculated from program at:
        # http://www.sworld.com.au/steven/space/atmosphere/

        Value = SA.alt2density_ratio(1999, alt_units='m')
        Truth = .82168
        self.failUnless(RE(Value, Truth) <= 5e-5)
コード例 #5
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def _pwr_std_temp(rpm, MP, altitude):
    """
    Returns the power at a given rpm, MP and altitude, assuming
    standard temperature.

    Units are n/mn, inches HG and feet.

    Example:

    Determine power at 2700 rpm, 28.6 inches HG manifold pressure
    and 0 ft altitude:
    >>> _pwr_std_temp(2700, 28.2, 0)
    179.78232558139536

    """
    # get the power at sea level (i.e. point B on the left side of the
    # Lycoming power chart)

    # get pwr at two even hundreds of rpm, and then interpolate
    if rpm >= 2600:
        rpm1 = 2600
        rpm2 = 2700
    elif rpm >= 2400:
        rpm1 = 2400
        rpm2 = 2600
    elif rpm >= 2200:
        rpm1 = 2200
        rpm2 = 2400
    else:
        rpm1 = 2000
        rpm2 = 2400

    pwr_SL1 = _pwr_sl(rpm1, MP)
    pwr_SL2 = _pwr_sl(rpm2, MP)

    # get power at full throttle at this rpm and MP at altitude (i.e. point A on the right side of the Lycoming power chart)
    # density ratio at point A on the right side of the Lycoming power chart)
    pwr_FT1, DR_FT1 = _hp_at_MP_and_altitude(rpm1, MP)
    pwr_FT2, DR_FT2 = _hp_at_MP_and_altitude(rpm2, MP)

    # density ratio at sea level
    DR_sl = 1

    # density ratio for the actual conditions (i.e. point D on the right side
    # of the Lycoming power chart)
    DR_test = SA.alt2density_ratio(altitude)

    pwr_std_temp1 = pwr_SL1 + (DR_test - DR_sl) * \
        (pwr_FT1 - pwr_SL1) / (DR_FT1 - DR_sl)
    pwr_std_temp2 = pwr_SL2 + (DR_test - DR_sl) * \
        (pwr_FT2 - pwr_SL2) / (DR_FT2 - DR_sl)

    pwr_std_temp = pwr_std_temp1 + \
        (rpm - rpm1) * (pwr_std_temp2 - pwr_std_temp1) / (rpm2 - rpm1)

    return pwr_std_temp
コード例 #6
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ファイル: io360a.py プロジェクト: khorton/AeroCalc_Package
def _hp_at_FT(rpm, altitude):
    """ 
    Returns the horsepower at full throttle at a given rpm and altitude.
    """
    # get density ratio from the altitude
    DR = SA.alt2density_ratio(altitude)

    # get power at rpm
    hp_sl = HP_FT[rpm]['hp_sl']
    hp_23K = HP_FT[rpm]['hp_23K']
    hp_at_FT = hp_sl - (1 - DR) * (hp_sl - hp_23K) / (1 - DR_23K)

    return hp_at_FT
コード例 #7
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def _hp_at_FT(rpm, altitude):
    """ 
    Returns the horsepower at full throttle at a given rpm and altitude.
    """
    # get density ratio from the altitude
    DR = SA.alt2density_ratio(altitude)
    
    # get power at rpm
    hp_sl = HP_FT[rpm]['hp_sl']
    hp_23K = HP_FT[rpm]['hp_23K']
    hp_at_FT = hp_sl - (1 - DR) * (hp_sl - hp_23K) / (1 - DR_23K)
    
    return hp_at_FT
コード例 #8
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ファイル: o360a.py プロジェクト: briandwendt/AeroCalc_Package
def _pwr_std_temp(rpm, MP, altitude):
	""" 
	Returns the power at a given rpm, MP and altitude, assuming 
	standard temperature.
	
	Units are n/mn, inches HG and feet.
	
