for ax, row in zip(axes.flatten(), finalyy):
ax.plot(myx, row, "r-")
# ax.set_label('Label via method')
# ax.legend()
# turn remaining axes off
for i in range(len(finalyy), m):
axes.flatten()[i].axis("off")
# ax.legend()
# ax.title(i)
plt.tight_layout()
if __name__ == "__main__":
plt.show()
return mycombination
x = lifting_line_theory_subplots()
def final_subplot():
num = 1
# num = int(input('Select the graph:')) #AAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAA
return x[num - 1]
y = final_subplot()
if __name__ == "__main__":
print(y[0], "this is twist", y[1], "and this is the wing incidence")
write_to_db("alpha_twist", y[0])
write_to_db("wing_incidence", y[1])
# IMPLIED, INCLUDING BUT NOT LIMITED TO THE WARRANTIES OF MERCHANTABILITY, #
# FITNESS FOR A PARTICULAR PURPOSE AND NONINFRINGEMENT. IN NO EVENT SHALL THE #
# AUTHORS OR COPYRIGHT HOLDERS BE LIABLE FOR ANY CLAIM, DAMAGES OR OTHER #
# LIABILITY, WHETHER IN AN ACTION OF CONTRACT, TORT OR OTHERWISE, ARISING FROM, #
# OUT OF OR IN CONNECTION WITH THE SOFTWARE OR THE USE OR OTHER DEALINGS IN THE #
# SOFTWARE. #
# ----- #
# Copyright (c) 2020 KENYA ONE PROJECT #
##################################################################################
import sys
sys.path.append("../")
from CORE.API.db_API import write_to_db
from CORE.engines.prerequisitesEngine import paxWeight, crewWeight, payloadPax
rhoSL: float = 0.0023769
write_to_db("rhoSL", rhoSL)
# testing main line 37 replace later
# Get from prerequisites? DONE:
# paxWeight = 180
# crewWeight = 200
# payloadPax = 50
write_to_db("paxWeight", paxWeight)
write_to_db("crewWeight", crewWeight)
write_to_db("payloadPax", payloadPax)
CLto: float = 0.5
groundFriction: float = 0.04
def oswaldEff(AR: float) -> float:
e = (1.78 * (1 - (0.045 * AR ** 0.68))) - 0.64
return e
e = oswaldEff(AR)
k: float = 1 / (pi * AR * e)
write_to_db("k", k)
# dynamic pressure at altitude
def rhoAlt(cruiseAltitude: int) -> float:
rhoalt = rhoSL * (1 - 0.0000068756 * cruiseAltitude) ** 4.2561
return rhoalt
rhoCruise = rhoAlt(cruiseAltitude)
# print ('air density at cruise altitude, rho = ' +str(rhoCruise))
qAltitude = 0.5 * rhoCruise * (1.688 * cruiseSpeed) ** 2
# print('dynamic pressure at altitude = ' +str(qAltitude))
# Gag Ferrar Model
def gagFerrar(bhp):
final,
"possible combination",
fuselage_angle,
"<fuselage angle",
df,
"match",
)
num1 = "{0:.2f}".format(fuselage_angle)
num2 = "{0:.2f}".format(df)
mycombination.append((num1, num2))
outputcombination.append((fuselage_angle, df))
myy = final
finalyy.append(myy)
yy = np.asarray(finalyy)
else:
pass
print(mycombination, "select one ")
return outputcombination
# select one combination
combination = llt_final()
selectone = 0 ##########A
mycombination = combination[selectone]
print(mycombination, "final fuselage_angle and df")
llt_full(mycombination[0], mycombination[1])
write_to_db("CL_TO", initial_CL_TO)
## 3D Lift Curve Slope
# for elliptical wing
Mach = cruiseSpeed / 11164.27
wing3 = aa.CLalfa(clalfa, rangeAR, Mach, sweepHalfChord)
