#CLAerothon1 = biwing.CL(Alpha1) # #biwing.Gap = 0.2 #CLAerothon2 = biwing.CL(Alpha1) # #biwing.Gap = 0.3 #CLAerothon3 = biwing.CL(Alpha1) # #biwing.Gap = 0.4 #CLAerothon4 = biwing.CL(Alpha1) Alpha2 = npy.linspace(0, 24, 9) biwing.Stagger = 0.0 biwing.Gap = 0.1 CLAVL1 = biwing.GetAVLCL(Alpha2, 'g0.1', 'BiWing_trade_example/', ExecuteAVL) biwing.Gap = 0.2 CLAVL2 = biwing.GetAVLCL(Alpha2, 'g0.2', 'BiWing_trade_example/', ExecuteAVL) biwing.Gap = 0.3 CLAVL3 = biwing.GetAVLCL(Alpha2, 'g0.3', 'BiWing_trade_example/', ExecuteAVL) biwing.Gap = 0.4 CLAVL4 = biwing.GetAVLCL(Alpha2, 'g0.4', 'BiWing_trade_example/', ExecuteAVL) biwing.Stagger = 1.0 biwing.EndPlate.CEdge = 'LE' CLAVL5 = biwing.GetAVLCL(Alpha2, 's1.0', 'BiWing_trade_example/', ExecuteAVL) biwing.Stagger = -1.0
RunDir = 'biwing_gap_vs_oeff/'
biwing.Stagger = -1.0
##DO NOT specify an Fb of 1 for the end plate!!!
##An Fb of 1 is at the Upper Wing and does not need to be specified
biwing.EndPlate.Fb = [0.2, 0.5, 0.8]
biwing.EndPlate.TR = [1, 1, 1]
biwing.EndPlate.Gam = [0 * ARCDEG, 0 * ARCDEG, 0 * ARCDEG]
biwing.EndPlate.Lam = [0 * ARCDEG, 0 * ARCDEG, 0 * ARCDEG]
biwing.EndPlate.Symmetric = True
biwing.EndPlate.CEdge = 'LE'
biwing.Gap = 0.1
e1 = biwing.GetAVLOswald('AVLBiWing0.1.avl', RunDir, True)
biwing.Draw(1)
biwing.Gap = 0.2
e2 = biwing.GetAVLOswald('AVLBiWing0.2.avl', RunDir, True)
biwing.Draw(2)
biwing.Gap = 0.3
e3 = biwing.GetAVLOswald('AVLBiWing0.3.avl', RunDir, True)
biwing.Draw(3)
biwing.Gap = 0.4
e4 = biwing.GetAVLOswald('AVLBiWing0.4.avl', RunDir, True)
biwing.Draw(4)
from __future__ import division # let 5/2 = 2.5 rather than 2 import numpy as npy import pylab as pyl from scalar.units import FT, SEC, LBF from Aircraft_Models.Reg2009Aircraft_RedBearon.BoxWingAircraft.BiWing import BoxWing BoxWing.Draw2DAirfoilPolars(fig=1) BoxWing.Draw3DWingPolars(fig=2) pyl.show()
import numpy as npy
import pylab as pyl
from scalar.units import ARCDEG
from Aircraft_Models.Reg2009Aircraft_RedBearon.BoxWingAircraft.BiWing import BoxWing as biwing
ExecuteAVL = True
# Define the important parameters to vary
biwing.Gap = 0.2
biwing.Stagger = 0.0
# Find the CL based on the Aerothon and AVL models
Alpha1 = npy.linspace(-5, 20, 26) * ARCDEG
AlFuse = (biwing.AlphaFus(Alpha1)) / (ARCDEG)
Alpha2 = npy.linspace(0, 24, 9)
Incidence = npy.linspace(0, 6, 4) * ARCDEG
clrstr = 'bgrycmk'
ind = 0
legend = []
for i in Incidence:
biwing.LowerWing.i = i
CLAerothon = biwing.CL(Alpha1)
CLAVL = biwing.GetAVLCL(Alpha2, 'i' + str(i), 'BiWing_trade_example/',
ExecuteAVL)
pyl.plot(AlFuse, CLAerothon, clrstr[ind])
pyl.plot(Alpha2, CLAVL, clrstr[ind] + 's')
ind = ind + 1
LHconstraint = 100 * IN #constraint
landinggearH = 10 * IN #landing gear height
gapvals = npy.linspace(.1, .4, 7)
alpha2d = npy.linspace(-5, 20, 26) * ARCDEG
a = alpha2d / (ARCDEG)
#a = BoxWing.AlphaWing(alpha2d) / (ARCDEG)
pyl.figure(1)
clrstr = 'bgrycmk'
ind = 0
labels = []
for g in gapvals:
BoxWing.Gap = g
BoxWing.b = (LHconstraint - landinggearH) / (1 + g)
CL = BoxWing.CL(alpha2d)
CDi = BoxWing.CDi(alpha2d)