	Example:
	
	Determine power at 2700 rpm, 28.6 inches HG manifold pressure 
	and 0 ft altitude:
	>>> _pwr_std_temp(2700, 28.2, 0)
	179.78232558139536

	"""
	# get the power at sea level (i.e. point B on the left side of the Lycoming power chart)
	
	# get pwr at two even hundreds of rpm, and then interpolate
	if rpm >= 2600:
		rpm1 = 2600
		rpm2 = 2700
	elif rpm >= 2400:
		rpm1 = 2400
		rpm2 = 2600
	elif rpm >= 2200:
		rpm1 = 2200
		rpm2 = 2400
	else:
		rpm1 = 2000
		rpm2 = 2400
	
	pwr_SL1 = _pwr_sl(rpm1, MP)
	pwr_SL2 = _pwr_sl(rpm2, MP)
	
	# get power at full throttle at this rpm and MP at altitude (i.e. point A on the right side of the Lycoming power chart)
	# density ratio at point A on the right side of the Lycoming power chart)
	pwr_FT1, DR_FT1 = _hp_at_MP_and_altitude(rpm1, MP)
	pwr_FT2, DR_FT2 = _hp_at_MP_and_altitude(rpm2, MP)
	
	# density ratio at sea level
	DR_sl = 1
		
	# density ratio for the actual conditions (i.e. point D on the right side of the Lycoming power chart)
	DR_test = SA.alt2density_ratio(altitude)
	
	pwr_std_temp1 = pwr_SL1 + (DR_test - DR_sl) * (pwr_FT1 - pwr_SL1) / (DR_FT1 - DR_sl)
	pwr_std_temp2 = pwr_SL2 + (DR_test - DR_sl) * (pwr_FT2 - pwr_SL2) / (DR_FT2 - DR_sl)
	
	pwr_std_temp = pwr_std_temp1 + (rpm - rpm1) * (pwr_std_temp2 - pwr_std_temp1) / (rpm2 - rpm1)

	return pwr_std_temp
コード例 #9
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 def test_01(self):
     PR = SA.alt2density_ratio(0)
     self.assertEqual(PR, 1)
コード例 #10
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ファイル: io360a.py プロジェクト: khorton/AeroCalc_Package
def _pwr_std_temp(rpm, MP, altitude):
    """ 
    Returns the power at a given rpm, MP and altitude, assuming 
    standard temperature.
    
    Units are n/mn, inches HG and feet.
    
    Example:
    
    Determine power at 2700 rpm, 28.6 inches HG manifold pressure and 
    0 ft altitude:
    >>> _pwr_std_temp(2700, 28.6, 0)
    200.0

    """
    # get the power at sea level (i.e. point B on the left side of the Lycoming power chart)

    # get pwr at two even hundreds of rpm, and then interpolate
    if rpm >= 2600:
        rpm1 = 2600
    elif rpm <= 1800:
        rpm1 = 1800
    else:
        rpm1 = rpm - rpm % 100

    rpm2 = rpm1 + 100

    pwr_SL1 = _pwr_sl(rpm1, MP)
    pwr_SL2 = _pwr_sl(rpm2, MP)
    # print "SL Pwr 1=", pwr_SL1
    # print "SL Pwr 2=", pwr_SL2

    # get power at full throttle at this rpm and MP at altitude (i.e. point A on the right side of the Lycoming power chart)
    # density ratio at point A on the right side of the Lycoming power chart)
    pwr_FT1, DR_FT1 = _hp_at_MP_and_altitude(rpm1, MP)
    pwr_FT2, DR_FT2 = _hp_at_MP_and_altitude(rpm2, MP)
    # print "FT pwr 1=", pwr_FT1
    # print "FT pwr 2=", pwr_FT2
    # print "DR FT 1=", DR_FT1
    # print "DR FT 2=", DR_FT2

    # density ratio at sea level
    DR_sl = 1

    # density ratio for the actual conditions (i.e. point D on the right side of the Lycoming power chart)
    DR_test = SA.alt2density_ratio(altitude)
    # print "DR_test=", DR_test

    # function is unstable if the DR at FT is close to 1.  This sends the slope off to unpredictable values.
    slope1 = (pwr_FT1 - pwr_SL1) / (DR_FT1 - DR_sl)
    slope2 = (pwr_FT2 - pwr_SL2) / (DR_FT2 - DR_sl)

    if MP > 28:
        if slope1 < -80:
            slope1 = -62
        elif slope1 > -60:
            slope1 = -62
        if slope2 < -80:
            slope2 = -62
        elif slope2 > -60:
            slope2 = -62

