GOE 358 AIRFOIL (goe358-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 358 AIRFOIL (goe358-il) Reynolds number: 200,000 Max Cl/Cd: 79.01 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe358-il-200000.txt Download as CSV file: xf-goe358-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 358 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3353 0.09284 0.08933 -0.0312 1.0000 0.0753
-7.750 -0.3488 0.09111 0.08768 -0.0294 1.0000 0.0776
-7.250 -0.4084 0.08522 0.08203 -0.0362 1.0000 0.0807
-7.000 -0.4076 0.08282 0.07967 -0.0292 1.0000 0.0819
-6.750 -0.3789 0.04783 0.04421 -0.0806 0.9949 0.0696
-6.500 -0.3221 0.03485 0.03033 -0.1014 0.9927 0.0666
-6.250 -0.2708 0.02859 0.02308 -0.1122 0.9899 0.0695
-6.000 -0.2301 0.02624 0.02061 -0.1163 0.9866 0.0723
-5.750 -0.1864 0.02472 0.01886 -0.1205 0.9838 0.0760
-5.500 -0.1446 0.02302 0.01674 -0.1240 0.9794 0.0787
-5.250 -0.1023 0.02161 0.01494 -0.1275 0.9751 0.0813
-5.000 -0.0602 0.01992 0.01315 -0.1309 0.9724 0.0842
-4.750 -0.0192 0.01910 0.01224 -0.1337 0.9683 0.0877
-4.500 0.0202 0.01826 0.01126 -0.1360 0.9619 0.0905
-4.250 0.0665 0.01745 0.01029 -0.1394 0.9579 0.0933
-4.000 0.1074 0.01634 0.00920 -0.1418 0.9509 0.0970
-3.750 0.1515 0.01555 0.00842 -0.1448 0.9453 0.1009
-3.500 0.1969 0.01488 0.00772 -0.1480 0.9422 0.1058
-3.250 0.2306 0.01430 0.00719 -0.1489 0.9335 0.1115
-3.000 0.2702 0.01375 0.00664 -0.1509 0.9283 0.1198
-2.750 0.3044 0.01321 0.00617 -0.1519 0.9199 0.1340
-2.500 0.3412 0.01227 0.00570 -0.1538 0.9129 0.2321
-2.250 0.3720 0.01233 0.00585 -0.1537 0.9023 0.3027
-2.000 0.4054 0.01235 0.00578 -0.1541 0.8938 0.3264
-1.750 0.4344 0.01240 0.00576 -0.1536 0.8809 0.3418
-1.500 0.4630 0.01246 0.00583 -0.1531 0.8675 0.3552
-1.250 0.4917 0.01251 0.00588 -0.1526 0.8541 0.3669
-1.000 0.5204 0.01253 0.00584 -0.1522 0.8401 0.3783
-0.750 0.5489 0.01256 0.00579 -0.1518 0.8254 0.3883
-0.500 0.5767 0.01257 0.00578 -0.1512 0.8099 0.3971
-0.250 0.6047 0.01264 0.00572 -0.1507 0.7937 0.4075
0.000 0.6317 0.01269 0.00578 -0.1500 0.7767 0.4161
0.250 0.6590 0.01276 0.00574 -0.1495 0.7592 0.4256
0.500 0.6859 0.01284 0.00577 -0.1489 0.7413 0.4334
0.750 0.7131 0.01291 0.00573 -0.1483 0.7231 0.4412
1.000 0.7398 0.01297 0.00573 -0.1478 0.7047 0.4471
1.250 0.7668 0.01306 0.00570 -0.1473 0.6857 0.4531
1.500 0.7934 0.01311 0.00567 -0.1467 0.6655 0.4580
1.750 0.8197 0.01317 0.00569 -0.1462 0.6434 0.4631
2.000 0.8459 0.01328 0.00567 -0.1456 0.6205 0.4686
2.250 0.8718 0.01337 0.00567 -0.1449 0.5960 0.4734
2.500 0.8973 0.01353 0.00572 -0.1443 0.5726 0.4788
2.750 0.9232 0.01376 0.00581 -0.1437 0.5514 0.4856
3.000 0.9490 0.01394 0.00595 -0.1431 0.5327 0.4914
3.250 0.9750 0.01418 0.00611 -0.1427 0.5168 0.4981
3.500 1.0013 0.01444 0.00630 -0.1423 0.5037 0.5047
3.750 1.0275 0.01465 0.00652 -0.1418 0.4913 0.5121
4.000 1.0539 0.01487 0.00675 -0.1415 0.4799 0.5206
4.250 1.0802 0.01513 0.00699 -0.1411 0.4702 0.5302
