def cl2lift(
Cl,
eas,
wing_area,
speed_units=default_speed_units,
lift_units=default_weight_units,
area_units=default_area_units,
):
"""
Returns the lift, given coefficient of lift, equivalent airspeed, and wing
area.
"""
eas = U.speed_conv(eas, from_units=speed_units, to_units='m/s')
wing_area = U.area_conv(wing_area, from_units=area_units,
to_units='m**2')
lift = (((0.5 * Rho0) * eas ** 2.) * wing_area) * Cl
if lift_units == 'kg':
lift = U.force_conv(lift, 'N', 'lb')
lift = U.mass_conv(lift, 'lb', 'kg')
else:
lift = U.force_conv(lift, 'N', lift_units)
return lift
def cl2lift(
Cl,
eas,
wing_area,
speed_units=default_speed_units,
lift_units=default_weight_units,
area_units=default_area_units,
):
"""
Returns the lift, given coefficient of lift, equivalent airspeed, and wing
area.
"""
eas = U.speed_conv(eas, from_units=speed_units, to_units='m/s')
wing_area = U.area_conv(wing_area, from_units=area_units, to_units='m**2')
lift = (((0.5 * Rho0) * eas**2.) * wing_area) * Cl
if lift_units == 'kg':
lift = U.force_conv(lift, 'N', 'lb')
lift = U.mass_conv(lift, 'lb', 'kg')
else:
lift = U.force_conv(lift, 'N', lift_units)
return lift
def test_03(self):
Value = U.mass_conv(100, from_units='lb', to_units='lb')
Truth = 100
self.failUnless(RE(Value, Truth) <= 1e-8)
def test_02(self):
Value = U.mass_conv(45.359237, from_units='kg', to_units='lb')
Truth = 100
self.failUnless(RE(Value, Truth) <= 1e-8)
def test_01(self):
Value = U.mass_conv(100, from_units='lb', to_units='kg')
Truth = 45.359237
self.failUnless(RE(Value, Truth) <= 1e-8)
def test_03(self):
Value = U.mass_conv(100, from_units='lb', to_units='lb')
Truth = 100
self.assertTrue(RE(Value, Truth) <= 1e-8)
def test_02(self):
Value = U.mass_conv(45.359237, from_units='kg', to_units='lb')
Truth = 100
self.assertTrue(RE(Value, Truth) <= 1e-8)
def test_01(self):
Value = U.mass_conv(100, from_units='lb', to_units='kg')
Truth = 45.359237
self.assertTrue(RE(Value, Truth) <= 1e-8)