    # print "slope1=", slope1
    # print "slope2=", slope2

    pwr_std_temp1 = pwr_SL1 + (DR_test - DR_sl) * slope1
    pwr_std_temp2 = pwr_SL2 + (DR_test - DR_sl) * slope2
    # print "Pwr Std Temp 1=", pwr_std_temp1
    # print "Pwr Std Temp 2=", pwr_std_temp2
    pwr_std_temp = pwr_std_temp1 + (rpm - rpm1) * (
        pwr_std_temp2 - pwr_std_temp1) / (rpm2 - rpm1)

    return pwr_std_temp
コード例 #11
0
ファイル: perf_climb_FF.py プロジェクト: khorton/POH
#! /usr/bin/env python

import std_atm as SA

FF0 = 17
for alt in range(0, 20001, 2000):
    sigma = SA.alt2density_ratio(alt)
    FF = sigma * FF0 * 2700 / 2700
    print "%.0f %.1f" % (alt, FF)
コード例 #12
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 def test_01(self):
     PR = SA.alt2density_ratio(0)
     self.assertEqual(PR, 1)
コード例 #13
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def _pwr_std_temp(rpm, MP, altitude):
    """ 
    Returns the power at a given rpm, MP and altitude, assuming 
    standard temperature.
    
    Units are n/mn, inches HG and feet.
    
    Example:
    
    Determine power at 2700 rpm, 28.6 inches HG manifold pressure and 
    0 ft altitude:
    >>> _pwr_std_temp(2700, 28.6, 0)
    200.0

    """
    # get the power at sea level (i.e. point B on the left side of the Lycoming power chart)
    
    # get pwr at two even hundreds of rpm, and then interpolate
    if rpm >= 2600:
        rpm1 = 2600
    elif rpm <= 1800:
        rpm1 = 1800
    else:
        rpm1 = rpm - rpm % 100

    rpm2 = rpm1 + 100
    
    pwr_SL1 = _pwr_sl(rpm1, MP)
    pwr_SL2 = _pwr_sl(rpm2, MP)
    # print "SL Pwr 1=", pwr_SL1
    # print "SL Pwr 2=", pwr_SL2
    
    # get power at full throttle at this rpm and MP at altitude (i.e. point A on the right side of the Lycoming power chart)
    # density ratio at point A on the right side of the Lycoming power chart)
    pwr_FT1, DR_FT1 = _hp_at_MP_and_altitude(rpm1, MP)
    pwr_FT2, DR_FT2 = _hp_at_MP_and_altitude(rpm2, MP)
    # print "FT pwr 1=", pwr_FT1
    # print "FT pwr 2=", pwr_FT2
    # print "DR FT 1=", DR_FT1
    # print "DR FT 2=", DR_FT2
    
    # density ratio at sea level
    DR_sl = 1
        
    # density ratio for the actual conditions (i.e. point D on the right side of the Lycoming power chart)
    DR_test = SA.alt2density_ratio(altitude)
    # print "DR_test=", DR_test
    
    # function is unstable if the DR at FT is close to 1.  This sends the slope off to unpredictable values.
    slope1=(pwr_FT1 - pwr_SL1) / (DR_FT1 - DR_sl)
    slope2=(pwr_FT2 - pwr_SL2) / (DR_FT2 - DR_sl)
    
    if MP > 28:
        if slope1 < -80:
            slope1=-62
        elif slope1> -60:
            slope1=-62
        if slope2< -80:
            slope2 = -62
        elif slope2> -60:
            slope2=-62
    
    # print "slope1=", slope1
    # print "slope2=", slope2
    
    pwr_std_temp1 = pwr_SL1 + (DR_test - DR_sl) * slope1
    pwr_std_temp2 = pwr_SL2 + (DR_test - DR_sl) * slope2
    # print "Pwr Std Temp 1=", pwr_std_temp1
    # print "Pwr Std Temp 2=", pwr_std_temp2
    pwr_std_temp = pwr_std_temp1 + (rpm - rpm1) * (pwr_std_temp2 - pwr_std_temp1) / (rpm2 - rpm1)

    return pwr_std_temp
コード例 #14
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def cruise_data(prop, cruise_A=821.27884302, cruise_B=3.8201670757e-05,\
    cruise_power = 130, mixture = 'econ', cruise_rpm=2400, climb_weight=1800., \
    descent_weight=1600., alt_max=20000., fuel_units='USG', alt_interval=500., \
    isa_dev=0, temp_units='C', rv='8', wing_area=110., TO_fuel = 1.5, TO_dist = 0, \
    climb_pwr = 'max', climb_pwr_factor=0.9, \
    climb_speed = 'norm',  \
    descent_tas=180, descent_ROD=-500., descent_angle='', speed_units='kt', \
    descent_rpm=2100., descent_sfc=0.45, fuel_reserve=8, output='raw'):
    """
    Returns a table of cruise 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), data 
    (suitable for graphing with gnuplot) or array.
    
