GOE 446 AIRFOIL (goe446-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 446 AIRFOIL (goe446-il) Reynolds number: 1,000,000 Max Cl/Cd: 148.66 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe446-il-1000000.txt Download as CSV file: xf-goe446-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 446 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0295 0.09254 0.09062 -0.0966 0.9118 0.0250
-10.750 -0.0212 0.09027 0.08832 -0.0966 0.9008 0.0252
-10.500 -0.1080 0.09689 0.09495 -0.0944 0.9365 0.0250
-10.250 -0.0992 0.09481 0.09285 -0.0945 0.9283 0.0252
-10.000 -0.0900 0.09270 0.09073 -0.0949 0.9192 0.0253
-9.750 -0.0817 0.09055 0.08854 -0.0954 0.9079 0.0255
-9.500 -0.0737 0.08829 0.08622 -0.0960 0.8936 0.0258
-9.250 -0.0661 0.08590 0.08376 -0.0969 0.8767 0.0262
-9.000 -0.0588 0.08336 0.08115 -0.0981 0.8591 0.0268
-8.750 -0.0032 0.06271 0.06029 -0.1050 0.8012 0.0293
-8.500 0.0046 0.06032 0.05788 -0.1057 0.7930 0.0295
-8.250 0.0122 0.05797 0.05549 -0.1063 0.7847 0.0297
-8.000 -0.1375 0.02342 0.01980 -0.1541 0.7968 0.0276
-7.750 -0.1192 0.02010 0.01603 -0.1550 0.7896 0.0275
-7.500 -0.0966 0.01836 0.01395 -0.1553 0.7829 0.0276
-7.250 -0.0720 0.01704 0.01241 -0.1554 0.7770 0.0277
-7.000 -0.0467 0.01601 0.01116 -0.1555 0.7705 0.0279
-6.750 -0.0207 0.01521 0.01016 -0.1555 0.7643 0.0281
-6.500 0.0063 0.01459 0.00940 -0.1556 0.7587 0.0284
-6.250 0.0338 0.01423 0.00892 -0.1557 0.7534 0.0287
-6.000 0.0612 0.01390 0.00844 -0.1557 0.7483 0.0289
-5.750 0.0880 0.01294 0.00735 -0.1558 0.7436 0.0291
-5.500 0.1146 0.01207 0.00636 -0.1559 0.7385 0.0295
-5.250 0.1417 0.01154 0.00574 -0.1559 0.7334 0.0298
-5.000 0.1696 0.01111 0.00526 -0.1560 0.7290 0.0301
-4.750 0.1977 0.01075 0.00487 -0.1561 0.7246 0.0304
-4.500 0.2257 0.01046 0.00453 -0.1562 0.7203 0.0307
-4.250 0.2537 0.01022 0.00422 -0.1563 0.7160 0.0311
-4.000 0.2822 0.00995 0.00393 -0.1565 0.7125 0.0315
-3.750 0.3107 0.00971 0.00367 -0.1566 0.7089 0.0320
-3.500 0.3391 0.00951 0.00342 -0.1567 0.7051 0.0325
-3.250 0.3674 0.00936 0.00323 -0.1568 0.7013 0.0331
-3.000 0.3959 0.00925 0.00308 -0.1570 0.6976 0.0336
-2.750 0.4245 0.00896 0.00278 -0.1571 0.6941 0.0345
-2.500 0.4530 0.00877 0.00258 -0.1573 0.6900 0.0355
-2.250 0.4814 0.00866 0.00243 -0.1574 0.6858 0.0365
-2.000 0.5097 0.00858 0.00232 -0.1575 0.6817 0.0377
-1.750 0.5386 0.00847 0.00221 -0.1577 0.6782 0.0389
-1.500 0.5672 0.00834 0.00209 -0.1578 0.6741 0.0421
-1.250 0.5955 0.00822 0.00201 -0.1580 0.6699 0.0529
-1.000 0.6235 0.00816 0.00203 -0.1581 0.6655 0.0816
-0.750 0.6523 0.00814 0.00205 -0.1583 0.6616 0.0903
-0.500 0.6808 0.00810 0.00205 -0.1584 0.6568 0.0973
-0.250 0.7087 0.00813 0.00205 -0.1584 0.6518 0.1020
0.000 0.7369 0.00814 0.00205 -0.1585 0.6469 0.1054
0.250 0.7653 0.00809 0.00204 -0.1587 0.6415 0.1114
0.500 0.7931 0.00810 0.00204 -0.1587 0.6360 0.1162
0.750 0.8211 0.00812 0.00205 -0.1588 0.6306 0.1214
1.000 0.8492 0.00809 0.00206 -0.1589 0.6244 0.1306
1.250 0.8764 0.00812 0.00208 -0.1588 0.6178 0.1409
1.500 0.9043 0.00808 0.00211 -0.1589 0.6111 0.1621
1.750 0.9314 0.00800 0.00218 -0.1589 0.6031 0.2308
2.000 0.9581 0.00740 0.00237 -0.1593 0.5949 0.5833
2.250 0.9787 0.00669 0.00252 -0.1576 0.5856 1.0000
2.500 1.0057 0.00680 0.00258 -0.1575 0.5757 1.0000
2.750 1.0317 0.00694 0.00265 -0.1572 0.5652 1.0000
