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Include script to calculate propulsion parameters over 24 hour cycle
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@djlee9812
djlee9812 committed Apr 4, 2020
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201 changes: 201 additions & 0 deletions airfoil/lrp01.dat
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LRP01
1.000132 0.1342817E-02
0.9960245 0.1957474E-02
0.9893750 0.2969499E-02
0.9803872 0.4339365E-02
0.9698709 0.5923217E-02
0.9587835 0.7580160E-02
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0.8914408 0.1717064E-01
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0.8690102 0.2008223E-01
0.8577757 0.2148551E-01
0.8465292 0.2285662E-01
0.8352741 0.2419714E-01
0.8240152 0.2550691E-01
0.8127525 0.2678558E-01
0.8014854 0.2803355E-01
0.7902154 0.2925074E-01
0.7789409 0.3043706E-01
0.7676588 0.3159371E-01
0.7563691 0.3272208E-01
0.7450726 0.3382306E-01
0.7337673 0.3489804E-01
0.7224527 0.3594901E-01
0.7111310 0.3697733E-01
0.6998028 0.3798388E-01
0.6884670 0.3897016E-01
0.6771251 0.3993762E-01
0.6657807 0.4088662E-01
0.6544351 0.4181690E-01
0.6430878 0.4272852E-01
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0.2860174E-04 -0.5302146E-03
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0.7221774 0.1344525E-01
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0.9801422 0.6975116E-03
0.9890846 -0.2040411E-03
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0.9998687 -0.1342817E-02
30 changes: 30 additions & 0 deletions airfoil/lrp01_polar.txt
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XFOIL Version 6.97

Calculated polar for: LRP01

1 1 Reynolds number fixed Mach number fixed

xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.300 Re = 0.100 e 6 Ncrit = 5.000

alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-5.000 -0.3054 0.05136 0.04652 -0.0491 1.0001 0.0255
-4.000 -0.1684 0.02864 0.02213 -0.0735 1.0001 0.0243
-3.000 -0.0352 0.01876 0.01030 -0.0785 1.0001 0.0315
-2.000 0.0896 0.01476 0.00598 -0.0798 1.0001 0.0863
-1.000 0.2309 0.01283 0.00530 -0.0855 0.9857 0.5199
0.000 0.3827 0.01142 0.00447 -0.0902 0.9244 0.9999
1.000 0.5226 0.01140 0.00395 -0.0922 0.8103 0.9999
2.000 0.6403 0.01224 0.00397 -0.0892 0.6337 0.9999
3.000 0.7500 0.01387 0.00487 -0.0861 0.4719 0.9999
4.000 0.8593 0.01581 0.00642 -0.0836 0.3442 0.9999
5.000 0.9670 0.01816 0.00868 -0.0810 0.2392 0.9999
6.000 1.0710 0.02122 0.01191 -0.0778 0.1569 0.9999
7.000 1.1672 0.02545 0.01658 -0.0737 0.0860 0.9999
8.000 1.2436 0.03244 0.02426 -0.0673 0.0461 0.9999
9.000 1.2869 0.04318 0.03641 -0.0589 0.0311 0.9999
10.000 1.2536 0.05855 0.05312 -0.0512 0.0278 0.9999
11.000 1.1802 0.08571 0.08118 -0.0664 0.0279 0.9999
12.000 1.1054 0.12231 0.11798 -0.0894 0.0291 0.9999
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46 changes: 46 additions & 0 deletions props/prop0402_1326
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Template prop lrp01.dat M0.3

2 ! Nblades

0.3800 6.2832 ! CL0 CL_a
-0.4000 1.2900 ! CLmin CLmax

0.01140 0.03400 0.02400 0.5226 ! CD0 CD2u CD2l CLCD0
100000.0 -0.500 ! REref REexp