    descent_angle is the flight path angle in degrees.  It overrides the rate of 
    descent (ROD) if provided.
    """
    Wt_std = 1800.
    Wt_ratio = climb_weight/Wt_std
    climb_data_a = climb_data(prop, weight = climb_weight, alt_max = alt_max, TO_fuel = TO_fuel, TO_dist = TO_dist,  fuel_units = fuel_units, alt_interval = alt_interval, isa_dev = isa_dev, temp_units = temp_units, rv = rv, wing_area = wing_area, pwr = climb_pwr, pwr_factor=climb_pwr_factor, climb_speed = climb_speed, output = 'array')
    descent_data_a = descent_data(prop, weight=descent_weight, alt_max=alt_max, fuel_units=fuel_units,  alt_interval=alt_interval, isa_dev=isa_dev, temp_units=temp_units, rv=rv,  wing_area=wing_area, tas=descent_tas, ROD=descent_ROD, angle=descent_angle, speed_units=speed_units, rpm=descent_rpm, sfc=descent_sfc, output='array')
    cruise_ff = IO.pwr2ff(cruise_power, cruise_rpm, mixture=mixture)
    
    if output == 'raw':
        print "Climb speed = %s and climb power = %s" % (climb_speed, climb_pwr)
        print "Cruise power = %.0f and cruise fuel flow = %.2f" % (cruise_power, cruise_ff)
        print S.center('Altitude', 10),
        print S.center('TAS', 10),
        print S.center('Range', 10),
        print S.center('Fuel Flow', 10)
        
        
        print S.center('(ft)', 10),
        print S.center('(kt)', 10),
        print S.center('(nm)', 10),
        print S.center('(USG/h)', 10)
    elif output == 'array':
        array = []
    elif output == 'data':
        if descent_angle:
            angle_text = 'a descent angle of %s degrees' % descent_angle
        else:
            angle_text = 'a descent rate of %i ft/mn' % descent_ROD
        print '# RV-8 Cruise Range Chart - Wheel Pants OFF'
        print '# descent at %.0f KTAS and %s' % (descent_tas, angle_text)
        print '# %i%% power with fuel flow of %.1f USG/hr' % (cruise_power / 2., cruise_ff)
        print '# altitude  range'
        print '# ft KTAS'
        