3.250 1.0824 0.00730 0.00285 -0.1563 0.5381 1.0000
3.500 1.1069 0.00751 0.00298 -0.1558 0.5221 1.0000
3.750 1.1310 0.00775 0.00313 -0.1551 0.5059 1.0000
4.000 1.1553 0.00798 0.00329 -0.1545 0.4916 1.0000
4.250 1.1800 0.00819 0.00344 -0.1540 0.4807 1.0000
4.500 1.2038 0.00843 0.00361 -0.1534 0.4701 1.0000
4.750 1.2275 0.00867 0.00380 -0.1527 0.4587 1.0000
5.000 1.2511 0.00891 0.00398 -0.1520 0.4472 1.0000
5.250 1.2739 0.00917 0.00419 -0.1512 0.4362 1.0000
5.500 1.2976 0.00939 0.00438 -0.1506 0.4283 1.0000
5.750 1.3206 0.00962 0.00458 -0.1498 0.4226 1.0000
6.000 1.3451 0.00978 0.00475 -0.1493 0.4173 1.0000
6.250 1.3657 0.01005 0.00498 -0.1481 0.4090 1.0000
6.500 1.3878 0.01026 0.00518 -0.1471 0.4010 1.0000
6.750 1.4083 0.01053 0.00543 -0.1459 0.3935 1.0000
7.000 1.4303 0.01076 0.00566 -0.1449 0.3867 1.0000
7.250 1.4513 0.01103 0.00592 -0.1439 0.3788 1.0000
7.500 1.4719 0.01132 0.00619 -0.1427 0.3693 1.0000
7.750 1.4906 0.01170 0.00652 -0.1413 0.3581 1.0000
8.000 1.5103 0.01204 0.00684 -0.1400 0.3458 1.0000
8.250 1.5272 0.01251 0.00725 -0.1383 0.3290 1.0000
8.500 1.5395 0.01320 0.00781 -0.1359 0.3014 1.0000
8.750 1.5430 0.01436 0.00872 -0.1322 0.2604 1.0000
9.000 1.5432 0.01574 0.00986 -0.1280 0.2206 1.0000
9.250 1.5467 0.01701 0.01096 -0.1246 0.1899 1.0000
9.500 1.5506 0.01831 0.01210 -0.1214 0.1631 1.0000
9.750 1.5574 0.01950 0.01318 -0.1187 0.1427 1.0000
10.000 1.5653 0.02065 0.01426 -0.1163 0.1279 1.0000
10.250 1.5740 0.02179 0.01535 -0.1141 0.1157 1.0000
10.500 1.5826 0.02299 0.01651 -0.1120 0.1046 1.0000
10.750 1.5893 0.02434 0.01780 -0.1098 0.0921 1.0000
11.000 1.5894 0.02623 0.01956 -0.1070 0.0723 1.0000
11.250 1.5708 0.02962 0.02272 -0.1025 0.0342 1.0000
11.500 1.5730 0.03157 0.02468 -0.1003 0.0280 1.0000
11.750 1.5784 0.03332 0.02647 -0.0986 0.0253 1.0000
12.000 1.5862 0.03491 0.02811 -0.0972 0.0238 1.0000
12.250 1.5915 0.03674 0.02998 -0.0956 0.0224 1.0000
12.500 1.5969 0.03862 0.03191 -0.0941 0.0213 1.0000
12.750 1.6048 0.04030 0.03365 -0.0930 0.0205 1.0000
13.000 1.6114 0.04214 0.03553 -0.0918 0.0197 1.0000
13.250 1.6163 0.04414 0.03759 -0.0905 0.0189 1.0000
13.500 1.6178 0.04652 0.04003 -0.0891 0.0182 1.0000
13.750 1.6209 0.04881 0.04239 -0.0880 0.0177 1.0000
14.000 1.6267 0.05085 0.04448 -0.0870 0.0173 1.0000
14.250 1.6312 0.05305 0.04675 -0.0861 0.0168 1.0000
14.500 1.6346 0.05540 0.04917 -0.0852 0.0164 1.0000
14.750 1.6375 0.05782 0.05165 -0.0843 0.0160 1.0000
15.000 1.6388 0.06048 0.05437 -0.0835 0.0156 1.0000
15.250 1.6373 0.06351 0.05746 -0.0827 0.0152 1.0000
15.500 1.6309 0.06718 0.06123 -0.0818 0.0148 1.0000
15.750 1.6309 0.07012 0.06424 -0.0812 0.0146 1.0000
16.000 1.6333 0.07280 0.06700 -0.0808 0.0143 1.0000
16.250 1.6339 0.07576 0.07004 -0.0805 0.0140 1.0000
16.500 1.6333 0.07890 0.07325 -0.0802 0.0138 1.0000
16.750 1.6325 0.08210 0.07653 -0.0799 0.0135 1.0000
17.000 1.6304 0.08548 0.07999 -0.0798 0.0133 1.0000
17.250 1.6277 0.08899 0.08357 -0.0797 0.0131 1.0000
17.500 1.6247 0.09256 0.08721 -0.0798 0.0129 1.0000
17.750 1.6207 0.09631 0.09104 -0.0799 0.0127 1.0000
18.000 1.6145 0.10042 0.09523 -0.0803 0.0125 1.0000
18.250 1.6057 0.10493 0.09983 -0.0807 0.0123 1.0000
18.500 1.5935 0.10996 0.10496 -0.0814 0.0121 1.0000
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