GOE 498 AIRFOIL (goe498-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 498 AIRFOIL (goe498-il) Reynolds number: 200,000 Max Cl/Cd: 75.94 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe498-il-200000.txt Download as CSV file: xf-goe498-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 498 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3086 0.12861 0.12493 -0.0357 0.9998 0.0883
-11.250 -0.2873 0.12510 0.12141 -0.0394 0.9972 0.0909
-11.000 -0.5438 0.06343 0.05939 -0.0884 0.9847 0.0704
-10.750 -0.5192 0.06076 0.05674 -0.0918 0.9814 0.0712
-10.500 -0.5110 0.05699 0.05294 -0.0966 0.9729 0.0720
-10.250 -0.5587 0.03987 0.03460 -0.1212 0.9538 0.0717
-10.000 -0.5387 0.03866 0.03338 -0.1211 0.9446 0.0729
-9.750 -0.5090 0.03589 0.03032 -0.1249 0.9404 0.0746
-9.500 -0.4894 0.03337 0.02741 -0.1264 0.9324 0.0760
-9.250 -0.4617 0.03110 0.02459 -0.1288 0.9264 0.0776
-9.000 -0.4253 0.02916 0.02266 -0.1315 0.9239 0.0797
-8.750 -0.3848 0.02791 0.02135 -0.1345 0.9221 0.0822
-8.500 -0.3665 0.02687 0.02011 -0.1334 0.9119 0.0842
-8.250 -0.3298 0.02534 0.01825 -0.1358 0.9086 0.0866
-8.000 -0.2890 0.02407 0.01708 -0.1385 0.9067 0.0895
-7.750 -0.2468 0.02304 0.01592 -0.1414 0.9050 0.0932
-7.500 -0.2261 0.02226 0.01497 -0.1403 0.8955 0.0957
-7.250 -0.1906 0.02129 0.01410 -0.1418 0.8913 0.0991
-7.000 -0.1512 0.02050 0.01320 -0.1439 0.8883 0.1035
-6.750 -0.1114 0.01956 0.01226 -0.1462 0.8858 0.1078
-6.500 -0.0926 0.01923 0.01194 -0.1444 0.8751 0.1114
-6.250 -0.0568 0.01856 0.01115 -0.1457 0.8705 0.1164
-6.000 -0.0186 0.01792 0.01057 -0.1476 0.8672 0.1220
-5.750 0.0019 0.01769 0.01025 -0.1460 0.8570 0.1269
-5.500 0.0349 0.01710 0.00972 -0.1468 0.8515 0.1332
-5.250 0.0718 0.01658 0.00912 -0.1482 0.8473 0.1416
-5.000 0.0912 0.01633 0.00894 -0.1465 0.8368 0.1489
-4.750 0.1243 0.01580 0.00842 -0.1473 0.8314 0.1606
-4.500 0.1509 0.01541 0.00808 -0.1469 0.8237 0.1754
-4.250 0.1786 0.01504 0.00776 -0.1467 0.8158 0.1949
-4.000 0.2128 0.01474 0.00741 -0.1476 0.8104 0.2171
-3.750 0.2358 0.01466 0.00739 -0.1466 0.8010 0.2329
-3.500 0.2672 0.01449 0.00719 -0.1469 0.7942 0.2489
-3.250 0.2950 0.01440 0.00710 -0.1466 0.7865 0.2630
-3.000 0.3232 0.01432 0.00697 -0.1464 0.7782 0.2772
-2.750 0.3560 0.01422 0.00679 -0.1470 0.7719 0.2922
-2.500 0.3796 0.01417 0.00680 -0.1459 0.7620 0.3049
-2.250 0.4115 0.01405 0.00662 -0.1463 0.7543 0.3209
-2.000 0.4359 0.01407 0.00660 -0.1453 0.7438 0.3360
-1.750 0.4663 0.01400 0.00650 -0.1455 0.7357 0.3521
-1.500 0.4911 0.01399 0.00654 -0.1447 0.7266 0.3660
-1.250 0.5195 0.01398 0.00649 -0.1445 0.7187 0.3816
-1.000 0.5475 0.01405 0.00651 -0.1442 0.7112 0.3975
-0.750 0.5727 0.01404 0.00657 -0.1435 0.7025 0.4119
-0.500 0.6030 0.01405 0.00654 -0.1436 0.6956 0.4277
-0.250 0.6266 0.01412 0.00663 -0.1426 0.6868 0.4424
0.000 0.6541 0.01411 0.00664 -0.1423 0.6793 0.4565
0.250 0.6810 0.01415 0.00670 -0.1418 0.6717 0.4709
0.500 0.7059 0.01417 0.00674 -0.1410 0.6628 0.4866
0.750 0.7357 0.01421 0.00671 -0.1411 0.6555 0.5045
1.000 0.7574 0.01422 0.00685 -0.1397 0.6459 0.5214
1.250 0.7851 0.01422 0.00684 -0.1393 0.6381 0.5415
1.500 0.8086 0.01427 0.00696 -0.1383 0.6293 0.5628
1.750 0.8341 0.01428 0.00699 -0.1375 0.6211 0.5875
