#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
Beispiel #5
0
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)
Beispiel #6
0
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)
Beispiel #9
0
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