GOE 498 AIRFOIL (goe498-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 498 AIRFOIL (goe498-il) Reynolds number: 500,000 Max Cl/Cd: 91.52 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe498-il-500000-n5.txt Download as CSV file: xf-goe498-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.6366 0.11149 0.10821 -0.0687 1.0000 0.0321
-17.250 -0.6741 0.10172 0.09832 -0.0739 1.0000 0.0325
-17.000 -0.7019 0.09404 0.09053 -0.0780 1.0000 0.0329
-16.750 -0.7250 0.08743 0.08382 -0.0813 1.0000 0.0333
-16.500 -0.7449 0.08161 0.07791 -0.0841 1.0000 0.0335
-16.250 -0.7634 0.07633 0.07255 -0.0864 1.0000 0.0337
-16.000 -0.7815 0.07148 0.06763 -0.0883 1.0000 0.0339
-15.750 -0.7955 0.06644 0.06249 -0.0913 0.9996 0.0342
-15.500 -0.7983 0.06117 0.05711 -0.0968 0.9979 0.0344
-15.250 -0.8007 0.05595 0.05176 -0.1025 0.9950 0.0348
-15.000 -0.8014 0.05127 0.04698 -0.1077 0.9912 0.0350
-14.750 -0.8015 0.04683 0.04249 -0.1126 0.9865 0.0354
-14.500 -0.7972 0.04240 0.03798 -0.1184 0.9823 0.0357
-14.250 -0.7962 0.03831 0.03381 -0.1229 0.9752 0.0361
-14.000 -0.7875 0.03434 0.02975 -0.1286 0.9700 0.0364
-13.750 -0.7824 0.03067 0.02597 -0.1332 0.9616 0.0368
-13.500 -0.7651 0.02702 0.02218 -0.1402 0.9561 0.0372
-13.250 -0.7431 0.02451 0.01952 -0.1453 0.9499 0.0377
-13.000 -0.7172 0.02307 0.01795 -0.1481 0.9452 0.0383
-12.750 -0.6876 0.02190 0.01667 -0.1506 0.9416 0.0390
-12.500 -0.6621 0.02084 0.01554 -0.1522 0.9369 0.0396
-12.250 -0.6382 0.01997 0.01463 -0.1529 0.9310 0.0403
-12.000 -0.6096 0.01921 0.01380 -0.1542 0.9263 0.0410
-11.750 -0.5810 0.01852 0.01303 -0.1554 0.9217 0.0418
-11.500 -0.5585 0.01794 0.01238 -0.1551 0.9149 0.0426
-11.250 -0.5317 0.01738 0.01172 -0.1555 0.9091 0.0434
-11.000 -0.5046 0.01680 0.01107 -0.1560 0.9037 0.0442
-10.750 -0.4824 0.01633 0.01057 -0.1553 0.8963 0.0450
-10.500 -0.4560 0.01589 0.01008 -0.1554 0.8894 0.0461
-10.250 -0.4302 0.01550 0.00961 -0.1552 0.8828 0.0472
-10.000 -0.4061 0.01514 0.00918 -0.1547 0.8750 0.0484
-9.750 -0.3799 0.01474 0.00872 -0.1546 0.8678 0.0495
-9.500 -0.3552 0.01440 0.00835 -0.1541 0.8602 0.0506
-9.250 -0.3296 0.01409 0.00799 -0.1537 0.8518 0.0520
-9.000 -0.3032 0.01380 0.00762 -0.1534 0.8439 0.0534
-8.750 -0.2780 0.01349 0.00727 -0.1530 0.8340 0.0547
-8.500 -0.2518 0.01323 0.00695 -0.1526 0.8242 0.0563
-8.250 -0.2258 0.01300 0.00666 -0.1522 0.8127 0.0580
-8.000 -0.1994 0.01281 0.00637 -0.1518 0.8017 0.0597
-7.750 -0.1737 0.01255 0.00606 -0.1513 0.7896 0.0613
