GOE 498 AIRFOIL (goe498-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 498 AIRFOIL (goe498-il) Reynolds number: 500,000 Max Cl/Cd: 105.79 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe498-il-500000.txt Download as CSV file: xf-goe498-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7349 0.07356 0.07012 -0.0892 1.0000 0.0410
-15.500 -0.7824 0.06506 0.06144 -0.0939 1.0000 0.0410
-15.250 -0.8177 0.05934 0.05559 -0.0960 1.0000 0.0411
-15.000 -0.8520 0.05458 0.05073 -0.0968 1.0000 0.0412
-14.750 -0.8752 0.05014 0.04616 -0.0989 0.9994 0.0413
-14.500 -0.8742 0.04466 0.04049 -0.1066 0.9961 0.0416
-14.250 -0.8582 0.04187 0.03769 -0.1109 0.9935 0.0422
-14.000 -0.8441 0.03913 0.03490 -0.1151 0.9899 0.0427
-13.750 -0.8287 0.03625 0.03195 -0.1201 0.9856 0.0431
-13.500 -0.8080 0.03332 0.02892 -0.1266 0.9821 0.0437
-13.250 -0.7957 0.03062 0.02606 -0.1312 0.9749 0.0443
-13.000 -0.7701 0.02868 0.02396 -0.1349 0.9712 0.0450
-12.750 -0.7412 0.02704 0.02214 -0.1383 0.9691 0.0457
-12.500 -0.7209 0.02585 0.02079 -0.1392 0.9641 0.0462
-12.250 -0.6975 0.02444 0.01938 -0.1402 0.9600 0.0471
-12.000 -0.6653 0.02359 0.01853 -0.1422 0.9578 0.0480
-11.750 -0.6311 0.02275 0.01764 -0.1445 0.9562 0.0489
-11.500 -0.5959 0.02180 0.01660 -0.1470 0.9549 0.0500
-11.250 -0.5588 0.02089 0.01555 -0.1498 0.9539 0.0511
-11.000 -0.5408 0.02009 0.01467 -0.1487 0.9466 0.0519
-10.750 -0.5088 0.01924 0.01384 -0.1502 0.9435 0.0529
-10.500 -0.4731 0.01864 0.01322 -0.1522 0.9411 0.0542
-10.250 -0.4370 0.01803 0.01252 -0.1541 0.9386 0.0557
-10.000 -0.4146 0.01758 0.01197 -0.1533 0.9314 0.0568
-9.750 -0.3856 0.01677 0.01115 -0.1540 0.9264 0.0582
-9.500 -0.3522 0.01625 0.01060 -0.1553 0.9225 0.0596
-9.250 -0.3282 0.01587 0.01019 -0.1547 0.9152 0.0611
-9.000 -0.2998 0.01549 0.00971 -0.1548 0.9088 0.0628
-8.750 -0.2690 0.01488 0.00906 -0.1556 0.9035 0.0647
-8.500 -0.2470 0.01455 0.00873 -0.1545 0.8947 0.0663
-8.250 -0.2182 0.01422 0.00832 -0.1546 0.8880 0.0684
-8.000 -0.1917 0.01398 0.00799 -0.1542 0.8800 0.0701
-7.750 -0.1676 0.01338 0.00740 -0.1536 0.8712 0.0723
-7.500 -0.1404 0.01306 0.00704 -0.1535 0.8632 0.0745
-7.250 -0.1149 0.01281 0.00672 -0.1529 0.8536 0.0768
-7.000 -0.0883 0.01238 0.00624 -0.1526 0.8451 0.0794
-6.750 -0.0634 0.01204 0.00589 -0.1520 0.8344 0.0819
-6.500 -0.0365 0.01179 0.00557 -0.1516 0.8248 0.0845
-6.250 -0.0105 0.01150 0.00521 -0.1511 0.8142 0.0872
-6.000 0.0155 0.01116 0.00487 -0.1507 0.8044 0.0906