CD = BoxWing.CD(alpha2d)
CDp = CD - CDi
print 'Gap = ', g, ' Oswald Efficiency = ', BoxWing.O_eff(
), ' AR = ', BoxWing.AR
pyl.subplot(131)
pyl.plot(a, CL, clrstr[ind])
pyl.subplot(132)
pyl.plot(a, CD, clrstr[ind] + '-')
pyl.plot(a, CDi, clrstr[ind] + '--')
pyl.plot(a, CDp, clrstr[ind] + ':')
pyl.subplot(133)
import numpy as npy
import pylab as pyl
from scalar.units import ARCDEG, FT, SEC, IN
from Aircraft_Models.Reg2009Aircraft_RedBearon.BoxWingAircraft.BiWing import BoxWing as biwing
from Aerocats2008BiWing import BoxWing as biwingAeroCats2008
RunDir = 'biwing_AVLCL/'
#biwing.V_Stall = 30.0*FT/SEC
chord = biwing.MAC().asUnit(IN)
Execute = False
clrstr = 'bgrycmk'
# Find the CL_alpha vs. gap for AVL
gap = npy.linspace(0.1, 0.4, 4)
a = npy.linspace(0, 1, 2)
print
print 'CLalpha for AVL and Aerothon'
pyl.figure(1)
ind = 0
lgnd = []
for g in gap:
biwing.Gap = g
CL = biwing.GetAVLCL(a, 'g' + str(g), RunDir, Execute)
CLalpha = (CL[-1] - CL[0])
print 'gap: ', g, ' CLalpha: ', CLalpha
biwing.LowerWing.FWCF = 1.0 biwing.UpperWing.FWCF = 1.0 # EndPlate biwing.EndPlate.Fb = [0.2,0.5,0.8] biwing.EndPlate.TR = [1,1,1] biwing.EndPlate.Gam = [0*ARCDEG,0*ARCDEG,0*ARCDEG] biwing.EndPlate.Lam = [0*ARCDEG,0*ARCDEG,0*ARCDEG] #biwing.EndPlate.CEdge = 'LE' # Find the CL based on the Aerothon and AVL models Alpha1 = npy.linspace(-5,20,26)*ARCDEG biwing.Gap = 0.1 CLAerothon1 = biwing.CL(Alpha1) biwing.Gap = 0.2 CLAerothon2 = biwing.CL(Alpha1) biwing.Gap = 0.3 CLAerothon3 = biwing.CL(Alpha1) biwing.Gap = 0.4 CLAerothon4 = biwing.CL(Alpha1) CLAerocats2008 = biwingAeroCats2008.CL(Alpha1) Alpha2 = npy.linspace(0,24,9) biwing.Stagger = 0.0
BoxWing.Gap = 0.1 BoxWing.Stagger = 0.0 BoxWing.EndPlate.Fb = [0.2,0.5,0.8] BoxWing.EndPlate.TR = [1,1,1] BoxWing.EndPlate.Gam = [0*ARCDEG,0*ARCDEG,0*ARCDEG] BoxWing.EndPlate.Lam = [0*ARCDEG,0*ARCDEG,0*ARCDEG] #BoxWing.EndPlate.CEdge = 'LE' # Find the CL based on the Aerothon and AVL models Alpha1 = npy.linspace(-5,20,26)*ARCDEG BoxWing.Gap = 0.1 #BoxWing.BWCF = 0.685 CL1 = BoxWing.CL(Alpha1) CD1 = BoxWing.CD(Alpha1) BoxWing.Draw(2) BoxWing.Gap = 0.2 #BoxWing.BWCF = 0.74 CL2 = BoxWing.CL(Alpha1) CD2 = BoxWing.CD(Alpha1) BoxWing.Draw(3) BoxWing.Gap = 0.3 #BoxWing.BWCF = 0.765 CL3 = BoxWing.CL(Alpha1) CD3 = BoxWing.CD(Alpha1) BoxWing.Draw(4)
from __future__ import division # let 5/2 = 2.5 rather than 2
from scalar.units import M, FT, IN, ARCDEG, RAD, LBF, SEC, KG
import numpy as npy
import pylab as pyl
from Aircraft_Models.Reg2009Aircraft_RedBearon.BoxWingAircraft.BiWing import BoxWing
BoxWing.Stagger = 0.0
BoxWing.Gap = 0.2
b = BoxWing.b
c = BoxWing.MAC()
stgvals = npy.linspace(-1,1,5)
gapvals = npy.linspace(.1,.4,7)
#alpha2d = npy.linspace(-5,20,26)*ARCDEG
#a = alpha2d / (ARCDEG)
pyl.figure(1)
clrstr = 'bgrycmk'
ind = 0
labels=[]
for s in stgvals:
CL2_CL3 = []
CL2_CL1 = []
for g in gapvals:
BoxWing.Stagger = s
BoxWing.Gap = g
alpha2d=0*ARCDEG
cl1 = BoxWing.CL(alpha2d)
cl2 = BoxWing.CL2(alpha2d)
cl3 = (BoxWing.UpperWing.CL(alpha2d) + BoxWing.LowerWing.CL(alpha2d))/2