GOE 358 AIRFOIL (goe358-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 358 AIRFOIL (goe358-il) Reynolds number: 500,000 Max Cl/Cd: 105.71 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe358-il-500000.txt Download as CSV file: xf-goe358-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3573 0.12560 0.12308 -0.0304 1.0000 0.0313
-11.250 -0.7328 0.05280 0.05011 -0.0644 1.0000 0.0250
-11.000 -0.7604 0.04305 0.04013 -0.0756 1.0000 0.0250
-10.750 -0.7481 0.03447 0.03127 -0.0900 1.0000 0.0256
-10.500 -0.7232 0.03213 0.02889 -0.0943 1.0000 0.0262
-10.250 -0.6953 0.02975 0.02640 -0.0990 1.0000 0.0270
-10.000 -0.6650 0.02698 0.02339 -0.1044 0.9999 0.0280
-9.750 -0.6254 0.02463 0.02065 -0.1103 0.9986 0.0294
-9.500 -0.5896 0.02326 0.01921 -0.1138 0.9971 0.0307
-9.250 -0.5535 0.02313 0.01910 -0.1160 0.9955 0.0317
-9.000 -0.5158 0.02225 0.01805 -0.1191 0.9942 0.0333
-8.750 -0.4795 0.02122 0.01673 -0.1220 0.9923 0.0348
-8.500 -0.4455 0.02020 0.01569 -0.1242 0.9902 0.0363
-8.250 -0.4099 0.02012 0.01561 -0.1261 0.9880 0.0376
-8.000 -0.3729 0.01963 0.01498 -0.1284 0.9862 0.0396
-7.750 -0.3344 0.01926 0.01439 -0.1309 0.9846 0.0411
-7.500 -0.2978 0.01792 0.01305 -0.1336 0.9835 0.0432
-7.250 -0.2634 0.01764 0.01273 -0.1351 0.9805 0.0450
-7.000 -0.2276 0.01715 0.01214 -0.1369 0.9771 0.0470
-6.750 -0.1888 0.01698 0.01181 -0.1390 0.9746 0.0485
-6.500 -0.1512 0.01535 0.01015 -0.1419 0.9731 0.0512
-6.250 -0.1116 0.01483 0.00959 -0.1444 0.9717 0.0532
-6.000 -0.0700 0.01431 0.00900 -0.1472 0.9705 0.0555
-5.750 -0.0379 0.01393 0.00854 -0.1479 0.9644 0.0571
-5.500 -0.0010 0.01294 0.00745 -0.1499 0.9606 0.0589
-5.250 0.0360 0.01211 0.00662 -0.1518 0.9570 0.0612
-5.000 0.0651 0.01163 0.00612 -0.1518 0.9484 0.0628
-4.750 0.0974 0.01120 0.00565 -0.1524 0.9423 0.0648
-4.500 0.1257 0.01085 0.00525 -0.1523 0.9335 0.0664
-4.250 0.1563 0.01049 0.00483 -0.1525 0.9262 0.0676
-4.000 0.1841 0.01025 0.00454 -0.1522 0.9150 0.0685
-3.750 0.2134 0.00968 0.00392 -0.1523 0.9038 0.0713
-3.500 0.2423 0.00936 0.00355 -0.1523 0.8915 0.0735
-3.250 0.2710 0.00912 0.00325 -0.1522 0.8778 0.0758
-3.000 0.2995 0.00894 0.00299 -0.1520 0.8623 0.0782
-2.750 0.3279 0.00881 0.00277 -0.1517 0.8452 0.0807
-2.500 0.3565 0.00861 0.00250 -0.1516 0.8271 0.0869
-2.250 0.3849 0.00846 0.00230 -0.1515 0.8086 0.0979
-2.000 0.4136 0.00805 0.00208 -0.1517 0.7905 0.1755
-1.750 0.4417 0.00788 0.00208 -0.1516 0.7731 0.2648
-1.500 0.4695 0.00797 0.00212 -0.1513 0.7569 0.2913
-1.250 0.4973 0.00808 0.00216 -0.1510 0.7419 0.3075
-1.000 0.5252 0.00819 0.00223 -0.1507 0.7279 0.3192
-0.750 0.5530 0.00831 0.00227 -0.1504 0.7142 0.3286
-0.500 0.5808 0.00843 0.00232 -0.1502 0.7004 0.3361
-0.250 0.6087 0.00853 0.00235 -0.1499 0.6860 0.3427
0.000 0.6365 0.00862 0.00242 -0.1496 0.6709 0.3502
0.250 0.6641 0.00876 0.00247 -0.1493 0.6537 0.3575
0.500 0.6913 0.00886 0.00253 -0.1490 0.6341 0.3642
0.750 0.7185 0.00899 0.00258 -0.1486 0.6108 0.3700
1.000 0.7452 0.00917 0.00264 -0.1481 0.5856 0.3762
1.250 0.7719 0.00934 0.00274 -0.1477 0.5602 0.3823
1.500 0.7983 0.00958 0.00284 -0.1473 0.5365 0.3887
1.750 0.8250 0.00975 0.00295 -0.1469 0.5141 0.3944
2.000 0.8516 0.00995 0.00308 -0.1465 0.4932 0.3994
2.250 0.8781 0.01017 0.00319 -0.1461 0.4738 0.4038
2.500 0.9047 0.01037 0.00331 -0.1457 0.4561 0.4079
2.750 0.9314 0.01053 0.00344 -0.1454 0.4407 0.4121
3.000 0.9583 0.01070 0.00359 -0.1451 0.4278 0.4168