    elif output == 'latex':
        line.append(str(locale.format('%.0f', calt, True)))
        line.append(str(locale.format('%.1f', cruise_tas)))
        line.append(str(locale.format('%.0f', total_dist)))
        # print line
        pass
    for item in zip(climb_data_a, descent_data_a):
        ([calt, ctime, cfuel, cdist], [dalt, dtime, dfuel, ddist]) = item
        cruise_fuel = 42 - (cfuel + dfuel + fuel_reserve)
        sigma = SA.alt2density_ratio(calt)
        cruise_tas = 1/12.*((8*cruise_A*cruise_B*Wt_ratio**2 + (3.*M.sqrt(3.)*cruise_power**2*sigma + M.sqrt(-256*cruise_A**3.*cruise_B*Wt_ratio**6 + 27.*cruise_power**4*sigma**2))**(2/3.)*2**(1/3.)*cruise_B**(2/3.))**(3./4)*3.**(3./4)*sigma**(1/4.) + M.sqrt(12.*M.sqrt(3.*M.sqrt(3.)*cruise_power**2*sigma + M.sqrt(-256*cruise_A**3.*cruise_B*Wt_ratio**6 + 27.*cruise_power**4*sigma**2))*cruise_B**(1/3.)*cruise_power*sigma - M.sqrt(8*cruise_A*cruise_B*Wt_ratio**2 + (3.*M.sqrt(3.)*cruise_power**2*sigma + M.sqrt(-256*cruise_A**3.*cruise_B*Wt_ratio**6 + 27.*cruise_power**4*sigma**2))**(2/3.)*2**(1/3.)*cruise_B**(2/3.))*(8*3.**(1/4.)*cruise_A*cruise_B**(1/3.)*Wt_ratio**2*M.sqrt(sigma) + (3.*M.sqrt(3.)*cruise_power**2*sigma + M.sqrt(-256*cruise_A**3.*cruise_B*Wt_ratio**6 + 27.*cruise_power**4*sigma**2))**(2/3.)*2**(1/3.)*3.**(1/4.)*M.sqrt(sigma)))*3.**(5/8)*abs(cruise_B)**(1/3.))*2**(2/3.)/((3.*M.sqrt(3.)*cruise_power**2*sigma + M.sqrt(-256*cruise_A**3.*cruise_B*Wt_ratio**6 + 27.*cruise_power**4*sigma**2))**(1/6.)*(8*cruise_A*cruise_B*Wt_ratio**2 + (3.*M.sqrt(3.)*cruise_power**2*sigma + M.sqrt(-256*cruise_A**3.*cruise_B*Wt_ratio**6 + 27.*cruise_power**4*sigma**2))**(2/3.)*2**(1/3.)*cruise_B**(2/3.))**(1/4.)*cruise_B**(2/3.)*sigma**(3./4))
        cruise_dist = cruise_fuel * cruise_tas / cruise_ff
        cruise_time = cruise_dist / cruise_tas * 60
        total_dist = cdist + cruise_dist + ddist
        total_time = ctime + cruise_time + dtime
#        print "%5.0f %.1f %.1f %.1f %5.1f" %  (calt, cruise_tas, cruise_fuel, cruise_dist, total_dist)
        if output == 'raw':
            print S.rjust(locale.format('%.0f', calt, True), 7),
            print S.rjust('%.1f' % (cruise_tas), 10),
            print S.rjust('%.1f' % (total_dist), 10),
            print S.rjust('%.1f' % (cruise_ff), 10)
        elif output == 'data':
            print '%.1f\t%.0f' % (total_dist, calt)
コード例 #15
0
ファイル: rv8_test.py プロジェクト: khorton/AeroCalc_Package
def cruise_data(prop, cruise_A=821.27884302, cruise_B=3.8201670757e-05,\
    cruise_power = 130, mixture = 'econ', cruise_rpm=2400, climb_weight=1800., \
    descent_weight=1600., alt_max=20000., fuel_units='USG', alt_interval=500., \
    isa_dev=0, temp_units='C', rv='8', wing_area=110., TO_fuel = 1.5, TO_dist = 0, \
    climb_pwr = 'max', climb_pwr_factor=0.9, \
    climb_speed = 'norm',  \
    descent_tas=180, descent_ROD=-500., descent_angle='', speed_units='kt', \
    descent_rpm=2100., descent_sfc=0.45, fuel_reserve=8, output='raw'):
    """
    Returns a table of cruise 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), data 
    (suitable for graphing with gnuplot) or array.
    
    descent_angle is the flight path angle in degrees.  It overrides the rate of 
    descent (ROD) if provided.
    """
    Wt_std = 1800.
    Wt_ratio = climb_weight / Wt_std
    climb_data_a = climb_data(prop,
                              weight=climb_weight,
                              alt_max=alt_max,
                              TO_fuel=TO_fuel,
                              TO_dist=TO_dist,
                              fuel_units=fuel_units,
                              alt_interval=alt_interval,
                              isa_dev=isa_dev,
                              temp_units=temp_units,
                              rv=rv,
                              wing_area=wing_area,
                              pwr=climb_pwr,
                              pwr_factor=climb_pwr_factor,
                              climb_speed=climb_speed,
                              output='array')
    descent_data_a = descent_data(prop,
                                  weight=descent_weight,
                                  alt_max=alt_max,
                                  fuel_units=fuel_units,
                                  alt_interval=alt_interval,
                                  isa_dev=isa_dev,
                                  temp_units=temp_units,
                                  rv=rv,
                                  wing_area=wing_area,
                                  tas=descent_tas,
                                  ROD=descent_ROD,
                                  angle=descent_angle,
                                  speed_units=speed_units,
                                  rpm=descent_rpm,
                                  sfc=descent_sfc,
                                  output='array')
    cruise_ff = IO.pwr2ff(cruise_power, cruise_rpm, mixture=mixture)

    if output == 'raw':
        print("Climb speed = %s and climb power = %s" %
              (climb_speed, climb_pwr))
        print("Cruise power = %.0f and cruise fuel flow = %.2f" %
              (cruise_power, cruise_ff))
        print(S.center('Altitude', 10), end=' ')
        print(S.center('TAS', 10), end=' ')
        print(S.center('Range', 10), end=' ')
        print(S.center('Fuel Flow', 10))

