GOE 342 AIRFOIL (goe342-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 342 AIRFOIL (goe342-il) Reynolds number: 200,000 Max Cl/Cd: 99.45 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe342-il-200000.txt Download as CSV file: xf-goe342-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 342 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2994 0.11231 0.10879 -0.0319 1.0000 0.0240
-8.500 -0.3075 0.11178 0.10834 -0.0308 1.0000 0.0241
-7.500 -0.3358 0.10363 0.10047 -0.0181 1.0000 0.0245
-7.250 -0.3290 0.10032 0.09717 -0.0181 0.9983 0.0248
-7.000 -0.3056 0.09600 0.09283 -0.0231 0.9946 0.0253
-6.750 -0.2807 0.09189 0.08871 -0.0290 0.9892 0.0260
-6.500 -0.2526 0.08776 0.08456 -0.0359 0.9848 0.0270
-6.250 -0.2244 0.08386 0.08063 -0.0430 0.9789 0.0282
-6.000 -0.1547 0.08057 0.07720 -0.0675 0.9716 0.0297
-5.750 -0.1339 0.07538 0.07201 -0.0706 0.9673 0.0301
-5.500 -0.1221 0.07129 0.06794 -0.0692 0.9628 0.0306
-5.250 -0.0949 0.06750 0.06411 -0.0732 0.9594 0.0315
-5.000 -0.0577 0.06360 0.06017 -0.0805 0.9571 0.0329
-4.750 -0.0222 0.06018 0.05668 -0.0875 0.9513 0.0350
-4.500 0.0545 0.05580 0.05202 -0.1064 0.9468 0.0373
-4.250 0.0731 0.05178 0.04804 -0.1070 0.9442 0.0382
-4.000 0.1070 0.04850 0.04471 -0.1113 0.9420 0.0398
-3.750 0.1397 0.04577 0.04190 -0.1154 0.9353 0.0420
-3.500 0.2087 0.04219 0.03791 -0.1275 0.9314 0.0467
-3.250 0.2349 0.03881 0.03457 -0.1295 0.9280 0.0481
-3.000 0.2643 0.03660 0.03231 -0.1317 0.9223 0.0505
-2.750 0.3204 0.03572 0.03088 -0.1375 0.9172 0.0572
-2.500 0.3459 0.03149 0.02677 -0.1398 0.9135 0.0593
-2.250 0.3735 0.02985 0.02510 -0.1410 0.9081 0.0637
-2.000 0.4106 0.02792 0.02290 -0.1435 0.9022 0.0720
-1.750 0.4410 0.02639 0.02132 -0.1447 0.8979 0.0778
-1.500 0.4727 0.02489 0.01963 -0.1460 0.8917 0.0865
-1.250 0.5050 0.02369 0.01820 -0.1470 0.8857 0.0986
-1.000 0.5353 0.02252 0.01687 -0.1475 0.8790 0.1119
-0.750 0.5628 0.02127 0.01554 -0.1476 0.8701 0.1265
-0.500 0.5895 0.02014 0.01441 -0.1477 0.8625 0.1447
-0.250 0.6166 0.01929 0.01354 -0.1480 0.8561 0.1764
0.000 0.6442 0.01834 0.01257 -0.1483 0.8512 0.2188
0.750 0.7456 0.01525 0.00822 -0.1470 0.8311 0.0806
1.000 0.7747 0.01439 0.00716 -0.1464 0.8240 0.0722
1.250 0.8020 0.01396 0.00669 -0.1459 0.8160 0.0715
1.500 0.8298 0.01349 0.00620 -0.1454 0.8084 0.0719
1.750 0.8566 0.01324 0.00597 -0.1448 0.7992 0.0704
2.000 0.8843 0.01290 0.00564 -0.1443 0.7908 0.0699
2.250 0.9112 0.01258 0.00537 -0.1438 0.7794 0.0705
2.500 0.9378 0.01235 0.00514 -0.1431 0.7662 0.0726
2.750 0.9641 0.01221 0.00500 -0.1423 0.7516 0.0772
3.000 0.9905 0.01210 0.00491 -0.1415 0.7359 0.0919
3.250 1.0118 0.01069 0.00494 -0.1399 0.7194 1.0000
3.500 1.0371 0.01074 0.00486 -0.1388 0.6959 1.0000
3.750 1.0616 0.01079 0.00480 -0.1377 0.6630 1.0000