-7.500 -0.1477 0.01236 0.00581 -0.1508 0.7769 0.0630
-7.250 -0.1215 0.01220 0.00556 -0.1504 0.7657 0.0647
-7.000 -0.0953 0.01205 0.00532 -0.1499 0.7552 0.0664
-6.750 -0.0692 0.01184 0.00507 -0.1495 0.7461 0.0683
-6.500 -0.0429 0.01170 0.00486 -0.1491 0.7369 0.0703
-6.250 -0.0162 0.01158 0.00467 -0.1487 0.7287 0.0723
-6.000 0.0103 0.01143 0.00446 -0.1483 0.7205 0.0740
-5.500 0.0639 0.01111 0.00407 -0.1476 0.7072 0.0785
-5.250 0.0909 0.01101 0.00391 -0.1473 0.7002 0.0808
-4.750 0.1447 0.01071 0.00356 -0.1466 0.6872 0.0870
-4.500 0.1718 0.01059 0.00342 -0.1463 0.6809 0.0906
-4.250 0.1986 0.01046 0.00328 -0.1460 0.6745 0.0962
-4.000 0.2256 0.01030 0.00316 -0.1457 0.6684 0.1059
-3.750 0.2524 0.01015 0.00307 -0.1454 0.6610 0.1245
-3.250 0.3055 0.01001 0.00292 -0.1445 0.6430 0.1509
-2.750 0.3585 0.00993 0.00280 -0.1435 0.6242 0.1678
-2.250 0.4120 0.00985 0.00271 -0.1427 0.6101 0.1873
-2.000 0.4389 0.00980 0.00268 -0.1424 0.6022 0.1978
-1.500 0.4907 0.00979 0.00265 -0.1412 0.5816 0.2259
-1.250 0.5162 0.00981 0.00266 -0.1406 0.5711 0.2405
-1.000 0.5422 0.00982 0.00268 -0.1400 0.5616 0.2554
-0.750 0.5682 0.00985 0.00270 -0.1395 0.5542 0.2695
-0.500 0.5948 0.00988 0.00273 -0.1390 0.5467 0.2826
-0.250 0.6204 0.00992 0.00278 -0.1384 0.5389 0.2936
0.000 0.6466 0.00998 0.00281 -0.1379 0.5313 0.3029
0.250 0.6723 0.01003 0.00287 -0.1373 0.5230 0.3134
0.500 0.6977 0.01011 0.00293 -0.1367 0.5155 0.3242
0.750 0.7236 0.01014 0.00299 -0.1361 0.5078 0.3361
1.000 0.7483 0.01025 0.00306 -0.1353 0.4999 0.3463
1.250 0.7739 0.01030 0.00314 -0.1347 0.4919 0.3580
1.750 0.8228 0.01049 0.00332 -0.1331 0.4730 0.3800
2.000 0.8467 0.01060 0.00342 -0.1322 0.4639 0.3924
2.250 0.8711 0.01069 0.00353 -0.1314 0.4560 0.4078
2.500 0.8946 0.01079 0.00366 -0.1305 0.4464 0.4241
2.750 0.9179 0.01091 0.00379 -0.1295 0.4371 0.4414
3.000 0.9403 0.01104 0.00393 -0.1283 0.4270 0.4604
3.250 0.9625 0.01116 0.00408 -0.1271 0.4178 0.4796
3.500 0.9830 0.01130 0.00425 -0.1256 0.4081 0.5039
3.750 1.0042 0.01143 0.00442 -0.1242 0.3990 0.5293
4.000 1.0239 0.01160 0.00461 -0.1226 0.3896 0.5524
4.250 1.0450 0.01177 0.00480 -0.1212 0.3812 0.5698
4.750 1.0844 0.01221 0.00524 -0.1180 0.3619 0.6021
5.000 1.1033 0.01245 0.00549 -0.1163 0.3536 0.6212
5.500 1.1418 0.01285 0.00601 -0.1131 0.3378 0.6718
5.750 1.1599 0.01301 0.00629 -0.1113 0.3315 0.7214
6.250 1.2071 0.01319 0.00687 -0.1100 0.3178 1.0000
6.500 1.2268 0.01350 0.00716 -0.1086 0.3107 1.0000
6.750 1.2442 0.01389 0.00750 -0.1068 0.3015 1.0000