3.250 0.9851 0.01089 0.00373 -0.1448 0.4155 0.4221
3.500 1.0116 0.01107 0.00389 -0.1444 0.4043 0.4272
3.750 1.0384 0.01123 0.00406 -0.1441 0.3952 0.4325
4.000 1.0651 0.01142 0.00423 -0.1438 0.3873 0.4381
4.250 1.0917 0.01157 0.00441 -0.1434 0.3790 0.4436
4.500 1.1182 0.01175 0.00460 -0.1431 0.3725 0.4499
4.750 1.1451 0.01189 0.00478 -0.1428 0.3665 0.4565
5.000 1.1711 0.01210 0.00501 -0.1423 0.3601 0.4638
5.250 1.1979 0.01224 0.00520 -0.1420 0.3533 0.4718
5.500 1.2238 0.01242 0.00541 -0.1416 0.3453 0.4799
5.750 1.2502 0.01258 0.00563 -0.1413 0.3380 0.4891
6.000 1.2757 0.01278 0.00585 -0.1408 0.3286 0.4995
6.250 1.3019 0.01291 0.00607 -0.1404 0.3188 0.5120
6.500 1.3273 0.01311 0.00631 -0.1399 0.3081 0.5285
6.750 1.3523 0.01331 0.00658 -0.1394 0.2953 0.5541
7.000 1.3755 0.01305 0.00688 -0.1386 0.2792 0.8106
7.250 1.3975 0.01322 0.00708 -0.1373 0.2524 1.0000
7.500 1.4132 0.01441 0.00777 -0.1355 0.1766 1.0000
7.750 1.4316 0.01533 0.00852 -0.1340 0.1504 1.0000
8.000 1.4515 0.01606 0.00915 -0.1327 0.1254 1.0000
8.250 1.4673 0.01715 0.00994 -0.1309 0.0853 1.0000
8.500 1.4846 0.01805 0.01073 -0.1292 0.0706 1.0000
8.750 1.5033 0.01875 0.01142 -0.1277 0.0636 1.0000
9.000 1.5211 0.01949 0.01217 -0.1261 0.0575 1.0000
9.250 1.5376 0.02027 0.01295 -0.1243 0.0522 1.0000
9.500 1.5540 0.02100 0.01372 -0.1224 0.0478 1.0000
9.750 1.5690 0.02176 0.01449 -0.1203 0.0438 1.0000
10.000 1.5801 0.02260 0.01537 -0.1176 0.0405 1.0000
10.250 1.5934 0.02329 0.01610 -0.1153 0.0377 1.0000
10.500 1.6005 0.02439 0.01721 -0.1122 0.0351 1.0000
10.750 1.6119 0.02525 0.01815 -0.1098 0.0333 1.0000
11.000 1.6224 0.02619 0.01915 -0.1074 0.0316 1.0000
11.250 1.6295 0.02740 0.02039 -0.1048 0.0301 1.0000
11.500 1.6302 0.02913 0.02218 -0.1016 0.0287 1.0000
11.750 1.6393 0.03032 0.02347 -0.0996 0.0276 1.0000
12.000 1.6463 0.03172 0.02496 -0.0975 0.0265 1.0000
12.250 1.6519 0.03331 0.02662 -0.0955 0.0256 1.0000
12.500 1.6529 0.03539 0.02876 -0.0934 0.0247 1.0000
12.750 1.6457 0.03839 0.03185 -0.0912 0.0239 1.0000
13.000 1.6489 0.04055 0.03412 -0.0898 0.0234 1.0000
13.250 1.6512 0.04291 0.03660 -0.0886 0.0228 1.0000
13.500 1.6521 0.04552 0.03932 -0.0876 0.0223 1.0000
13.750 1.6517 0.04836 0.04226 -0.0868 0.0217 1.0000
14.000 1.6504 0.05140 0.04538 -0.0862 0.0212 1.0000
14.250 1.6477 0.05469 0.04877 -0.0858 0.0208 1.0000
14.500 1.6425 0.05835 0.05251 -0.0855 0.0204 1.0000
14.750 1.6335 0.06255 0.05680 -0.0853 0.0200 1.0000
15.000 1.6222 0.06708 0.06143 -0.0851 0.0196 1.0000
15.250 1.6209 0.07058 0.06505 -0.0853 0.0193 1.0000
15.500 1.6181 0.07432 0.06891 -0.0856 0.0190 1.0000
15.750 1.6147 0.07821 0.07292 -0.0860 0.0186 1.0000
16.000 1.6106 0.08224 0.07707 -0.0866 0.0183 1.0000
16.250 1.6060 0.08636 0.08129 -0.0872 0.0179 1.0000
16.500 1.6014 0.09054 0.08556 -0.0879 0.0176 1.0000
16.750 1.5969 0.09474 0.08986 -0.0888 0.0174 1.0000
17.000 1.5924 0.09898 0.09418 -0.0897 0.0171 1.0000
17.250 1.5878 0.10322 0.09849 -0.0907 0.0168 1.0000
17.500 1.5831 0.10742 0.10276 -0.0917 0.0166 1.0000
17.750 1.5782 0.11150 0.10691 -0.0925 0.0163 1.0000
18.000 1.5723 0.11539 0.11087 -0.0928 0.0160 1.0000
18.250 1.5676 0.12003 0.11565 -0.0945 0.0158 1.0000
18.500 1.5628 0.12467 0.12043 -0.0964 0.0157 1.0000
18.750 1.5574 0.12942 0.12532 -0.0983 0.0155 1.0000
19.000 1.5521 0.13423 0.13025 -0.1004 0.0153 1.0000
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