-5.750 0.0423 0.01096 0.00459 -0.1504 0.7943 0.0939
-5.500 0.0686 0.01071 0.00431 -0.1499 0.7844 0.0978
-5.250 0.0954 0.01051 0.00407 -0.1496 0.7747 0.1025
-5.000 0.1220 0.01033 0.00387 -0.1492 0.7658 0.1084
-4.750 0.1490 0.01017 0.00369 -0.1488 0.7571 0.1170
-4.500 0.1759 0.01001 0.00357 -0.1485 0.7488 0.1312
-4.250 0.2028 0.00988 0.00346 -0.1482 0.7403 0.1503
-4.000 0.2302 0.00980 0.00335 -0.1479 0.7328 0.1666
-3.750 0.2569 0.00968 0.00327 -0.1475 0.7247 0.1802
-3.500 0.2841 0.00965 0.00319 -0.1472 0.7160 0.1926
-3.250 0.3104 0.00958 0.00313 -0.1466 0.7066 0.2038
-3.000 0.3372 0.00955 0.00307 -0.1462 0.6977 0.2168
-2.750 0.3641 0.00950 0.00305 -0.1458 0.6900 0.2303
-2.500 0.3911 0.00946 0.00302 -0.1454 0.6824 0.2439
-2.250 0.4185 0.00949 0.00300 -0.1451 0.6753 0.2591
-2.000 0.4453 0.00944 0.00300 -0.1447 0.6680 0.2739
-1.750 0.4721 0.00943 0.00300 -0.1443 0.6604 0.2887
-1.500 0.4990 0.00945 0.00300 -0.1439 0.6530 0.3015
-1.250 0.5256 0.00945 0.00300 -0.1434 0.6444 0.3139
-1.000 0.5520 0.00948 0.00301 -0.1429 0.6366 0.3260
-0.750 0.5787 0.00947 0.00302 -0.1424 0.6289 0.3370
-0.500 0.6048 0.00948 0.00303 -0.1419 0.6206 0.3488
-0.250 0.6312 0.00951 0.00305 -0.1413 0.6125 0.3597
0.000 0.6570 0.00952 0.00307 -0.1407 0.6035 0.3714
0.250 0.6829 0.00957 0.00310 -0.1401 0.5955 0.3830
0.500 0.7091 0.00959 0.00314 -0.1396 0.5875 0.3965
0.750 0.7345 0.00965 0.00319 -0.1389 0.5798 0.4110
1.000 0.7606 0.00966 0.00325 -0.1384 0.5721 0.4256
1.250 0.7859 0.00973 0.00331 -0.1377 0.5639 0.4411
1.500 0.8113 0.00977 0.00340 -0.1371 0.5561 0.4585
1.750 0.8364 0.00982 0.00348 -0.1364 0.5478 0.4779
2.000 0.8610 0.00992 0.00359 -0.1356 0.5402 0.4990
2.250 0.8863 0.00996 0.00370 -0.1349 0.5323 0.5230
2.500 0.9104 0.01008 0.00381 -0.1340 0.5243 0.5463
2.750 0.9350 0.01015 0.00394 -0.1332 0.5162 0.5689
3.000 0.9583 0.01025 0.00406 -0.1322 0.5073 0.5921
3.250 0.9820 0.01033 0.00420 -0.1313 0.4995 0.6155
3.500 1.0052 0.01041 0.00433 -0.1302 0.4909 0.6390
4.000 1.0491 0.01053 0.00461 -0.1276 0.4731 0.7039
4.250 1.0666 0.01047 0.00479 -0.1254 0.4644 0.7908
4.500 1.0992 0.01039 0.00495 -0.1263 0.4539 1.0000
4.750 1.1198 0.01060 0.00510 -0.1248 0.4452 1.0000
5.000 1.1402 0.01079 0.00526 -0.1233 0.4357 1.0000
5.250 1.1598 0.01102 0.00544 -0.1216 0.4264 1.0000
5.500 1.1793 0.01126 0.00563 -0.1200 0.4167 1.0000
5.750 1.1988 0.01151 0.00585 -0.1184 0.4080 1.0000
6.000 1.2178 0.01178 0.00607 -0.1167 0.3983 1.0000
