GOE 195 AIRFOIL (goe195-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 195 AIRFOIL (goe195-il) Reynolds number: 200,000 Max Cl/Cd: 84.03 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe195-il-200000-n5.txt Download as CSV file: xf-goe195-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2561 0.10262 0.09918 -0.0352 1.0000 0.0342
-9.500 -0.2650 0.09977 0.09638 -0.0360 1.0000 0.0346
-9.250 -0.2710 0.09683 0.09347 -0.0361 1.0000 0.0347
-9.000 -0.2770 0.09394 0.09063 -0.0358 1.0000 0.0348
-8.750 -0.2680 0.08999 0.08670 -0.0346 0.9992 0.0356
-8.500 -0.2517 0.08654 0.08325 -0.0357 0.9969 0.0365
-8.250 -0.2386 0.08270 0.07939 -0.0381 0.9944 0.0374
-8.000 -0.2282 0.07879 0.07548 -0.0407 0.9906 0.0386
-7.750 -0.2181 0.07454 0.07123 -0.0440 0.9868 0.0399
-7.500 -0.2227 0.06874 0.06545 -0.0534 0.9773 0.0435
-7.250 -0.2108 0.06322 0.05992 -0.0598 0.9713 0.0437
-7.000 -0.1980 0.05953 0.05625 -0.0583 0.9675 0.0450
-6.750 -0.2590 0.06804 0.06451 -0.0625 0.9756 0.0343
-6.500 -0.2363 0.06387 0.06031 -0.0675 0.9701 0.0335
-6.250 -0.2054 0.05759 0.05396 -0.0775 0.9645 0.0330
-6.000 -0.1530 0.04036 0.03634 -0.1041 0.9567 0.0334
-5.750 -0.1050 0.02978 0.02483 -0.1195 0.9514 0.0333
-5.500 -0.0657 0.02591 0.02034 -0.1248 0.9481 0.0337
-5.250 -0.0354 0.02413 0.01808 -0.1264 0.9406 0.0346
-5.000 -0.0013 0.02200 0.01553 -0.1287 0.9358 0.0351
-4.750 0.0313 0.02021 0.01343 -0.1302 0.9301 0.0353
-4.500 0.0616 0.01880 0.01180 -0.1311 0.9223 0.0357
-4.250 0.0954 0.01760 0.01040 -0.1325 0.9172 0.0361
-4.000 0.1236 0.01670 0.00937 -0.1326 0.9075 0.0365
-3.750 0.1559 0.01588 0.00845 -0.1335 0.9012 0.0373
-3.500 0.1844 0.01527 0.00776 -0.1336 0.8912 0.0385
-3.250 0.2146 0.01465 0.00706 -0.1339 0.8821 0.0393
-3.000 0.2448 0.01405 0.00638 -0.1341 0.8725 0.0397
-2.750 0.2737 0.01355 0.00583 -0.1342 0.8614 0.0402
-2.500 0.3030 0.01311 0.00533 -0.1342 0.8501 0.0408
-2.250 0.3323 0.01273 0.00488 -0.1343 0.8381 0.0415
-2.000 0.3614 0.01242 0.00449 -0.1343 0.8247 0.0422
-1.750 0.3903 0.01217 0.00414 -0.1342 0.8107 0.0430
-1.500 0.4189 0.01197 0.00383 -0.1341 0.7965 0.0441
-1.250 0.4473 0.01174 0.00352 -0.1340 0.7823 0.0471
-1.000 0.4755 0.01161 0.00329 -0.1338 0.7677 0.0501
-0.750 0.5034 0.01153 0.00310 -0.1335 0.7532 0.0531
-0.500 0.5313 0.01140 0.00296 -0.1333 0.7391 0.0640
-0.250 0.5589 0.01098 0.00299 -0.1334 0.7250 0.2067
0.000 0.5862 0.01102 0.00304 -0.1331 0.7106 0.2477
0.250 0.6134 0.01109 0.00308 -0.1327 0.6959 0.2737
0.500 0.6404 0.01115 0.00313 -0.1324 0.6806 0.2969
0.750 0.6673 0.01120 0.00316 -0.1320 0.6644 0.3155
1.000 0.6941 0.01123 0.00321 -0.1317 0.6474 0.3355
1.250 0.7207 0.01125 0.00325 -0.1313 0.6297 0.3577
1.500 0.7467 0.01127 0.00332 -0.1308 0.6094 0.3926
1.750 0.7724 0.01131 0.00342 -0.1303 0.5886 0.4457
2.000 0.7976 0.01132 0.00354 -0.1296 0.5717 0.5305
2.250 0.8228 0.01125 0.00365 -0.1290 0.5603 0.6424
2.500 0.8470 0.01086 0.00369 -0.1278 0.5509 1.0000
2.750 0.8739 0.01108 0.00383 -0.1275 0.5428 1.0000
3.000 0.9004 0.01133 0.00399 -0.1271 0.5332 1.0000
3.250 0.9268 0.01157 0.00418 -0.1267 0.5218 1.0000
3.500 0.9530 0.01182 0.00437 -0.1263 0.5108 1.0000
3.750 0.9792 0.01208 0.00458 -0.1259 0.5011 1.0000
