GOE 650 AIRFOIL (goe650-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 650 AIRFOIL (goe650-il) Reynolds number: 200,000 Max Cl/Cd: 70.47 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe650-il-200000-n5.txt Download as CSV file: xf-goe650-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 650 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.6796 0.07874 0.07390 -0.0736 1.0000 0.0376
-14.000 -0.6926 0.07417 0.06931 -0.0754 1.0000 0.0379
-13.750 -0.7104 0.06915 0.06423 -0.0775 1.0000 0.0381
-13.500 -0.7270 0.06464 0.05967 -0.0792 1.0000 0.0383
-13.250 -0.7454 0.06023 0.05521 -0.0806 1.0000 0.0385
-13.000 -0.7658 0.05602 0.05096 -0.0815 1.0000 0.0386
-12.750 -0.7892 0.05203 0.04692 -0.0818 1.0000 0.0387
-12.500 -0.8176 0.04833 0.04318 -0.0812 1.0000 0.0388
-12.250 -0.8293 0.04414 0.03890 -0.0846 0.9966 0.0390
-12.000 -0.8197 0.03942 0.03402 -0.0925 0.9891 0.0396
-11.750 -0.7982 0.03538 0.02977 -0.1003 0.9835 0.0404
-11.500 -0.7799 0.03293 0.02714 -0.1034 0.9772 0.0411
-11.250 -0.7561 0.03092 0.02494 -0.1064 0.9726 0.0419
-11.000 -0.7337 0.02928 0.02310 -0.1081 0.9674 0.0427
-10.750 -0.7112 0.02780 0.02155 -0.1094 0.9620 0.0435
-10.500 -0.6834 0.02644 0.02012 -0.1115 0.9587 0.0446
-10.250 -0.6613 0.02534 0.01892 -0.1119 0.9532 0.0458
-10.000 -0.6363 0.02429 0.01776 -0.1127 0.9483 0.0471
-9.750 -0.6071 0.02328 0.01660 -0.1141 0.9453 0.0485
-9.250 -0.5566 0.02146 0.01465 -0.1149 0.9356 0.0515
-9.000 -0.5274 0.02065 0.01374 -0.1159 0.9320 0.0540
-8.750 -0.4957 0.01984 0.01286 -0.1173 0.9294 0.0570
-8.500 -0.4622 0.01911 0.01207 -0.1190 0.9274 0.0615
-8.250 -0.4423 0.01857 0.01150 -0.1178 0.9200 0.0661
-8.000 -0.4120 0.01800 0.01089 -0.1186 0.9164 0.0731
-7.750 -0.3791 0.01751 0.01033 -0.1198 0.9137 0.0812
-7.500 -0.3449 0.01709 0.00985 -0.1212 0.9115 0.0896
-7.250 -0.3212 0.01681 0.00955 -0.1204 0.9050 0.0959
-7.000 -0.2911 0.01651 0.00915 -0.1209 0.9005 0.1027
-6.750 -0.2584 0.01621 0.00882 -0.1219 0.8972 0.1089
-6.500 -0.2242 0.01592 0.00841 -0.1231 0.8947 0.1147
-6.250 -0.1995 0.01569 0.00819 -0.1225 0.8888 0.1191
-6.000 -0.1709 0.01547 0.00791 -0.1226 0.8838 0.1242
-5.750 -0.1385 0.01521 0.00757 -0.1234 0.8799 0.1300
-5.500 -0.1043 0.01496 0.00729 -0.1246 0.8762 0.1369
-5.250 -0.0806 0.01484 0.00708 -0.1236 0.8682 0.1423
-5.000 -0.0501 0.01453 0.00680 -0.1240 0.8629 0.1480
-4.750 -0.0175 0.01430 0.00650 -0.1248 0.8582 0.1543