6.250 1.2369 0.01206 0.00632 -0.1151 0.3896 1.0000
6.500 1.2552 0.01236 0.00658 -0.1133 0.3804 1.0000
6.750 1.2737 0.01267 0.00686 -0.1116 0.3715 1.0000
7.000 1.2913 0.01301 0.00717 -0.1098 0.3625 1.0000
7.250 1.3092 0.01335 0.00749 -0.1081 0.3540 1.0000
7.500 1.3261 0.01374 0.00784 -0.1063 0.3449 1.0000
7.750 1.3434 0.01411 0.00820 -0.1046 0.3369 1.0000
8.000 1.3592 0.01455 0.00860 -0.1027 0.3270 1.0000
8.250 1.3752 0.01499 0.00902 -0.1008 0.3167 1.0000
8.500 1.3880 0.01557 0.00953 -0.0985 0.3053 1.0000
8.750 1.4036 0.01606 0.01001 -0.0967 0.2940 1.0000
9.000 1.4182 0.01660 0.01053 -0.0948 0.2836 1.0000
9.250 1.4298 0.01729 0.01117 -0.0926 0.2702 1.0000
9.500 1.4407 0.01805 0.01186 -0.0904 0.2545 1.0000
9.750 1.4500 0.01892 0.01266 -0.0880 0.2361 1.0000
10.000 1.4567 0.01996 0.01361 -0.0855 0.2174 1.0000
10.250 1.4636 0.02105 0.01462 -0.0830 0.2035 1.0000
10.500 1.4704 0.02219 0.01571 -0.0807 0.1936 1.0000
10.750 1.4799 0.02322 0.01673 -0.0788 0.1874 1.0000
11.000 1.4873 0.02441 0.01791 -0.0768 0.1818 1.0000
11.250 1.4969 0.02550 0.01902 -0.0751 0.1775 1.0000
11.500 1.5063 0.02665 0.02019 -0.0735 0.1733 1.0000
11.750 1.5130 0.02802 0.02157 -0.0717 0.1691 1.0000
12.000 1.5189 0.02949 0.02305 -0.0700 0.1651 1.0000
12.250 1.5310 0.03058 0.02420 -0.0689 0.1619 1.0000
12.500 1.5398 0.03193 0.02560 -0.0676 0.1583 1.0000
12.750 1.5455 0.03357 0.02725 -0.0662 0.1546 1.0000
13.000 1.5502 0.03534 0.02905 -0.0649 0.1509 1.0000
13.250 1.5632 0.03647 0.03027 -0.0641 0.1472 1.0000
13.500 1.5706 0.03812 0.03195 -0.0631 0.1427 1.0000
13.750 1.5727 0.04027 0.03411 -0.0620 0.1379 1.0000
14.000 1.5855 0.04150 0.03541 -0.0614 0.1316 1.0000
14.250 1.5895 0.04359 0.03750 -0.0605 0.1233 1.0000
14.500 1.5913 0.04594 0.03981 -0.0597 0.1068 1.0000
14.750 1.5814 0.04956 0.04330 -0.0588 0.0894 1.0000
15.000 1.5725 0.05318 0.04689 -0.0581 0.0814 1.0000
15.250 1.5635 0.05696 0.05068 -0.0576 0.0762 1.0000
15.500 1.5585 0.06043 0.05420 -0.0573 0.0723 1.0000
15.750 1.5493 0.06450 0.05830 -0.0572 0.0693 1.0000
16.000 1.5476 0.06773 0.06162 -0.0572 0.0666 1.0000
16.250 1.5422 0.07152 0.06546 -0.0573 0.0641 1.0000
16.500 1.5320 0.07603 0.07001 -0.0578 0.0621 1.0000
16.750 1.5313 0.07936 0.07344 -0.0581 0.0603 1.0000
17.000 1.5288 0.08299 0.07714 -0.0586 0.0585 1.0000
17.250 1.5240 0.08699 0.08119 -0.0593 0.0570 1.0000
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Polar data table (+)
Polar graphs
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