def xfoil():
x = request.args.get('x')
y = request.args.get('y')
Re = float(request.args.get('Re'))
M = float(request.args.get('M'))
Alpha = float(request.args.get('Alpha'))
x = x.split()
y = y.split()
ctrlX = [float(ele) for ele in x]
ctrlY = [float(ele) for ele in y]
#bezierX, bezierY = airfoil(ctrlX, ctrlY, 16)
xf = XFoil()
xf.airfoil = Airfoil(np.array(ctrlX), np.array(ctrlY))
xf.repanel()
xf.Re = Re
xf.M = 0
xf.max_iter = 100
aero = xf.a(Alpha)
xcp, cp = xf.get_cp_distribution()
y = savgol_filter(cp, 5, 2)
for i in range(30):
y = savgol_filter(y, 5, 2)
LD = aero[0] / aero[1]
vol = PolyArea(ctrlX, ctrlY)
return jsonify(result=str(round(aero[0], 3)) + " " +
str(round(aero[1], 3)) + " " + str(round(aero[2], 3)) +
" " + str(round(LD, 2)) + " " + str(round(vol, 3)),
xcp=xcp.tolist(),
cp=y.tolist())
def evaluate(individual):
global code_division
#----------------------------------
#遺伝子にも続いて新翼型を生成
#----------------------------------
#遺伝子をデコード
ratios = decoder(individual, code_division)
#遺伝子に基づき翼型を混合して、新しい翼型を作る
datlist_list = [fc.read_datfile(file) for file in datfiles]
datlist_shaped_list = [fc.shape_dat(datlist) for datlist in datlist_list]
newdat = fc.interpolate_dat(datlist_shaped_list,ratios)
#翼型の形に関する情報を取得する
#foilpara == [最大翼厚、最大翼厚位置、最大キャンバ、最大キャンバ位置、S字の強さ]
foil_para = fc.get_foil_para(newdat)
#新しい翼型をAerofoilオブジェクトに適用
datx = np.array([ax[0] for ax in newdat])
daty = np.array([ax[1] for ax in newdat])
newfoil = Airfoil(x = datx, y = daty)
mt, mta, mc, mca, s = foil_para
#----------------------------------
#翼の形に関する拘束条件
#----------------------------------
penalty = 0
print('===================')
if(mc<0):
print("out of the border")
print("reverse_cmaber")
penalty -= mc
if(mt<0.08):
print("out of the border")
print("too_thin")
penalty += 0.08-mt
if(mt>0.11):
print("out of the border")
print("too_fat")
penalty += mt-0.11
#if(foil_para[4]>0.03):
# print("out of the border")
# print("peacock")
# print('===================')
# return (1.0+(foil_para[4]-0.03),)*NOBJ
if(mta<0.23):
print("out of the border")
print("Atama Dekkachi!")
penalty += 0.23 - mta
if(mta>0.3):
print("out of the border")
print("Oshiri Dekkachi!")
penalty += mta - 0.3
#----------------------------------
#新翼型の解析
#----------------------------------
xf = XFoil()
xf.airfoil = newfoil
#レイノルズ数の設定
xf.Re = 1.5e5
#境界要素法計算時1ステップにおける計算回数
xf.max_iter = 60
#座標整形
xf.repanel(n_nodes = 300)
xf.print = False
#計算結果格納
a, cl, cd, cm, cp = xf.cseq(0.4, 1.1, 0.1)
lr = [l/d for l, d in zip(cl,cd)]
#----------------------------------
#目的値
#----------------------------------
try:
#揚抗比の逆数を最小化
obj1 = 1/lr[1]
#揚抗比のピークを滑らかに(安定性の最大化)
maxlr = max(lr)
maxlr_index = lr.index(maxlr)
obj2 = abs(maxlr - lr[maxlr_index+1])
#下面の反りを最小化(製作再現性の最大化)
obj3 = foil_para[4]
except Exception as e:
obj1,obj2,obj3=[1.0]*NOBJ
traceback.print_exc()
if (np.isnan(obj1) or obj1 > 1):
obj1 = 1
if (np.isnan(obj2) or obj2 > 1):
obj2 = 1
if (np.isnan(obj3) or obj3 > 1):
obj3 = 1
obj1 += penalty
obj2 += penalty
obj3 += penalty
print("individual",individual)
print("evaluate",obj1,obj2,obj3)
print("max_thickness",foil_para[0])
print("at",foil_para[1])
print("max_camber",foil_para[2])
print("at",foil_para[3])
print("S",foil_para[4])
print('===================')
return [obj1, obj2, obj3]