2.000 0.8593 0.01430 0.00708 -0.1368 0.6134 0.6134
2.250 0.8824 0.01428 0.00717 -0.1356 0.6047 0.6422
2.500 0.9092 0.01426 0.00717 -0.1351 0.5973 0.6731
2.750 0.9297 0.01421 0.00730 -0.1334 0.5879 0.7074
3.000 0.9536 0.01410 0.00729 -0.1322 0.5802 0.7580
3.250 0.9849 0.01380 0.00738 -0.1325 0.5703 1.0000
3.500 1.0126 0.01397 0.00738 -0.1324 0.5618 1.0000
3.750 1.0357 0.01417 0.00755 -0.1315 0.5524 1.0000
4.000 1.0615 0.01436 0.00764 -0.1310 0.5439 1.0000
4.250 1.0850 0.01460 0.00784 -0.1301 0.5351 1.0000
4.500 1.1091 0.01481 0.00798 -0.1293 0.5263 1.0000
4.750 1.1326 0.01507 0.00819 -0.1284 0.5175 1.0000
5.000 1.1551 0.01529 0.00837 -0.1273 0.5083 1.0000
5.250 1.1783 0.01556 0.00859 -0.1264 0.4994 1.0000
5.500 1.1994 0.01580 0.00881 -0.1251 0.4901 1.0000
5.750 1.2226 0.01610 0.00905 -0.1242 0.4818 1.0000
6.000 1.2422 0.01636 0.00931 -0.1226 0.4725 1.0000
6.250 1.2643 0.01666 0.00954 -0.1215 0.4639 1.0000
6.500 1.2823 0.01693 0.00984 -0.1197 0.4546 1.0000
6.750 1.3047 0.01726 0.01009 -0.1187 0.4468 1.0000
7.000 1.3212 0.01756 0.01045 -0.1166 0.4382 1.0000
7.250 1.3433 0.01790 0.01071 -0.1156 0.4307 1.0000
7.500 1.3573 0.01822 0.01111 -0.1131 0.4226 1.0000
7.750 1.3745 0.01856 0.01141 -0.1112 0.4148 1.0000
8.000 1.3891 0.01894 0.01181 -0.1089 0.4066 1.0000
8.250 1.4028 0.01931 0.01217 -0.1064 0.3978 1.0000
8.500 1.4157 0.01974 0.01261 -0.1039 0.3887 1.0000
8.750 1.4278 0.02018 0.01303 -0.1014 0.3794 1.0000
9.000 1.4388 0.02068 0.01357 -0.0987 0.3699 1.0000
9.250 1.4503 0.02124 0.01406 -0.0962 0.3602 1.0000
9.500 1.4582 0.02185 0.01473 -0.0933 0.3495 1.0000
9.750 1.4665 0.02255 0.01538 -0.0906 0.3387 1.0000
10.000 1.4724 0.02333 0.01617 -0.0877 0.3269 1.0000
10.250 1.4785 0.02419 0.01706 -0.0849 0.3151 1.0000
10.500 1.4837 0.02518 0.01800 -0.0822 0.3036 1.0000
10.750 1.4884 0.02625 0.01907 -0.0796 0.2917 1.0000
11.000 1.4937 0.02737 0.02022 -0.0772 0.2801 1.0000
11.250 1.4980 0.02862 0.02145 -0.0748 0.2695 1.0000
11.500 1.5019 0.02996 0.02279 -0.0726 0.2585 1.0000
11.750 1.5068 0.03134 0.02419 -0.0706 0.2482 1.0000
12.000 1.5096 0.03291 0.02572 -0.0686 0.2395 1.0000
12.250 1.5154 0.03437 0.02724 -0.0670 0.2307 1.0000
12.500 1.5182 0.03610 0.02894 -0.0653 0.2233 1.0000
12.750 1.5237 0.03771 0.03061 -0.0639 0.2157 1.0000
13.000 1.5253 0.03966 0.03251 -0.0624 0.2093 1.0000
13.250 1.5308 0.04141 0.03435 -0.0613 0.2024 1.0000
13.500 1.5322 0.04353 0.03644 -0.0601 0.1962 1.0000
13.750 1.5360 0.04553 0.03851 -0.0591 0.1900 1.0000
14.000 1.5373 0.04780 0.04079 -0.0581 0.1836 1.0000
14.250 1.5381 0.05018 0.04317 -0.0572 0.1773 1.0000
14.500 1.5384 0.05270 0.04576 -0.0565 0.1706 1.0000
14.750 1.5372 0.05540 0.04843 -0.0558 0.1638 1.0000
15.000 1.5348 0.05839 0.05154 -0.0554 0.1562 1.0000
15.250 1.5306 0.06161 0.05478 -0.0550 0.1486 1.0000
15.500 1.5244 0.06524 0.05848 -0.0550 0.1400 1.0000
15.750 1.5185 0.06904 0.06238 -0.0551 0.1305 1.0000
16.000 1.5112 0.07310 0.06650 -0.0555 0.1210 1.0000
16.250 1.5031 0.07738 0.07079 -0.0561 0.1124 1.0000
16.500 1.4952 0.08175 0.07517 -0.0568 0.1047 1.0000
16.750 1.4894 0.08588 0.07933 -0.0575 0.0986 1.0000
17.000 1.4804 0.09046 0.08386 -0.0584 0.0942 1.0000
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