GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.79 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe346-il-1000000.txt Download as CSV file: xf-goe346-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4206 0.09493 0.09330 -0.0113 1.0000 0.0132
-8.000 -0.4145 0.09186 0.09025 -0.0130 1.0000 0.0141
-7.750 -0.4097 0.08826 0.08668 -0.0171 1.0000 0.0147
-7.500 -0.3994 0.08408 0.08250 -0.0228 1.0000 0.0148
-7.250 -0.3891 0.07999 0.07841 -0.0275 1.0000 0.0148
-7.000 -0.3815 0.07645 0.07487 -0.0301 1.0000 0.0148
-6.750 -0.3730 0.07171 0.07014 -0.0322 0.9988 0.0150
-6.500 -0.3504 0.06833 0.06674 -0.0358 0.9966 0.0153
-6.250 -0.3226 0.06484 0.06322 -0.0410 0.9945 0.0156
-6.000 -0.2932 0.06132 0.05965 -0.0465 0.9910 0.0165
-5.750 -0.2438 0.05559 0.05375 -0.0576 0.9864 0.0184
-5.500 -0.2089 0.05091 0.04895 -0.0633 0.9815 0.0185
-5.250 -0.1777 0.04659 0.04451 -0.0673 0.9738 0.0186
-4.500 -0.1102 0.03821 0.03593 -0.0719 0.9464 0.0203
-4.250 -0.0829 0.03580 0.03339 -0.0730 0.9381 0.0218
-4.000 -0.0472 0.03332 0.03065 -0.0739 0.9300 0.0229
-3.750 -0.0196 0.03072 0.02786 -0.0744 0.9223 0.0230
-3.500 0.0053 0.02565 0.02249 -0.0755 0.9147 0.0235
-3.250 0.0299 0.02413 0.02089 -0.0758 0.9074 0.0239
-3.000 0.0553 0.02284 0.01950 -0.0760 0.9000 0.0243
-2.750 0.0818 0.02156 0.01811 -0.0762 0.8928 0.0248
-2.500 0.1088 0.02026 0.01668 -0.0762 0.8850 0.0257
-2.250 0.1390 0.01974 0.01597 -0.0755 0.8761 0.0285
-2.000 0.1671 0.01873 0.01475 -0.0751 0.8660 0.0288
-1.750 0.1948 0.01740 0.01320 -0.0749 0.8544 0.0289
-1.500 0.2223 0.01620 0.01179 -0.0747 0.8404 0.0289
-1.250 0.1182 0.04121 0.03920 -0.0320 0.8514 0.0268
1.000 0.4983 0.00844 0.00279 -0.0737 0.6910 0.0345
1.250 0.5259 0.00814 0.00244 -0.0736 0.6741 0.0343
1.500 0.5532 0.00795 0.00216 -0.0734 0.6470 0.0344
1.750 0.5797 0.00787 0.00191 -0.0731 0.6008 0.0340
2.000 0.6059 0.00797 0.00178 -0.0728 0.5438 0.0346
2.250 0.6323 0.00814 0.00175 -0.0726 0.4948 0.0357
2.500 0.6590 0.00831 0.00177 -0.0725 0.4543 0.0365
2.750 0.6855 0.00848 0.00173 -0.0723 0.4032 0.0374
3.000 0.7115 0.00875 0.00176 -0.0721 0.3486 0.0390
3.250 0.7378 0.00901 0.00187 -0.0719 0.3079 0.0420
3.750 0.7906 0.00950 0.00210 -0.0716 0.2404 0.0569
4.000 0.8124 0.00806 0.00242 -0.0710 0.2088 1.0000
4.250 0.8388 0.00836 0.00259 -0.0708 0.1859 1.0000
4.500 0.8652 0.00864 0.00278 -0.0706 0.1651 1.0000
4.750 0.8911 0.00899 0.00299 -0.0704 0.1385 1.0000
5.000 0.9141 0.00984 0.00343 -0.0698 0.0679 1.0000
5.250 0.9384 0.01046 0.00386 -0.0694 0.0371 1.0000
5.500 0.9647 0.01074 0.00416 -0.0691 0.0340 1.0000
5.750 0.9907 0.01103 0.00448 -0.0688 0.0324 1.0000
