GOE 401 AIRFOIL (goe401-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 401 AIRFOIL (goe401-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.71 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe401-il-1000000.txt Download as CSV file: xf-goe401-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 401 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3298 0.09042 0.08884 -0.0191 1.0000 0.0176
-7.750 -0.3375 0.08787 0.08633 -0.0197 1.0000 0.0180
-7.500 -0.3472 0.08526 0.08376 -0.0202 1.0000 0.0181
-7.250 -0.3231 0.08002 0.07850 -0.0289 0.9977 0.0182
-7.000 -0.2998 0.07368 0.07213 -0.0367 0.9938 0.0184
-6.750 -0.2773 0.07064 0.06908 -0.0395 0.9887 0.0186
-6.500 -0.2540 0.06768 0.06611 -0.0432 0.9794 0.0189
-6.250 -0.2315 0.06448 0.06289 -0.0474 0.9605 0.0192
-6.000 -0.1905 0.06032 0.05867 -0.0561 0.9448 0.0203
-5.250 -0.0587 0.02741 0.02510 -0.0781 0.8183 0.0227
-5.000 -0.0415 0.02548 0.02308 -0.0783 0.8029 0.0230
-4.750 -0.0230 0.02370 0.02122 -0.0787 0.7883 0.0234
-4.500 -0.0031 0.02168 0.01909 -0.0793 0.7743 0.0240
-4.250 0.0184 0.01942 0.01670 -0.0803 0.7610 0.0249
-4.000 0.0482 0.01659 0.01363 -0.0819 0.7501 0.0270
-3.750 0.0715 0.01416 0.01101 -0.0825 0.7389 0.0271
-3.500 0.1012 0.02375 0.02010 -0.0895 0.7524 0.0278
-3.250 0.1235 0.02295 0.01920 -0.0890 0.7378 0.0282
-3.000 0.1465 0.02190 0.01802 -0.0884 0.7239 0.0287
-2.750 0.1700 0.02078 0.01676 -0.0879 0.7100 0.0294
-2.500 0.1939 0.01926 0.01505 -0.0871 0.6956 0.0309
-2.250 0.2162 0.01543 0.01059 -0.0854 0.6829 0.0340
-2.000 0.2395 0.01432 0.00936 -0.0847 0.6665 0.0349
-1.750 0.2642 0.01377 0.00870 -0.0841 0.6485 0.0356
-1.500 0.2889 0.01322 0.00800 -0.0833 0.6271 0.0366
-1.250 0.3135 0.01268 0.00726 -0.0825 0.6026 0.0381
-1.000 0.3375 0.01055 0.00460 -0.0809 0.5767 0.0313
-0.750 0.3619 0.00997 0.00378 -0.0799 0.5445 0.0308
-0.250 0.4112 0.00952 0.00297 -0.0783 0.4841 0.0313
0.000 0.4363 0.00935 0.00268 -0.0776 0.4649 0.0315
0.500 0.4874 0.00904 0.00224 -0.0763 0.4404 0.0318
0.750 0.5131 0.00894 0.00208 -0.0757 0.4311 0.0321
1.000 0.5390 0.00887 0.00198 -0.0752 0.4230 0.0327
1.250 0.5649 0.00881 0.00188 -0.0746 0.4159 0.0330
1.500 0.5910 0.00873 0.00179 -0.0741 0.4092 0.0335
1.750 0.6164 0.00865 0.00165 -0.0734 0.4026 0.0350
2.000 0.6429 0.00860 0.00160 -0.0730 0.3974 0.0366
2.250 0.6690 0.00861 0.00159 -0.0725 0.3912 0.0383
2.500 0.6953 0.00864 0.00161 -0.0721 0.3856 0.0403
2.750 0.7216 0.00860 0.00165 -0.0717 0.3805 0.0653
3.000 0.7471 0.00857 0.00177 -0.0711 0.3747 0.1425
3.250 0.7733 0.00858 0.00185 -0.0707 0.3681 0.1777
3.500 0.7970 0.00831 0.00198 -0.0700 0.3604 0.4075
3.750 0.8751 0.00726 0.00221 -0.0819 0.3516 1.0000
4.000 0.9003 0.00738 0.00229 -0.0812 0.3450 1.0000