4.000 1.0850 0.01091 0.00474 -0.1363 0.6074 1.0000
4.250 1.1050 0.01143 0.00475 -0.1345 0.5317 1.0000
4.500 1.1257 0.01217 0.00510 -0.1330 0.4848 1.0000
4.750 1.1478 0.01282 0.00551 -0.1320 0.4540 1.0000
5.000 1.1707 0.01340 0.00594 -0.1312 0.4301 1.0000
5.250 1.1942 0.01390 0.00635 -0.1304 0.4111 1.0000
5.500 1.2180 0.01438 0.00677 -0.1297 0.3962 1.0000
5.750 1.2417 0.01484 0.00719 -0.1290 0.3818 1.0000
6.000 1.2654 0.01529 0.00765 -0.1283 0.3687 1.0000
6.250 1.2888 0.01576 0.00811 -0.1276 0.3561 1.0000
6.500 1.3119 0.01622 0.00857 -0.1268 0.3429 1.0000
6.750 1.3347 0.01663 0.00903 -0.1260 0.3272 1.0000
7.000 1.3570 0.01700 0.00951 -0.1250 0.3072 1.0000
7.250 1.3779 0.01742 0.00994 -0.1239 0.2784 1.0000
7.500 1.3959 0.01807 0.01039 -0.1224 0.2140 1.0000
7.750 1.4060 0.01971 0.01143 -0.1200 0.1452 1.0000
8.000 1.4195 0.02103 0.01261 -0.1179 0.1235 1.0000
8.250 1.4339 0.02221 0.01379 -0.1160 0.1100 1.0000
8.500 1.4475 0.02341 0.01496 -0.1139 0.0988 1.0000
8.750 1.4635 0.02433 0.01592 -0.1122 0.0871 1.0000
9.000 1.4785 0.02527 0.01688 -0.1104 0.0737 1.0000
9.250 1.4897 0.02654 0.01815 -0.1079 0.0589 1.0000
9.500 1.4922 0.02829 0.01990 -0.1042 0.0492 1.0000
9.750 1.5009 0.02957 0.02127 -0.1014 0.0428 1.0000
10.000 1.5030 0.03148 0.02321 -0.0980 0.0390 1.0000
10.250 1.5114 0.03292 0.02479 -0.0954 0.0360 1.0000
10.500 1.5179 0.03454 0.02648 -0.0929 0.0338 1.0000
10.750 1.5210 0.03669 0.02866 -0.0901 0.0320 1.0000
11.000 1.5270 0.03899 0.03108 -0.0876 0.0307 1.0000
11.250 1.5355 0.04076 0.03305 -0.0854 0.0293 1.0000
11.500 1.5428 0.04260 0.03505 -0.0834 0.0278 1.0000
11.750 1.5487 0.04452 0.03708 -0.0814 0.0265 1.0000
12.000 1.5546 0.04671 0.03938 -0.0795 0.0257 1.0000
12.250 1.5606 0.04936 0.04212 -0.0776 0.0249 1.0000
12.500 1.5674 0.05333 0.04632 -0.0756 0.0242 1.0000
12.750 1.5665 0.05647 0.04974 -0.0734 0.0239 1.0000
13.000 1.5627 0.05978 0.05336 -0.0714 0.0237 1.0000
13.250 1.5557 0.06347 0.05734 -0.0696 0.0236 1.0000
13.500 1.5456 0.06748 0.06165 -0.0681 0.0234 1.0000
13.750 1.5328 0.07185 0.06630 -0.0671 0.0233 1.0000
14.000 1.5178 0.07660 0.07132 -0.0666 0.0232 1.0000
14.250 1.5007 0.08181 0.07680 -0.0666 0.0231 1.0000
14.500 1.4822 0.08745 0.08269 -0.0674 0.0231 1.0000
14.750 1.4623 0.09361 0.08909 -0.0690 0.0231 1.0000
15.000 1.4415 0.10040 0.09611 -0.0715 0.0231 1.0000
15.250 1.4201 0.10795 0.10388 -0.0750 0.0232 1.0000
15.500 1.3986 0.11614 0.11228 -0.0795 0.0234 1.0000
15.750 1.3770 0.12503 0.12136 -0.0849 0.0236 1.0000
16.000 1.3551 0.13462 0.13109 -0.0909 0.0239 1.0000
16.250 1.0817 0.13434 0.13127 -0.0726 0.0270 1.0000
16.500 1.0013 0.15506 0.15217 -0.0857 0.0298 1.0000
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Polar data table (+)
Polar graphs
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