GOE 195 AIRFOIL (goe195-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 195 AIRFOIL (goe195-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.06 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe195-il-1000000-n5.txt Download as CSV file: xf-goe195-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 195 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3609 0.09082 0.08910 -0.0405 0.9953 0.0119
-9.000 -0.4056 0.02249 0.01959 -0.1285 0.9565 0.0175
-8.750 -0.3786 0.02042 0.01720 -0.1305 0.9512 0.0179
-8.500 -0.3520 0.01865 0.01520 -0.1321 0.9461 0.0182
-8.250 -0.3250 0.01812 0.01460 -0.1324 0.9398 0.0184
-8.000 -0.2977 0.01774 0.01416 -0.1326 0.9332 0.0186
-7.750 -0.2705 0.01732 0.01367 -0.1328 0.9260 0.0189
-7.500 -0.2434 0.01668 0.01292 -0.1330 0.9187 0.0191
-7.250 -0.2162 0.01601 0.01212 -0.1333 0.9110 0.0193
-7.000 -0.1891 0.01534 0.01131 -0.1335 0.9021 0.0197
-6.750 -0.1617 0.01477 0.01061 -0.1337 0.8929 0.0201
-6.500 -0.1344 0.01405 0.00973 -0.1338 0.8823 0.0204
-6.250 -0.1072 0.01334 0.00884 -0.1339 0.8686 0.0208
-6.000 -0.0799 0.01273 0.00805 -0.1339 0.8527 0.0211
-5.750 -0.0527 0.01220 0.00735 -0.1338 0.8344 0.0214
-5.500 -0.0254 0.01183 0.00681 -0.1337 0.8146 0.0217
-5.250 0.0018 0.01161 0.00643 -0.1335 0.7932 0.0220
-5.000 0.0291 0.01137 0.00604 -0.1333 0.7726 0.0222
-4.750 0.0568 0.01111 0.00565 -0.1332 0.7580 0.0223
-4.500 0.0845 0.01034 0.00475 -0.1334 0.7456 0.0227
-4.250 0.1123 0.00995 0.00426 -0.1334 0.7328 0.0230
-4.000 0.1404 0.00965 0.00389 -0.1334 0.7217 0.0232
-3.750 0.1686 0.00940 0.00358 -0.1334 0.7127 0.0235
-3.500 0.1969 0.00918 0.00330 -0.1334 0.7038 0.0237
-3.250 0.2253 0.00897 0.00304 -0.1335 0.6950 0.0239
-3.000 0.2535 0.00880 0.00280 -0.1335 0.6844 0.0242
-2.750 0.2818 0.00864 0.00258 -0.1335 0.6719 0.0245
-2.500 0.3100 0.00852 0.00240 -0.1334 0.6571 0.0249
-2.250 0.3380 0.00844 0.00223 -0.1333 0.6371 0.0254
-2.000 0.3654 0.00843 0.00207 -0.1332 0.6021 0.0258
-1.750 0.3926 0.00846 0.00194 -0.1329 0.5695 0.0262
-1.500 0.4203 0.00846 0.00184 -0.1328 0.5516 0.0266
-1.250 0.4483 0.00844 0.00175 -0.1328 0.5402 0.0270
-1.000 0.4763 0.00843 0.00168 -0.1327 0.5310 0.0273
-0.750 0.5045 0.00840 0.00162 -0.1326 0.5233 0.0276
-0.500 0.5324 0.00841 0.00158 -0.1325 0.5147 0.0278
-0.250 0.5606 0.00837 0.00150 -0.1325 0.5061 0.0285
0.000 0.5885 0.00837 0.00145 -0.1324 0.4980 0.0293
0.250 0.6168 0.00836 0.00142 -0.1324 0.4911 0.0303
0.500 0.6448 0.00837 0.00142 -0.1323 0.4858 0.0318
0.750 0.6730 0.00837 0.00142 -0.1322 0.4814 0.0335
1.250 0.7293 0.00813 0.00144 -0.1323 0.4675 0.1618
1.500 0.7575 0.00804 0.00152 -0.1324 0.4613 0.2236
1.750 0.7852 0.00810 0.00160 -0.1323 0.4517 0.2486
2.000 0.8129 0.00816 0.00166 -0.1322 0.4388 0.2627
2.250 0.8404 0.00825 0.00173 -0.1320 0.4251 0.2734
2.500 0.8678 0.00834 0.00182 -0.1319 0.4115 0.2871
2.750 0.8947 0.00849 0.00192 -0.1317 0.3905 0.2993
3.000 0.9211 0.00869 0.00204 -0.1314 0.3642 0.3133
3.250 0.9471 0.00893 0.00221 -0.1310 0.3368 0.3286
3.500 0.9728 0.00921 0.00240 -0.1307 0.3079 0.3448
4.000 1.0227 0.00983 0.00297 -0.1299 0.2387 0.4813
