GOE 195 AIRFOIL (goe195-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 195 AIRFOIL (goe195-il) Reynolds number: 500,000 Max Cl/Cd: 109.07 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe195-il-500000-n5.txt Download as CSV file: xf-goe195-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3527 0.10983 0.10738 -0.0309 1.0000 0.0129
-10.000 -0.3500 0.10635 0.10392 -0.0320 1.0000 0.0134
-9.750 -0.3598 0.09989 0.09748 -0.0344 1.0000 0.0145
-9.500 -0.3543 0.09804 0.09565 -0.0343 1.0000 0.0147
-9.250 -0.3505 0.09606 0.09370 -0.0341 1.0000 0.0148
-9.000 -0.3486 0.09391 0.09157 -0.0339 0.9999 0.0150
-8.750 -0.3354 0.09041 0.08807 -0.0373 0.9971 0.0154
-8.500 -0.3224 0.08646 0.08411 -0.0415 0.9940 0.0159
-8.250 -0.3115 0.08202 0.07968 -0.0460 0.9890 0.0165
-8.000 -0.3098 0.07158 0.06924 -0.0576 0.9793 0.0181
-7.750 -0.2880 0.06839 0.06603 -0.0629 0.9747 0.0184
-7.500 -0.2682 0.06525 0.06288 -0.0676 0.9676 0.0187
-7.250 -0.2237 0.02901 0.02582 -0.1222 0.9520 0.0215
-7.000 -0.1895 0.02368 0.01968 -0.1293 0.9468 0.0222
-6.750 -0.1632 0.02119 0.01693 -0.1312 0.9399 0.0228
-6.500 -0.1345 0.02008 0.01570 -0.1322 0.9342 0.0233
-6.250 -0.1070 0.01902 0.01449 -0.1329 0.9272 0.0236
-6.000 -0.0788 0.01789 0.01318 -0.1335 0.9197 0.0240
-5.750 -0.0508 0.01683 0.01192 -0.1340 0.9120 0.0244
-5.500 -0.0227 0.01585 0.01075 -0.1343 0.9038 0.0248
-5.250 0.0053 0.01502 0.00973 -0.1345 0.8945 0.0253
-5.000 0.0332 0.01435 0.00889 -0.1346 0.8832 0.0259
-4.750 0.0610 0.01368 0.00803 -0.1346 0.8695 0.0263
-4.500 0.0888 0.01307 0.00726 -0.1345 0.8555 0.0267
-4.250 0.1164 0.01256 0.00659 -0.1344 0.8398 0.0269
-4.000 0.1440 0.01213 0.00601 -0.1342 0.8224 0.0272
-3.750 0.1716 0.01176 0.00550 -0.1340 0.8058 0.0274
-3.500 0.1991 0.01145 0.00505 -0.1338 0.7893 0.0276
-3.250 0.2266 0.01118 0.00465 -0.1336 0.7735 0.0278
-3.000 0.2542 0.01062 0.00398 -0.1336 0.7594 0.0283
-2.750 0.2819 0.01024 0.00353 -0.1335 0.7471 0.0290
-2.500 0.3098 0.01000 0.00321 -0.1334 0.7354 0.0296
-2.250 0.3378 0.00979 0.00294 -0.1334 0.7240 0.0300
-2.000 0.3658 0.00963 0.00271 -0.1333 0.7125 0.0304
-1.750 0.3937 0.00949 0.00250 -0.1332 0.7007 0.0310
-1.500 0.4218 0.00937 0.00233 -0.1331 0.6883 0.0315
-1.250 0.4498 0.00928 0.00217 -0.1330 0.6743 0.0322
-1.000 0.4775 0.00922 0.00204 -0.1328 0.6576 0.0328
-0.750 0.5050 0.00919 0.00192 -0.1326 0.6373 0.0335
-0.500 0.5322 0.00922 0.00183 -0.1323 0.6111 0.0341
-0.250 0.5590 0.00929 0.00177 -0.1320 0.5856 0.0350
0.000 0.5860 0.00935 0.00171 -0.1317 0.5672 0.0374
0.250 0.6131 0.00942 0.00170 -0.1315 0.5518 0.0401
0.750 0.6677 0.00920 0.00180 -0.1314 0.5252 0.2082
1.000 0.6948 0.00929 0.00191 -0.1312 0.5156 0.2412
1.250 0.7226 0.00933 0.00199 -0.1311 0.5100 0.2608
1.500 0.7502 0.00940 0.00208 -0.1309 0.5041 0.2778
1.750 0.7776 0.00947 0.00218 -0.1308 0.4970 0.2954
2.000 0.8051 0.00953 0.00227 -0.1306 0.4889 0.3088
2.250 0.8324 0.00961 0.00236 -0.1304 0.4822 0.3223
2.500 0.8600 0.00963 0.00247 -0.1303 0.4741 0.3454
2.750 0.8872 0.00966 0.00258 -0.1302 0.4648 0.3787
3.000 0.9142 0.00965 0.00274 -0.1300 0.4520 0.4643