4.250 0.9255 0.00750 0.00238 -0.0806 0.3363 1.0000
4.500 0.9503 0.00765 0.00247 -0.0799 0.3274 1.0000
4.750 0.9756 0.00776 0.00258 -0.0793 0.3203 1.0000
5.000 1.0002 0.00792 0.00270 -0.0786 0.3119 1.0000
5.250 1.0254 0.00804 0.00282 -0.0780 0.3042 1.0000
5.500 1.0498 0.00822 0.00295 -0.0773 0.2943 1.0000
5.750 1.0738 0.00843 0.00311 -0.0765 0.2815 1.0000
6.000 1.0975 0.00866 0.00328 -0.0757 0.2666 1.0000
6.250 1.1210 0.00891 0.00347 -0.0749 0.2512 1.0000
6.750 1.1673 0.00946 0.00391 -0.0731 0.2224 1.0000
7.000 1.1898 0.00979 0.00416 -0.0722 0.2038 1.0000
7.250 1.2117 0.01017 0.00445 -0.0711 0.1850 1.0000
7.500 1.2324 0.01065 0.00480 -0.0699 0.1598 1.0000
7.750 1.2473 0.01163 0.00544 -0.0678 0.1056 1.0000
8.000 1.2608 0.01272 0.00625 -0.0655 0.0606 1.0000
8.250 1.2817 0.01315 0.00668 -0.0644 0.0530 1.0000
8.500 1.3027 0.01357 0.00709 -0.0632 0.0475 1.0000
8.750 1.3237 0.01397 0.00750 -0.0621 0.0409 1.0000
9.000 1.3420 0.01459 0.00801 -0.0606 0.0282 1.0000
9.250 1.3601 0.01520 0.00857 -0.0590 0.0206 1.0000
9.500 1.3777 0.01584 0.00920 -0.0574 0.0173 1.0000
9.750 1.3970 0.01630 0.00972 -0.0560 0.0164 1.0000
10.000 1.4148 0.01686 0.01033 -0.0544 0.0153 1.0000
10.250 1.4306 0.01754 0.01105 -0.0526 0.0142 1.0000
10.500 1.4443 0.01832 0.01190 -0.0504 0.0134 1.0000
10.750 1.4605 0.01887 0.01251 -0.0486 0.0130 1.0000
11.000 1.4748 0.01949 0.01320 -0.0466 0.0125 1.0000
11.250 1.4857 0.02012 0.01389 -0.0440 0.0121 1.0000
11.500 1.4946 0.02084 0.01466 -0.0411 0.0115 1.0000
11.750 1.5016 0.02172 0.01560 -0.0382 0.0112 1.0000
12.000 1.5017 0.02306 0.01704 -0.0346 0.0106 1.0000
12.250 1.5011 0.02456 0.01866 -0.0315 0.0104 1.0000
12.500 1.5083 0.02569 0.01987 -0.0295 0.0102 1.0000
12.750 1.5155 0.02692 0.02118 -0.0279 0.0100 1.0000
13.000 1.5195 0.02850 0.02285 -0.0263 0.0098 1.0000
13.250 1.5226 0.03031 0.02476 -0.0250 0.0097 1.0000
13.500 1.5248 0.03236 0.02690 -0.0240 0.0095 1.0000
13.750 1.5273 0.03452 0.02915 -0.0234 0.0092 1.0000
14.000 1.5243 0.03740 0.03214 -0.0230 0.0092 1.0000
14.250 1.5217 0.04042 0.03526 -0.0229 0.0090 1.0000
14.500 1.5205 0.04340 0.03833 -0.0230 0.0088 1.0000
14.750 1.5145 0.04710 0.04214 -0.0235 0.0087 1.0000
15.000 1.5089 0.05086 0.04600 -0.0241 0.0086 1.0000
15.250 1.5016 0.05499 0.05023 -0.0250 0.0085 1.0000
15.500 1.4939 0.05926 0.05459 -0.0260 0.0083 1.0000
15.750 1.4838 0.06394 0.05938 -0.0272 0.0083 1.0000
16.000 1.4685 0.06943 0.06498 -0.0287 0.0082 1.0000
16.250 1.4590 0.07414 0.06978 -0.0300 0.0081 1.0000
16.500 1.4454 0.07945 0.07519 -0.0315 0.0080 1.0000
16.750 1.4253 0.08549 0.08133 -0.0329 0.0078 1.0000
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Polar data table (+)
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