def test_03(self):
# Truth values from NASA RP 1046
Value = SA.density_ratio2alt(.088035 / 1.225, alt_units='m')
Truth = 20000
self.assertTrue(RE(Value, Truth) <= 1e-5)
def test_03(self):
# Truth values from NASA RP 1046
Value = SA.density_ratio2alt(.088035 / 1.225, alt_units='m')
Truth = 20000
self.failUnless(RE(Value, Truth) <= 1e-5)
def test_02(self):
# Truth values from NASA RP 1046
Value = SA.density_ratio2alt(0.78601648829428272)
Truth = 8000
self.assertTrue(RE(Value, Truth) <= 1e-5)
def test_02(self):
# Truth values from NASA RP 1046
Value = SA.density_ratio2alt(0.78601648829428272)
Truth = 8000
self.failUnless(RE(Value, Truth) <= 1e-5)
def _hp_at_MP_and_altitude(rpm, MP):
"""
Returns the power and density ratio at a given rpm and MP at full throttle.
"""
# get density ratio for this MP and altitude, at full throttle
DR = _DR_FT_from_MP(rpm, MP)
# get power at this condition
altitude = SA.density_ratio2alt(DR)
hp = _hp_at_FT(rpm, altitude)
return hp, DR
def _hp_at_MP_and_altitude(rpm, MP):
"""
Returns the power and density ratio at a given rpm and MP at full throttle.
"""
# get density ratio for this MP and altitude, at full throttle
DR = _DR_FT_from_MP(rpm, MP)
# get power at this condition
altitude = SA.density_ratio2alt(DR)
hp = _hp_at_FT(rpm, altitude)
return hp, DR
def test_01(self):
PR = SA.density_ratio2alt(1)
self.assertEqual(PR, 0)
def test_01(self):
PR = SA.density_ratio2alt(1)
self.assertEqual(PR, 0)