-4.500 0.0069 0.01413 0.00628 -0.1239 0.8501 0.1592
-4.250 0.0372 0.01384 0.00600 -0.1242 0.8447 0.1642
-4.000 0.0665 0.01365 0.00576 -0.1243 0.8396 0.1694
-3.750 0.0920 0.01351 0.00558 -0.1237 0.8332 0.1745
-3.500 0.1209 0.01329 0.00538 -0.1238 0.8281 0.1808
-3.250 0.1516 0.01312 0.00517 -0.1241 0.8238 0.1882
-3.000 0.1759 0.01300 0.00508 -0.1233 0.8173 0.1947
-2.750 0.2039 0.01286 0.00494 -0.1231 0.8120 0.2031
-2.500 0.2347 0.01270 0.00478 -0.1235 0.8076 0.2129
-2.250 0.2593 0.01263 0.00472 -0.1227 0.8008 0.2239
-2.000 0.2866 0.01252 0.00465 -0.1224 0.7952 0.2362
-1.750 0.3167 0.01240 0.00455 -0.1226 0.7907 0.2505
-1.500 0.3417 0.01235 0.00455 -0.1219 0.7838 0.2653
-1.250 0.3693 0.01226 0.00448 -0.1216 0.7764 0.2818
-1.000 0.3968 0.01220 0.00443 -0.1212 0.7683 0.2980
-0.750 0.4235 0.01214 0.00437 -0.1206 0.7586 0.3144
-0.500 0.4497 0.01210 0.00434 -0.1200 0.7484 0.3307
-0.250 0.4777 0.01205 0.00427 -0.1197 0.7382 0.3461
0.000 0.5022 0.01203 0.00430 -0.1187 0.7274 0.3602
0.250 0.5300 0.01202 0.00427 -0.1184 0.7188 0.3748
0.500 0.5545 0.01203 0.00431 -0.1174 0.7083 0.3884
0.750 0.5808 0.01204 0.00432 -0.1168 0.6986 0.4026
1.000 0.6058 0.01204 0.00435 -0.1160 0.6873 0.4159
1.250 0.6303 0.01206 0.00440 -0.1150 0.6755 0.4288
1.500 0.6553 0.01208 0.00442 -0.1142 0.6632 0.4423
1.750 0.6798 0.01211 0.00445 -0.1132 0.6493 0.4568
2.000 0.7032 0.01213 0.00451 -0.1121 0.6335 0.4719
2.250 0.7263 0.01217 0.00456 -0.1108 0.6156 0.4893
2.500 0.7489 0.01223 0.00462 -0.1095 0.5959 0.5082
2.750 0.7710 0.01232 0.00469 -0.1081 0.5751 0.5272
3.000 0.7924 0.01245 0.00478 -0.1066 0.5537 0.5465
3.250 0.8132 0.01261 0.00490 -0.1050 0.5338 0.5677
3.500 0.8335 0.01279 0.00506 -0.1033 0.5145 0.5929
3.750 0.8536 0.01296 0.00524 -0.1016 0.4958 0.6243
4.000 0.8741 0.01310 0.00544 -0.1000 0.4762 0.6682
4.500 0.9408 0.01335 0.00598 -0.1024 0.4220 1.0000
4.750 0.9576 0.01374 0.00622 -0.1003 0.3957 1.0000
5.000 0.9730 0.01418 0.00649 -0.0979 0.3716 1.0000
5.250 0.9887 0.01460 0.00679 -0.0955 0.3512 1.0000
5.500 1.0038 0.01503 0.00710 -0.0931 0.3347 1.0000
5.750 1.0190 0.01546 0.00744 -0.0907 0.3204 1.0000
6.000 1.0350 0.01589 0.00780 -0.0885 0.3075 1.0000
6.250 1.0522 0.01630 0.00816 -0.0866 0.2960 1.0000
6.500 1.0685 0.01675 0.00855 -0.0845 0.2858 1.0000
6.750 1.0861 0.01717 0.00895 -0.0827 0.2757 1.0000
7.000 1.1031 0.01761 0.00936 -0.0809 0.2667 1.0000
7.250 1.1199 0.01808 0.00979 -0.0790 0.2570 1.0000
