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)