def optimizeFullyTest():
import planeDesigner, jets, lift
# use the same plane as above but with a turbojet because that shows more interesting behaviour
p = plane(planeDesigner.part(jets.turbojet),
planeDesigner.part(jets.radialIntake, 2),
planeDesigner.part(lift.avr8, 2),
planeDesigner.part(lift.deltaDeluxe, 2),
planeDesigner.part(lift.deltaDeluxe, 2, AoAdegrees = 10),
planeDesigner.part(None, n = 2, Cd = 0.2, extraMass = 0.15 + 150 * 0.005), # two fuel tanks
)
p.optimizeFuelConsumption(verbose = True, altitudeStep = 1000)
def speedTest():
import planeDesigner, jets, lift
p = plane(planeDesigner.part(jets.basicjet),
planeDesigner.part(jets.radialIntake, 2),
planeDesigner.part(lift.avr8, 2),
planeDesigner.part(lift.deltaDeluxe, 2),
planeDesigner.part(lift.deltaDeluxe, 2, AoAdegrees = 10),
planeDesigner.part(None, n = 2, Cd = 0.2, extraMass = 0.15 + 150 * 0.005), # two fuel tanks
)
speed = p.equilibriumHorizontalSpeed(2.5, altitude = 10000, throttle = 0.5)
print ("equilibrium speed: %g m/s" % speed)
p.forces(0, 2.5, speed, altitude = 10000, throttle = 0.5)
def optimizePitchTest():
import planeDesigner, jets, lift
p = plane(planeDesigner.part(jets.basicjet),
planeDesigner.part(jets.radialIntake, 2),
planeDesigner.part(lift.avr8, 2),
planeDesigner.part(lift.deltaDeluxe, 2),
planeDesigner.part(lift.deltaDeluxe, 2, AoAdegrees = 10),
planeDesigner.part(None, n = 2, Cd = 0.2, extraMass = 0.15 + 150 * 0.005), # two fuel tanks
)
opt = p.optimizeFuelConsumptionAtAltitude(altitude = 10000, verbose = True)
if opt is None:
print ("Level flight is impossible with any pitch and throttle at this altitude")
else:
(pitch, throttle, speed, fuelKgPerM) = opt
fuelUnitsPerKm = fuelKgPerM * 1000 / 5
print ("Fly at %d degrees, throttle %.3f, to achieve %.2f m/s using %g U/km" % (pitch, throttle, speed, fuelUnitsPerKm))
def throttleTest():
import planeDesigner, jets, lift
p = plane(planeDesigner.part(jets.basicjet),
planeDesigner.part(jets.radialIntake, 2),
planeDesigner.part(lift.avr8, 2),
planeDesigner.part(lift.deltaDeluxe, 2),
planeDesigner.part(lift.deltaDeluxe, 2, AoAdegrees = 10),
planeDesigner.part(None, n = 2, Cd = 0.2, extraMass = 0.15 + 150 * 0.005), # two fuel tanks
)
throttle = p.levelThrottle(10, altitude = 10000)
if throttle is None:
print ("level flight is impossible")
else:
speed = p.equilibriumHorizontalSpeed(2.5, altitude = 10000, throttle = throttle)
print ("equilibrium speed: %g m/s" % speed)
p.forces(0, 2.5, speed, altitude = 10000, throttle = throttle)
def forcesTest():
"""
The plane has a basic jet and two radial intakes.
It's got 2 AV-R8 for its elevator, two deltaDeluxe for ailerons,
and two deltaDeluxe for wings, which are tilted 10 degrees.
There's also two fuel tanks, full.
We're climbing at a 5 degree angle, with pitch 7.5 degrees (so angle of attack 2.5 degrees).
We're going Mach 0.85, at 10km altitude.
This plane is not at equilibrium: we've got horizontal speed to gain,
and vertical speed is going down. Specifically, we should see:
net: ( 25.72, -15.09) kN
"""
import planeDesigner, jets, lift
p = plane(planeDesigner.part(jets.basicjet),
planeDesigner.part(jets.radialIntake, 2),
planeDesigner.part(lift.avr8, 2),
planeDesigner.part(lift.deltaDeluxe, 2),
planeDesigner.part(lift.deltaDeluxe, 2, AoAdegrees = 10),
planeDesigner.part(None, n = 2, Cd = 0.2, extraMass = 0.15 + 150 * 0.005), # two fuel tanks
)
p.forces(5, 2.5, 0.85 * 342, altitude = 10000, throttle = 0.5)