1.0000 1.0000 1.0000 ! Rfac Cfac Bfac
0.0000 0.0000 0.0000 ! Radd Cadd Badd

# r c beta
0.16750 0.16127 72.6928
0.20250 0.20192 68.6625
0.23750 0.24105 64.8964
0.27250 0.27730 61.3844
0.30750 0.31009 58.1103
0.34250 0.33931 55.0578
0.37750 0.36462 52.2177
0.41250 0.38581 49.5796
0.44750 0.40287 47.1315
0.48250 0.41594 44.8601
0.51750 0.42530 42.7520
0.55250 0.43127 40.7940
0.58750 0.43418 38.9736
0.62250 0.43418 37.2805
0.65750 0.43142 35.7048
0.69250 0.42603 34.2372
0.72750 0.41812 32.8695
0.76250 0.40780 31.5938
0.79750 0.39514 30.4031
0.83250 0.38024 29.2909
0.86750 0.36314 28.2513
0.90250 0.34389 27.2789
0.93750 0.32250 26.3689
0.97250 0.29892 25.5168
1.0075 0.27306 24.7185
1.0425 0.24465 23.9705
1.0775 0.21318 23.2694
1.1125 0.17760 22.6120
1.1475 0.13530 21.9956
1.1825 0.76654E-01 21.4177
1.2000 0.41207E-01 21.1431
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104 changes: 104 additions & 0 deletions trajectory.py
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import numpy as np
import matplotlib.pyplot as plt
from mpl_toolkits.mplot3d import Axes3D
from matplotlib import cm
from air_data import change_air_data
from qprop_sweep import opt_dbeta, get_nums

def follow_trajectory(ts, hs, vs, thrusts, npt=24, unopt=False):
"""
Calculate propulsion parameters over a cycle trajectory and saves data
to "cycle.npz" using QProp
Requires time, altitude, airspeed, and thrust over the 24 hour trajectory
Parameters
----------
ts : array-like
Points in time
hs : array-like
Altitudes at given time points
vs : array-like
Airspeeds at given time poitns
thrusts : array-like
Required thrust at given time points
npt : int, optional
Number of time samples to evaluate/optimize at
unopt : boolean, optional
If checked, variable pitch is not allowed
"""
step = len(ts) // npt if npt <= len(ts) else 1
result = []
for i, t in enumerate(ts[::step]):
i *= step
h, v, thrust = (hs[i], vs[i], thrusts[i])
p = thrust * v
change_air_data(h)
opt = opt_dbeta(v, thrust)
dbeta = 0 if unopt else opt.x
eta_opt = -opt.fun
data = get_nums(dbeta, v, thrust)
rpm = data[1]
Q = data[4]
Pshaft = data[5]
eta = data[9]
J = data[10]
result.append([t, h, v, p, thrust, rpm, Q, Pshaft, J, dbeta, eta])
result = np.array(result)
plt.figure()
plt.title('24 Hour Trajectory')
plt.subplot(211)
plt.plot(result[:,0], result[:,1]/1000)
plt.ylabel('Altitude [km]')
plt.subplot(212)
plt.plot(result[:,0], result[:,2])
plt.ylabel('Airspeed [m/s]')
plt.xlabel("time [hr]")
plt.show()
np.savez("cycle", res=result)
print("Average Efficiency:", np.mean(result[:,10]))

def plot_trajectory(data_file="cycle.npz"):
"""
Plot various propulsion parameters from cycle.npz
Parameters
----------
data_file : str, optional
Name/Address of file containing plot data (from follow_trajectory())
"""
result = np.load(data_file)["res"].T
t, h, v, p, thrust, rpm, Q, Pshaft, J, dbeta, eta = result
plt.figure(figsize=(6,8))
plt.title("24 Hour Cycle")
plt.subplot(411)
plt.plot(t, h/1000)
plt.ylabel('Altitude [km]')
plt.subplot(412)
plt.plot(t, rpm)
plt.ylabel('RPM')
plt.subplot(413)
plt.plot(t, dbeta)
plt.ylabel(r'$d\beta$')
plt.subplot(414)
plt.plot(t, eta)
plt.ylabel(r'$\eta$')
plt.xlabel("Time [hr]")

plt.figure()
plt.plot(J, eta)
plt.xlabel("Advance Ratio")
plt.ylabel(r"$\eta$")
plt.figure()
plt.plot(rpm, Q)
plt.xlabel("RPM")
plt.ylabel("Torque [N/m]")
plt.show()

data = np.load('time_altitude_airspeed.npz')
ts = data['t']/3600
hs = data['h']
vs = data['v']
thrusts = data['thrust']
follow_trajectory(ts, hs, vs, thrusts, 200)

plot_trajectory()

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