        print(S.center('(ft)', 10), end=' ')
        print(S.center('(kt)', 10), end=' ')
        print(S.center('(nm)', 10), end=' ')
        print(S.center('(USG/h)', 10))
    elif output == 'array':
        array = []
    elif output == 'data':
        if descent_angle:
            angle_text = 'a descent angle of %s degrees' % descent_angle
        else:
            angle_text = 'a descent rate of %i ft/mn' % descent_ROD
        print('# RV-8 Cruise Range Chart - Wheel Pants OFF')
        print('# descent at %.0f KTAS and %s' % (descent_tas, angle_text))
        print('# %i%% power with fuel flow of %.1f USG/hr' %
              (cruise_power / 2., cruise_ff))
        print('# altitude  range')
        print('# ft KTAS')

    elif output == 'latex':
        line.append(str(locale.format('%.0f', calt, True)))
        line.append(str(locale.format('%.1f', cruise_tas)))
        line.append(str(locale.format('%.0f', total_dist)))
        # print line
        pass
    for item in zip(climb_data_a, descent_data_a):
        ([calt, ctime, cfuel, cdist], [dalt, dtime, dfuel, ddist]) = item
        cruise_fuel = 42 - (cfuel + dfuel + fuel_reserve)
        sigma = SA.alt2density_ratio(calt)
        cruise_tas = 1 / 12. * (
            (8 * cruise_A * cruise_B * Wt_ratio**2 +
             (3. * M.sqrt(3.) * cruise_power**2 * sigma +
              M.sqrt(-256 * cruise_A**3. * cruise_B * Wt_ratio**6 +
                     27. * cruise_power**4 * sigma**2))**(2 / 3.) * 2**
             (1 / 3.) * cruise_B**(2 / 3.))**(3. / 4) * 3.**(3. / 4) * sigma**
            (1 / 4.) + M.sqrt(
                12. *
                M.sqrt(3. * M.sqrt(3.) * cruise_power**2 * sigma +
                       M.sqrt(-256 * cruise_A**3. * cruise_B * Wt_ratio**6 +
                              27. * cruise_power**4 * sigma**2)) * cruise_B**
                (1 / 3.) * cruise_power * sigma -
                M.sqrt(8 * cruise_A * cruise_B * Wt_ratio**2 +
                       (3. * M.sqrt(3.) * cruise_power**2 * sigma +
                        M.sqrt(-256 * cruise_A**3. * cruise_B * Wt_ratio**6 +
                               27. * cruise_power**4 * sigma**2))**
                       (2 / 3.) * 2**(1 / 3.) * cruise_B**(2 / 3.)) *
                (8 * 3.**(1 / 4.) * cruise_A * cruise_B**
                 (1 / 3.) * Wt_ratio**2 * M.sqrt(sigma) +
                 (3. * M.sqrt(3.) * cruise_power**2 * sigma +
                  M.sqrt(-256 * cruise_A**3. * cruise_B * Wt_ratio**6 +
                         27. * cruise_power**4 * sigma**2))**(2 / 3.) * 2**
                 (1 / 3.) * 3.**(1 / 4.) * M.sqrt(sigma))) * 3.**
            (5 / 8) * abs(cruise_B)**(1 / 3.)) * 2**(2 / 3.) / (
                (3. * M.sqrt(3.) * cruise_power**2 * sigma +
                 M.sqrt(-256 * cruise_A**3. * cruise_B * Wt_ratio**6 +
                        27. * cruise_power**4 * sigma**2))**(1 / 6.) *
                (8 * cruise_A * cruise_B * Wt_ratio**2 +
                 (3. * M.sqrt(3.) * cruise_power**2 * sigma +
                  M.sqrt(-256 * cruise_A**3. * cruise_B * Wt_ratio**6 +
                         27. * cruise_power**4 * sigma**2))**(2 / 3.) * 2**
                 (1 / 3.) * cruise_B**(2 / 3.))**(1 / 4.) *
                cruise_B**(2 / 3.) * sigma**(3. / 4))
        cruise_dist = cruise_fuel * cruise_tas / cruise_ff
        cruise_time = cruise_dist / cruise_tas * 60
        total_dist = cdist + cruise_dist + ddist
        total_time = ctime + cruise_time + dtime
        #        print "%5.0f %.1f %.1f %.1f %5.1f" %  (calt, cruise_tas, cruise_fuel, cruise_dist, total_dist)
        if output == 'raw':
            print(S.rjust(locale.format('%.0f', calt, True), 7), end=' ')
            print(S.rjust('%.1f' % (cruise_tas), 10), end=' ')
            print(S.rjust('%.1f' % (total_dist), 10), end=' ')
            print(S.rjust('%.1f' % (cruise_ff), 10))
        elif output == 'data':
            print('%.1f\t%.0f' % (total_dist, calt))