7.500 1.1372 0.01853 0.01023 -0.0773 0.2484 1.0000
7.750 1.1535 0.01903 0.01071 -0.0754 0.2399 1.0000
8.000 1.1704 0.01952 0.01120 -0.0737 0.2321 1.0000
8.250 1.1861 0.02006 0.01172 -0.0719 0.2234 1.0000
8.500 1.2024 0.02059 0.01226 -0.0701 0.2158 1.0000
8.750 1.2175 0.02118 0.01284 -0.0683 0.2075 1.0000
9.000 1.2330 0.02178 0.01344 -0.0666 0.1998 1.0000
9.250 1.2475 0.02242 0.01407 -0.0648 0.1920 1.0000
9.500 1.2622 0.02309 0.01474 -0.0631 0.1850 1.0000
9.750 1.2766 0.02377 0.01545 -0.0614 0.1779 1.0000
10.000 1.2899 0.02454 0.01621 -0.0596 0.1720 1.0000
10.250 1.3048 0.02523 0.01695 -0.0580 0.1659 1.0000
10.500 1.3169 0.02609 0.01781 -0.0563 0.1602 1.0000
10.750 1.3307 0.02689 0.01865 -0.0547 0.1546 1.0000
11.000 1.3437 0.02774 0.01954 -0.0532 0.1494 1.0000
11.250 1.3544 0.02875 0.02056 -0.0515 0.1450 1.0000
11.500 1.3679 0.02962 0.02151 -0.0500 0.1410 1.0000
11.750 1.3803 0.03058 0.02253 -0.0486 0.1366 1.0000
12.000 1.3897 0.03174 0.02370 -0.0470 0.1320 1.0000
12.250 1.4012 0.03280 0.02483 -0.0457 0.1275 1.0000
12.500 1.4120 0.03393 0.02603 -0.0443 0.1228 1.0000
12.750 1.4201 0.03527 0.02740 -0.0429 0.1189 1.0000
13.000 1.4300 0.03652 0.02873 -0.0416 0.1148 1.0000
13.250 1.4391 0.03785 0.03014 -0.0404 0.1099 1.0000
13.500 1.4442 0.03955 0.03185 -0.0391 0.1053 1.0000
13.750 1.4536 0.04093 0.03334 -0.0381 0.1005 1.0000
14.000 1.4589 0.04270 0.03516 -0.0370 0.0953 1.0000
14.250 1.4648 0.04449 0.03703 -0.0360 0.0899 1.0000
14.500 1.4680 0.04656 0.03915 -0.0351 0.0839 1.0000
14.750 1.4717 0.04865 0.04132 -0.0343 0.0771 1.0000
15.000 1.4722 0.05115 0.04385 -0.0335 0.0692 1.0000
15.250 1.4709 0.05393 0.04666 -0.0330 0.0611 1.0000
15.500 1.4664 0.05716 0.04991 -0.0326 0.0538 1.0000
15.750 1.4604 0.06070 0.05348 -0.0325 0.0489 1.0000
16.000 1.4537 0.06447 0.05732 -0.0326 0.0457 1.0000
16.250 1.4454 0.06861 0.06154 -0.0330 0.0435 1.0000
16.500 1.4382 0.07275 0.06579 -0.0337 0.0420 1.0000
16.750 1.4297 0.07721 0.07037 -0.0345 0.0407 1.0000
17.000 1.4185 0.08221 0.07548 -0.0358 0.0395 1.0000
17.250 1.4063 0.08752 0.08092 -0.0374 0.0387 1.0000
17.750 1.3804 0.09878 0.09243 -0.0413 0.0373 1.0000
18.000 1.3684 0.10445 0.09826 -0.0435 0.0367 1.0000
18.250 1.3554 0.11041 0.10436 -0.0460 0.0361 1.0000
18.500 1.3425 0.11646 0.11053 -0.0486 0.0356 1.0000
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Polar data table (+)
Polar graphs
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