3.250 0.9410 0.00965 0.00290 -0.1298 0.4369 0.5480
3.500 0.9677 0.00962 0.00304 -0.1296 0.4231 0.6298
4.000 1.0165 0.00932 0.00326 -0.1279 0.3883 1.0000
4.250 1.0416 0.00966 0.00345 -0.1274 0.3565 1.0000
4.500 1.0656 0.01012 0.00371 -0.1268 0.3190 1.0000
4.750 1.0885 0.01072 0.00406 -0.1260 0.2745 1.0000
5.000 1.1123 0.01122 0.00440 -0.1253 0.2430 1.0000
5.250 1.1367 0.01164 0.00471 -0.1248 0.2214 1.0000
5.500 1.1610 0.01205 0.00503 -0.1242 0.2003 1.0000
5.750 1.1848 0.01251 0.00538 -0.1235 0.1759 1.0000
6.000 1.2069 0.01315 0.00582 -0.1227 0.1395 1.0000
6.250 1.2293 0.01374 0.00627 -0.1218 0.1158 1.0000
6.500 1.2526 0.01420 0.00670 -0.1211 0.1029 1.0000
6.750 1.2755 0.01469 0.00712 -0.1203 0.0900 1.0000
7.000 1.2982 0.01517 0.00756 -0.1195 0.0771 1.0000
7.250 1.3170 0.01605 0.00820 -0.1181 0.0439 1.0000
7.500 1.3381 0.01666 0.00879 -0.1171 0.0367 1.0000
7.750 1.3594 0.01721 0.00935 -0.1160 0.0328 1.0000
8.000 1.3814 0.01767 0.00986 -0.1151 0.0310 1.0000
8.250 1.4027 0.01817 0.01042 -0.1140 0.0293 1.0000
8.500 1.4228 0.01876 0.01105 -0.1128 0.0273 1.0000
8.750 1.4411 0.01948 0.01182 -0.1113 0.0252 1.0000
9.000 1.4616 0.01996 0.01235 -0.1102 0.0242 1.0000
9.250 1.4810 0.02050 0.01295 -0.1089 0.0228 1.0000
9.500 1.4993 0.02109 0.01360 -0.1075 0.0212 1.0000
9.750 1.5154 0.02181 0.01435 -0.1057 0.0197 1.0000
10.000 1.5303 0.02247 0.01507 -0.1037 0.0186 1.0000
10.250 1.5446 0.02312 0.01579 -0.1016 0.0176 1.0000
10.500 1.5580 0.02384 0.01656 -0.0995 0.0165 1.0000
10.750 1.5704 0.02464 0.01740 -0.0973 0.0155 1.0000
11.000 1.5803 0.02562 0.01843 -0.0949 0.0146 1.0000
11.250 1.5917 0.02652 0.01942 -0.0928 0.0139 1.0000
11.500 1.6022 0.02751 0.02050 -0.0907 0.0132 1.0000
11.750 1.6116 0.02861 0.02167 -0.0886 0.0125 1.0000
12.000 1.6199 0.02985 0.02297 -0.0866 0.0120 1.0000
12.250 1.6258 0.03132 0.02451 -0.0845 0.0114 1.0000
12.500 1.6304 0.03298 0.02627 -0.0824 0.0110 1.0000
12.750 1.6359 0.03462 0.02803 -0.0806 0.0107 1.0000
13.000 1.6405 0.03643 0.02995 -0.0790 0.0104 1.0000
13.250 1.6441 0.03842 0.03205 -0.0775 0.0100 1.0000
13.500 1.6472 0.04055 0.03428 -0.0762 0.0097 1.0000
13.750 1.6498 0.04282 0.03666 -0.0752 0.0094 1.0000
14.000 1.6511 0.04534 0.03928 -0.0743 0.0091 1.0000
14.250 1.6504 0.04814 0.04218 -0.0735 0.0088 1.0000
14.500 1.6473 0.05136 0.04551 -0.0730 0.0086 1.0000
14.750 1.6405 0.05512 0.04939 -0.0726 0.0084 1.0000
15.000 1.6373 0.05857 0.05297 -0.0725 0.0082 1.0000
15.250 1.6331 0.06228 0.05682 -0.0727 0.0081 1.0000
15.500 1.6277 0.06631 0.06098 -0.0730 0.0079 1.0000
15.750 1.6212 0.07060 0.06541 -0.0737 0.0078 1.0000
16.000 1.6137 0.07515 0.07010 -0.0745 0.0077 1.0000
16.250 1.6056 0.07988 0.07497 -0.0755 0.0076 1.0000
16.500 1.5964 0.08484 0.08005 -0.0766 0.0075 1.0000
16.750 1.5864 0.08997 0.08531 -0.0780 0.0074 1.0000
17.000 1.5758 0.09531 0.09078 -0.0795 0.0073 1.0000
17.250 1.5649 0.10082 0.09642 -0.0812 0.0072 1.0000
17.500 1.5535 0.10649 0.10222 -0.0831 0.0071 1.0000
17.750 1.5418 0.11231 0.10817 -0.0852 0.0070 1.0000
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