4.000 1.0057 0.01229 0.00480 -0.1256 0.4913 1.0000
4.250 1.0316 0.01253 0.00503 -0.1251 0.4797 1.0000
4.500 1.0572 0.01276 0.00524 -0.1246 0.4654 1.0000
4.750 1.0824 0.01297 0.00547 -0.1240 0.4476 1.0000
5.000 1.1073 0.01321 0.00568 -0.1234 0.4263 1.0000
5.250 1.1319 0.01347 0.00591 -0.1227 0.4040 1.0000
5.500 1.1555 0.01380 0.00617 -0.1219 0.3759 1.0000
5.750 1.1777 0.01426 0.00650 -0.1209 0.3412 1.0000
6.000 1.1990 0.01483 0.00691 -0.1198 0.3071 1.0000
6.250 1.2198 0.01547 0.00740 -0.1187 0.2747 1.0000
6.500 1.2407 0.01611 0.00794 -0.1176 0.2464 1.0000
6.750 1.2617 0.01674 0.00849 -0.1165 0.2233 1.0000
7.000 1.2821 0.01742 0.00907 -0.1154 0.1968 1.0000
7.250 1.3012 0.01820 0.00972 -0.1141 0.1641 1.0000
7.500 1.3190 0.01910 0.01045 -0.1127 0.1333 1.0000
7.750 1.3364 0.01999 0.01123 -0.1112 0.1123 1.0000
8.000 1.3540 0.02084 0.01203 -0.1097 0.0954 1.0000
8.250 1.3716 0.02166 0.01282 -0.1082 0.0767 1.0000
8.500 1.3863 0.02270 0.01372 -0.1063 0.0528 1.0000
8.750 1.3996 0.02379 0.01474 -0.1042 0.0438 1.0000
9.000 1.4131 0.02480 0.01579 -0.1021 0.0395 1.0000
9.250 1.4253 0.02577 0.01686 -0.0998 0.0367 1.0000
9.500 1.4338 0.02692 0.01808 -0.0970 0.0342 1.0000
9.750 1.4400 0.02825 0.01950 -0.0941 0.0321 1.0000
10.000 1.4495 0.02936 0.02075 -0.0917 0.0307 1.0000
10.250 1.4573 0.03063 0.02217 -0.0892 0.0291 1.0000
10.500 1.4633 0.03208 0.02373 -0.0868 0.0276 1.0000
10.750 1.4664 0.03382 0.02555 -0.0843 0.0262 1.0000
11.000 1.4639 0.03611 0.02793 -0.0815 0.0251 1.0000
11.250 1.4705 0.03773 0.02969 -0.0797 0.0243 1.0000
11.500 1.4752 0.03959 0.03170 -0.0779 0.0233 1.0000
11.750 1.4787 0.04163 0.03387 -0.0763 0.0223 1.0000
12.000 1.4817 0.04380 0.03617 -0.0749 0.0213 1.0000
12.250 1.4838 0.04613 0.03860 -0.0737 0.0205 1.0000
12.500 1.4838 0.04875 0.04131 -0.0726 0.0198 1.0000
12.750 1.4807 0.05182 0.04444 -0.0716 0.0192 1.0000
13.000 1.4828 0.05441 0.04722 -0.0707 0.0187 1.0000
13.250 1.4831 0.05726 0.05022 -0.0700 0.0181 1.0000
13.500 1.4827 0.06025 0.05337 -0.0694 0.0176 1.0000
13.750 1.4817 0.06337 0.05663 -0.0689 0.0171 1.0000
14.000 1.4801 0.06662 0.06003 -0.0687 0.0166 1.0000
14.250 1.4782 0.07001 0.06356 -0.0688 0.0161 1.0000
14.500 1.4758 0.07358 0.06724 -0.0690 0.0157 1.0000
14.750 1.4729 0.07730 0.07107 -0.0695 0.0154 1.0000
15.000 1.4690 0.08121 0.07507 -0.0701 0.0150 1.0000
15.250 1.4637 0.08532 0.07926 -0.0707 0.0147 1.0000
15.500 1.4587 0.08967 0.08382 -0.0716 0.0144 1.0000
15.750 1.4527 0.09424 0.08859 -0.0727 0.0141 1.0000
16.000 1.4457 0.09903 0.09357 -0.0739 0.0138 1.0000
16.250 1.4379 0.10408 0.09881 -0.0755 0.0136 1.0000
16.500 1.4292 0.10941 0.10433 -0.0774 0.0134 1.0000
16.750 1.4197 0.11507 0.11017 -0.0797 0.0132 1.0000
17.000 1.4095 0.12102 0.11631 -0.0824 0.0131 1.0000
17.250 1.3986 0.12731 0.12278 -0.0855 0.0129 1.0000
17.500 1.3870 0.13399 0.12964 -0.0890 0.0128 1.0000
17.750 1.3746 0.14114 0.13698 -0.0931 0.0127 1.0000
18.000 1.3612 0.14888 0.14490 -0.0979 0.0127 1.0000
18.250 1.3461 0.15741 0.15362 -0.1033 0.0126 1.0000
18.500 1.3279 0.16729 0.16370 -0.1099 0.0126 1.0000
18.750 1.3030 0.18003 0.17665 -0.1187 0.0128 1.0000
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