7.000 1.2619 0.01427 0.00785 -0.1052 0.2922 1.0000
7.250 1.2775 0.01475 0.00827 -0.1032 0.2815 1.0000
7.500 1.2953 0.01514 0.00865 -0.1017 0.2720 1.0000
7.750 1.3106 0.01565 0.00911 -0.0998 0.2608 1.0000
8.000 1.3245 0.01624 0.00963 -0.0978 0.2465 1.0000
8.250 1.3326 0.01712 0.01037 -0.0950 0.2202 1.0000
8.500 1.3361 0.01828 0.01133 -0.0918 0.1914 1.0000
8.750 1.3435 0.01928 0.01224 -0.0892 0.1776 1.0000
9.000 1.3545 0.02013 0.01305 -0.0872 0.1700 1.0000
9.250 1.3673 0.02090 0.01382 -0.0854 0.1655 1.0000
9.500 1.3796 0.02172 0.01464 -0.0837 0.1620 1.0000
9.750 1.3929 0.02251 0.01545 -0.0821 0.1592 1.0000
10.000 1.4074 0.02325 0.01622 -0.0807 0.1571 1.0000
10.250 1.4209 0.02407 0.01707 -0.0792 0.1547 1.0000
10.500 1.4333 0.02498 0.01801 -0.0777 0.1522 1.0000
10.750 1.4442 0.02601 0.01906 -0.0762 0.1495 1.0000
11.000 1.4535 0.02718 0.02025 -0.0746 0.1464 1.0000
11.250 1.4665 0.02814 0.02125 -0.0734 0.1442 1.0000
11.500 1.4796 0.02910 0.02227 -0.0722 0.1417 1.0000
11.750 1.4916 0.03019 0.02339 -0.0711 0.1390 1.0000
12.000 1.5015 0.03145 0.02469 -0.0698 0.1357 1.0000
12.250 1.5089 0.03296 0.02621 -0.0685 0.1323 1.0000
12.500 1.5213 0.03409 0.02740 -0.0676 0.1293 1.0000
12.750 1.5311 0.03548 0.02882 -0.0666 0.1238 1.0000
13.000 1.5388 0.03707 0.03043 -0.0656 0.1177 1.0000
13.250 1.5429 0.03903 0.03234 -0.0645 0.1033 1.0000
13.500 1.5349 0.04216 0.03532 -0.0630 0.0843 1.0000
13.750 1.5332 0.04480 0.03796 -0.0620 0.0777 1.0000
14.000 1.5327 0.04743 0.04060 -0.0611 0.0733 1.0000
14.250 1.5347 0.04988 0.04310 -0.0605 0.0700 1.0000
14.500 1.5346 0.05258 0.04584 -0.0599 0.0671 1.0000
14.750 1.5368 0.05512 0.04844 -0.0594 0.0645 1.0000
15.000 1.5377 0.05786 0.05124 -0.0591 0.0620 1.0000
15.250 1.5370 0.06086 0.05428 -0.0589 0.0599 1.0000
15.500 1.5392 0.06356 0.05704 -0.0587 0.0578 1.0000
15.750 1.5395 0.06655 0.06010 -0.0587 0.0558 1.0000
16.000 1.5379 0.06984 0.06344 -0.0588 0.0540 1.0000
16.250 1.5388 0.07287 0.06654 -0.0590 0.0525 1.0000
16.500 1.5385 0.07611 0.06985 -0.0592 0.0509 1.0000
16.750 1.5373 0.07949 0.07329 -0.0596 0.0494 1.0000
17.000 1.5345 0.08317 0.07702 -0.0602 0.0481 1.0000
17.250 1.5335 0.08665 0.08059 -0.0607 0.0469 1.0000
17.500 1.5328 0.09013 0.08414 -0.0614 0.0457 1.0000
17.750 1.5302 0.09391 0.08799 -0.0622 0.0446 1.0000
18.000 1.5265 0.09791 0.09206 -0.0632 0.0437 1.0000
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Polar data table (+)
Polar graphs
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