6.000 1.0164 0.01139 0.00485 -0.0685 0.0304 1.0000
6.250 1.0414 0.01185 0.00535 -0.0681 0.0277 1.0000
6.500 1.0661 0.01235 0.00591 -0.0676 0.0260 1.0000
6.750 1.0918 0.01265 0.00623 -0.0673 0.0252 1.0000
7.000 1.1170 0.01299 0.00661 -0.0669 0.0238 1.0000
7.250 1.1420 0.01337 0.00699 -0.0666 0.0223 1.0000
7.500 1.1655 0.01397 0.00763 -0.0660 0.0205 1.0000
7.750 1.1879 0.01470 0.00844 -0.0652 0.0193 1.0000
8.000 1.2130 0.01500 0.00876 -0.0648 0.0185 1.0000
8.250 1.2375 0.01536 0.00915 -0.0644 0.0174 1.0000
8.500 1.2621 0.01567 0.00947 -0.0641 0.0163 1.0000
8.750 1.2840 0.01636 0.01018 -0.0633 0.0151 1.0000
9.000 1.3050 0.01715 0.01105 -0.0623 0.0144 1.0000
9.250 1.3283 0.01759 0.01154 -0.0618 0.0138 1.0000
9.500 1.3509 0.01808 0.01209 -0.0611 0.0131 1.0000
9.750 1.3734 0.01857 0.01261 -0.0604 0.0125 1.0000
10.000 1.3952 0.01910 0.01317 -0.0597 0.0119 1.0000
10.250 1.4102 0.02042 0.01457 -0.0580 0.0111 1.0000
10.500 1.4289 0.02123 0.01548 -0.0568 0.0107 1.0000
10.750 1.4492 0.02182 0.01615 -0.0559 0.0103 1.0000
11.000 1.4675 0.02260 0.01701 -0.0547 0.0099 1.0000
11.250 1.4851 0.02338 0.01787 -0.0534 0.0096 1.0000
11.500 1.5021 0.02414 0.01871 -0.0521 0.0092 1.0000
11.750 1.5183 0.02493 0.01955 -0.0507 0.0089 1.0000
12.000 1.5316 0.02590 0.02060 -0.0489 0.0086 1.0000
12.250 1.5353 0.02737 0.02219 -0.0457 0.0083 1.0000
12.500 1.5232 0.03008 0.02512 -0.0407 0.0080 1.0000
12.750 1.5274 0.03156 0.02673 -0.0383 0.0079 1.0000
13.000 1.5327 0.03301 0.02829 -0.0362 0.0078 1.0000
13.250 1.5363 0.03469 0.03011 -0.0343 0.0077 1.0000
13.500 1.5376 0.03669 0.03225 -0.0325 0.0076 1.0000
13.750 1.5375 0.03895 0.03464 -0.0310 0.0074 1.0000
14.000 1.5362 0.04148 0.03732 -0.0298 0.0073 1.0000
14.250 1.5338 0.04427 0.04025 -0.0290 0.0072 1.0000
14.500 1.5309 0.04732 0.04345 -0.0287 0.0070 1.0000
14.750 1.5254 0.05089 0.04716 -0.0288 0.0069 1.0000
15.000 1.5192 0.05478 0.05119 -0.0295 0.0068 1.0000
15.250 1.5107 0.05925 0.05580 -0.0306 0.0068 1.0000
15.500 1.5009 0.06417 0.06086 -0.0323 0.0067 1.0000
15.750 1.4883 0.06985 0.06669 -0.0346 0.0066 1.0000
16.000 1.4755 0.07590 0.07287 -0.0374 0.0066 1.0000
16.250 1.4552 0.08352 0.08066 -0.0411 0.0066 1.0000
16.500 1.4328 0.09193 0.08923 -0.0453 0.0066 1.0000
16.750 1.4095 0.10077 0.09822 -0.0499 0.0066 1.0000
17.000 1.3797 0.11122 0.10885 -0.0553 0.0066 1.0000
17.250 1.3503 0.12186 0.11965 -0.0609 0.0067 1.0000
17.500 1.3165 0.13388 0.13184 -0.0674 0.0068 1.0000
17.750 1.2797 0.14739 0.14551 -0.0750 0.0069 1.0000
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Polar data table (+)
Polar graphs
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