4.250 1.0482 0.01006 0.00324 -0.1295 0.2142 0.5520
4.500 1.0733 0.01029 0.00353 -0.1291 0.1893 0.6333
5.000 1.1178 0.01055 0.00413 -0.1271 0.1278 1.0000
5.250 1.1425 0.01096 0.00443 -0.1265 0.1094 1.0000
5.500 1.1676 0.01129 0.00471 -0.1261 0.0984 1.0000
5.750 1.1930 0.01158 0.00496 -0.1256 0.0895 1.0000
6.000 1.2180 0.01191 0.00524 -0.1251 0.0806 1.0000
6.250 1.2422 0.01230 0.00556 -0.1245 0.0666 1.0000
6.500 1.2632 0.01305 0.00610 -0.1234 0.0362 1.0000
6.750 1.2876 0.01339 0.00644 -0.1228 0.0320 1.0000
7.000 1.3121 0.01371 0.00677 -0.1223 0.0303 1.0000
7.250 1.3361 0.01407 0.00714 -0.1216 0.0285 1.0000
7.500 1.3596 0.01446 0.00754 -0.1209 0.0265 1.0000
7.750 1.3830 0.01484 0.00794 -0.1202 0.0249 1.0000
8.000 1.4069 0.01516 0.00828 -0.1195 0.0242 1.0000
8.250 1.4303 0.01550 0.00866 -0.1188 0.0230 1.0000
8.500 1.4530 0.01589 0.00906 -0.1180 0.0214 1.0000
8.750 1.4747 0.01635 0.00952 -0.1170 0.0196 1.0000
9.000 1.4969 0.01675 0.00995 -0.1161 0.0186 1.0000
9.250 1.5186 0.01717 0.01038 -0.1152 0.0173 1.0000
9.500 1.5394 0.01763 0.01085 -0.1141 0.0157 1.0000
9.750 1.5596 0.01813 0.01136 -0.1130 0.0143 1.0000
10.000 1.5795 0.01862 0.01188 -0.1117 0.0133 1.0000
10.250 1.5983 0.01916 0.01243 -0.1104 0.0122 1.0000
10.500 1.6158 0.01976 0.01306 -0.1088 0.0112 1.0000
10.750 1.6331 0.02031 0.01366 -0.1072 0.0107 1.0000
11.000 1.6478 0.02089 0.01429 -0.1051 0.0102 1.0000
11.250 1.6612 0.02153 0.01497 -0.1029 0.0096 1.0000
11.500 1.6736 0.02225 0.01573 -0.1006 0.0090 1.0000
11.750 1.6845 0.02309 0.01662 -0.0982 0.0084 1.0000
12.000 1.6963 0.02388 0.01748 -0.0960 0.0081 1.0000
12.250 1.7075 0.02473 0.01839 -0.0939 0.0078 1.0000
12.500 1.7180 0.02567 0.01940 -0.0917 0.0075 1.0000
12.750 1.7274 0.02671 0.02050 -0.0896 0.0073 1.0000
13.000 1.7361 0.02786 0.02171 -0.0875 0.0070 1.0000
13.250 1.7435 0.02913 0.02305 -0.0855 0.0067 1.0000
13.500 1.7498 0.03057 0.02457 -0.0835 0.0065 1.0000
13.750 1.7542 0.03222 0.02630 -0.0815 0.0062 1.0000
14.000 1.7588 0.03395 0.02811 -0.0798 0.0061 1.0000
14.250 1.7639 0.03570 0.02996 -0.0783 0.0060 1.0000
14.500 1.7678 0.03765 0.03199 -0.0769 0.0058 1.0000
14.750 1.7706 0.03979 0.03423 -0.0757 0.0057 1.0000
15.000 1.7725 0.04212 0.03666 -0.0746 0.0056 1.0000
15.250 1.7733 0.04465 0.03929 -0.0737 0.0055 1.0000
15.500 1.7727 0.04741 0.04215 -0.0730 0.0054 1.0000
15.750 1.7713 0.05037 0.04521 -0.0724 0.0052 1.0000
16.000 1.7689 0.05352 0.04846 -0.0721 0.0051 1.0000
16.250 1.7650 0.05698 0.05202 -0.0719 0.0050 1.0000
16.500 1.7599 0.06074 0.05589 -0.0720 0.0049 1.0000
16.750 1.7539 0.06479 0.06004 -0.0724 0.0048 1.0000
17.000 1.7461 0.06920 0.06456 -0.0731 0.0047 1.0000
17.250 1.7368 0.07393 0.06940 -0.0739 0.0046 1.0000
17.500 1.7258 0.07899 0.07458 -0.0750 0.0046 1.0000
17.750 1.7132 0.08440 0.08011 -0.0763 0.0045 1.0000
18.000 1.6989 0.09010 0.08593 -0.0778 0.0044 1.0000
18.250 1.6826 0.09626 0.09222 -0.0796 0.0044 1.0000
18.500 1.6670 0.10244 0.09853 -0.0815 0.0043 1.0000
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Polar data table (+)
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