# make this shit work
# finalCLalfa = np.average(wing1.ellipticalCLalfa(),wing1.hemboldCLalfa(),wing1.polhamusCLalfa())
finalCLalfa = (wing3.ellipticalCLalfa() + wing3.hemboldCLalfa() +
wing3.polhamusCLalfa()) / 3
# print(wing3.ellipticalCLalfa())
# print(wing3.hemboldCLalfa())
# # print(wing3.polhamusCLalfa())
# print('average CLalfa')
# print(finalCLalfa,"final Clalfa")
write_to_db("finalCLalfa", finalCLalfa)
CLo = -alfazero * finalCLalfa / 57.3
# print(CLo)
write_to_db("CLo", CLo)
Cma = (finalCLalfa / 57.3) * (cma / (clalfa / 57.3))
# print(Cma)
write_to_db("Cma", Cma)
cruiseCL = (CLo + ((initialWeight + finalWeight) /
(altitudeDensity * S * cruiseSpeed**2)) +
((finalCLalfa / 57.3) * alfazero))
print(cruiseCL, "cruiseCl")
write_to_db("cruiseCL", cruiseCL)
##################################################################################
import sys
sys.path.append("../")
from CORE.API.db_API import write_to_db, read_from_db
import numpy as np # type: ignore
import matplotlib.pylab as plt # type: ignore
a = np.arange(50)
ws = np.arange(10, 35, 0.01)
cdmin: float = 0.025
write_to_db("cdMin", cdmin)
do = read_from_db("rhoSL")
dalt = read_from_db("altitudeDensity") # AAAAA
k = read_from_db("k")
# v = read_from_db('cruiseSpeed') * 1.688
v: float = 140 * 1.688 # AAAAA
qcruise = 0.5 * dalt * v**2 # dynamic pressure at cruise
qtakeoff = 0.5 * do * v**2 # dynamic pressure at take-off
turnangle = 40 # turn angle
loadfactor = 1 / (np.cos(turnangle)) # loadfactor
twturn = (qcruise * ((cdmin / ws) + (k * (loadfactor / qcruise)**2) * ws) *
(v * 5850 / (0.8 * 550 * 0.6604)))
payload = (payloadPax * pax) + paxTotal # total payload
crewTotal = crew * crewWeight
## also in input main file, decide what to import and from which file
oswaldeff = (
1.78 * (1 - 0.045 * AR ** 0.68) - 0.64
) # e is oswalds span efficiency factor 0.7-0.95 #
k = 1 / (np.pi * oswaldeff * AR) # k is the induced drag factor k=1/(pi*e*AR) #
cdo: float = 0.025 # zerolift drag coefficient cdo = 0.022 - 0.028#
ldmax1 = 2 * np.sqrt(k * cdo)
ldMax = ldmax1 ** (-1)
write_to_db("cdo", cdo)
write_to_db("ldMax", ldMax)
write_to_db("k", k)
Vc: float = 140.0 # AAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAA
cbhp: float = 0.4
fuelAllowance: float = 5.0 # in %
write_to_db("cbhp", cbhp)
w4w3 = math.exp((-Range * 3280.8399 * cbhp / 3600) / (propEff * ldMax * 550))
w2w1: float = 0.98
w3w2: float = 0.97
w5w4: float = 0.99
w6w5: float = 0.997
w6w1 = w2w1 * w3w2 * w4w3 * w5w4 * w6w5
propEff = read_from_db("propEff")
cruiseSpeed = (
read_from_db("maxSpeed") / 1.2
) # CALCULATE THIS, MAYBE USE MAXSPEED/1.2 THEN LATER OPTIMIZE IN PERFORMANCE
Range = read_from_db("Range") * 3280.84 # ft
cdMin = 0.02541 # CALCULATE THIS SOMEHOW CZ WE HAVE IMPORTED IT INTO THE VALUES FILES
endurance = 5.172 # hours
### check spelling from previous modules
ldMax = read_from_db("ldMax")
rhoSL = read_from_db("rhoSL")
altitudeDensity = read_from_db("altitudeDensity")
write_to_db("cdMin", cdMin)
write_to_db("cbhp", cbhp)
write_to_db("cruiseSpeed", cruiseSpeed)
wing = wapi.aspectRatio(
initialWeight,
finalWeight,
cruiseSpeed,
S,
rhoSL,
altitude,
cbhp,
propEff,
Range,
cdMin,