4.500 1.1065 0.01530 0.00724 -0.1407 0.4603 0.5400
4.750 1.1329 0.01554 0.00751 -0.1404 0.4517 0.5513
5.000 1.1589 0.01574 0.00776 -0.1399 0.4426 0.5647
5.250 1.1847 0.01592 0.00805 -0.1395 0.4335 0.5815
5.500 1.2102 0.01609 0.00831 -0.1389 0.4253 0.6056
5.750 1.2352 0.01612 0.00863 -0.1383 0.4173 0.6693
6.000 1.2574 0.01598 0.00881 -0.1369 0.4091 1.0000
6.250 1.2828 0.01627 0.00913 -0.1364 0.3997 1.0000
6.500 1.3077 0.01664 0.00942 -0.1358 0.3905 1.0000
6.750 1.3315 0.01687 0.00973 -0.1349 0.3788 1.0000
7.000 1.3550 0.01715 0.01006 -0.1341 0.3666 1.0000
7.250 1.3779 0.01746 0.01038 -0.1331 0.3539 1.0000
7.500 1.4001 0.01778 0.01072 -0.1320 0.3400 1.0000
7.750 1.4216 0.01810 0.01109 -0.1308 0.3238 1.0000
8.000 1.4424 0.01842 0.01147 -0.1294 0.3031 1.0000
8.250 1.4615 0.01883 0.01187 -0.1279 0.2722 1.0000
8.500 1.4711 0.01995 0.01254 -0.1251 0.1920 1.0000
8.750 1.4742 0.02188 0.01407 -0.1216 0.1481 1.0000
9.000 1.4828 0.02333 0.01537 -0.1187 0.1138 1.0000
9.250 1.4895 0.02476 0.01662 -0.1156 0.0945 1.0000
9.500 1.4938 0.02610 0.01792 -0.1120 0.0843 1.0000
9.750 1.4975 0.02753 0.01938 -0.1085 0.0771 1.0000
10.000 1.4973 0.02928 0.02111 -0.1048 0.0716 1.0000
10.250 1.5005 0.03091 0.02284 -0.1017 0.0670 1.0000
10.500 1.5034 0.03262 0.02461 -0.0988 0.0630 1.0000
10.750 1.4986 0.03509 0.02704 -0.0955 0.0599 1.0000
11.000 1.5045 0.03677 0.02887 -0.0933 0.0571 1.0000
11.250 1.5088 0.03864 0.03082 -0.0912 0.0542 1.0000
11.500 1.5109 0.04079 0.03298 -0.0892 0.0518 1.0000
11.750 1.5125 0.04326 0.03546 -0.0869 0.0496 1.0000
12.000 1.5190 0.04516 0.03752 -0.0853 0.0478 1.0000
12.250 1.5245 0.04719 0.03965 -0.0837 0.0459 1.0000
12.500 1.5297 0.04928 0.04179 -0.0823 0.0442 1.0000
12.750 1.5359 0.05143 0.04390 -0.0808 0.0425 1.0000
13.000 1.5423 0.05372 0.04630 -0.0792 0.0410 1.0000
13.250 1.5467 0.05604 0.04880 -0.0780 0.0398 1.0000
13.500 1.5514 0.05840 0.05132 -0.0767 0.0386 1.0000
13.750 1.5554 0.06086 0.05390 -0.0757 0.0376 1.0000
14.000 1.5591 0.06330 0.05642 -0.0747 0.0366 1.0000
14.250 1.5663 0.06552 0.05864 -0.0736 0.0355 1.0000
14.500 1.5723 0.06837 0.06160 -0.0722 0.0345 1.0000
14.750 1.5662 0.07190 0.06538 -0.0718 0.0339 1.0000
15.000 1.5605 0.07560 0.06932 -0.0715 0.0333 1.0000
15.250 1.5546 0.07947 0.07342 -0.0714 0.0327 1.0000
15.500 1.5479 0.08359 0.07776 -0.0715 0.0323 1.0000
15.750 1.5400 0.08795 0.08234 -0.0719 0.0319 1.0000
16.000 1.5310 0.09259 0.08717 -0.0727 0.0315 1.0000
16.250 1.5207 0.09756 0.09235 -0.0739 0.0312 1.0000
16.500 1.5091 0.10288 0.09788 -0.0755 0.0310 1.0000
16.750 1.4967 0.10849 0.10369 -0.0776 0.0307 1.0000
17.000 1.4824 0.11464 0.11004 -0.0804 0.0306 1.0000
17.250 1.4629 0.12209 0.11772 -0.0843 0.0306 1.0000
17.500 1.4346 0.13185 0.12779 -0.0903 0.0308 1.0000
17.750 1.3917 0.14594 0.14226 -0.1001 0.0314 1.0000
18.000 1.3408 0.16381 0.16047 -0.1133 0.0325 1.0000
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