GOE 496 AIRFOIL (goe496-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 496 AIRFOIL (goe496-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.96 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe496-il-1000000-n5.txt Download as CSV file: xf-goe496-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 496 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.4431 0.13678 0.13497 -0.0331 1.0000 0.0095
-14.000 -0.4365 0.13448 0.13267 -0.0338 1.0000 0.0097
-13.500 -0.8973 0.02604 0.02305 -0.1249 0.9878 0.0109
-13.250 -0.8697 0.02356 0.02038 -0.1293 0.9863 0.0115
-13.000 -0.8404 0.02183 0.01850 -0.1324 0.9852 0.0120
-12.750 -0.8166 0.02049 0.01704 -0.1336 0.9820 0.0128
-12.500 -0.7888 0.01942 0.01589 -0.1351 0.9799 0.0137
-12.250 -0.7593 0.01851 0.01489 -0.1366 0.9783 0.0146
-12.000 -0.7289 0.01766 0.01393 -0.1382 0.9771 0.0153
-11.750 -0.6973 0.01698 0.01320 -0.1398 0.9761 0.0162
-11.500 -0.6670 0.01651 0.01270 -0.1408 0.9744 0.0172
-11.250 -0.6402 0.01607 0.01221 -0.1410 0.9710 0.0181
-11.000 -0.6104 0.01556 0.01162 -0.1419 0.9685 0.0188
-10.750 -0.5794 0.01506 0.01103 -0.1430 0.9664 0.0193
-10.500 -0.5489 0.01448 0.01037 -0.1441 0.9641 0.0199
-10.250 -0.5220 0.01408 0.00994 -0.1442 0.9593 0.0205
-10.000 -0.4914 0.01376 0.00960 -0.1449 0.9560 0.0212
-9.750 -0.4608 0.01349 0.00928 -0.1457 0.9524 0.0219
-9.500 -0.4328 0.01315 0.00888 -0.1459 0.9466 0.0225
-9.250 -0.4022 0.01278 0.00844 -0.1466 0.9417 0.0231
-9.000 -0.3744 0.01248 0.00807 -0.1467 0.9338 0.0236
-8.750 -0.3452 0.01221 0.00772 -0.1471 0.9252 0.0240
-8.500 -0.3164 0.01197 0.00739 -0.1473 0.9147 0.0243
-8.250 -0.2895 0.01143 0.00674 -0.1474 0.9023 0.0250
-8.000 -0.2623 0.01102 0.00625 -0.1474 0.8903 0.0257
-7.750 -0.2349 0.01077 0.00592 -0.1473 0.8783 0.0263
-7.500 -0.2078 0.01053 0.00559 -0.1472 0.8665 0.0268
-7.250 -0.1808 0.01032 0.00530 -0.1470 0.8542 0.0274
-7.000 -0.1537 0.01008 0.00498 -0.1468 0.8429 0.0278
-6.750 -0.1266 0.00986 0.00465 -0.1466 0.8323 0.0283
-6.500 -0.0996 0.00964 0.00435 -0.1465 0.8219 0.0287
-6.250 -0.0722 0.00944 0.00406 -0.1463 0.8123 0.0292
-6.000 -0.0450 0.00926 0.00380 -0.1461 0.8032 0.0296
-5.750 -0.0174 0.00910 0.00357 -0.1460 0.7942 0.0299
-5.500 0.0101 0.00897 0.00337 -0.1458 0.7860 0.0303
-5.250 0.0376 0.00878 0.00311 -0.1457 0.7770 0.0306
-5.000 0.0651 0.00854 0.00280 -0.1456 0.7691 0.0315
-4.750 0.0928 0.00837 0.00256 -0.1455 0.7608 0.0323
-4.500 0.1205 0.00822 0.00238 -0.1454 0.7530 0.0332
-4.250 0.1482 0.00811 0.00222 -0.1452 0.7443 0.0340
-4.000 0.1760 0.00800 0.00207 -0.1451 0.7365 0.0350
-3.750 0.2037 0.00792 0.00194 -0.1450 0.7283 0.0360
-3.500 0.2316 0.00784 0.00181 -0.1449 0.7204 0.0370
-3.250 0.2592 0.00779 0.00171 -0.1447 0.7116 0.0378
-3.000 0.2872 0.00769 0.00158 -0.1446 0.7036 0.0404
-2.750 0.3147 0.00761 0.00148 -0.1444 0.6949 0.0438
-2.500 0.3426 0.00755 0.00140 -0.1443 0.6863 0.0467
-2.250 0.3702 0.00752 0.00132 -0.1441 0.6776 0.0514
-2.000 0.3981 0.00744 0.00124 -0.1440 0.6686 0.0595
-1.750 0.4255 0.00732 0.00122 -0.1439 0.6598 0.0930
-1.500 0.4531 0.00733 0.00120 -0.1437 0.6496 0.0985
-1.250 0.4806 0.00733 0.00118 -0.1435 0.6380 0.1054
-1.000 0.5078 0.00737 0.00117 -0.1433 0.6249 0.1092
-0.750 0.5349 0.00743 0.00117 -0.1430 0.6110 0.1115
-0.500 0.5620 0.00746 0.00117 -0.1427 0.5977 0.1173
-0.250 0.5892 0.00749 0.00118 -0.1425 0.5859 0.1228
0.000 0.6163 0.00753 0.00119 -0.1423 0.5725 0.1305
0.500 0.6705 0.00757 0.00124 -0.1418 0.5490 0.1630
0.750 0.6973 0.00752 0.00130 -0.1416 0.5364 0.2212
1.000 0.7241 0.00755 0.00136 -0.1414 0.5223 0.2542
1.250 0.7510 0.00761 0.00143 -0.1411 0.5094 0.2758
1.500 0.7782 0.00766 0.00150 -0.1409 0.5008 0.2941
1.750 0.8053 0.00771 0.00157 -0.1407 0.4921 0.3120
2.000 0.8324 0.00776 0.00165 -0.1405 0.4830 0.3351
2.250 0.8591 0.00782 0.00175 -0.1402 0.4722 0.3638
2.500 0.8858 0.00788 0.00185 -0.1400 0.4607 0.3920
2.750 0.9126 0.00794 0.00196 -0.1397 0.4507 0.4229
3.000 0.9391 0.00804 0.00208 -0.1394 0.4395 0.4492
3.250 0.9653 0.00815 0.00221 -0.1390 0.4259 0.4757
3.500 0.9911 0.00828 0.00235 -0.1386 0.4092 0.5059
3.750 1.0164 0.00843 0.00251 -0.1381 0.3887 0.5407
4.000 1.0411 0.00853 0.00273 -0.1376 0.3675 0.6312
4.250 1.0653 0.00870 0.00295 -0.1369 0.3443 0.7014
4.750 1.1094 0.00895 0.00347 -0.1347 0.2848 1.0000
5.000 1.1316 0.00944 0.00377 -0.1337 0.2508 1.0000
5.250 1.1548 0.00982 0.00405 -0.1329 0.2294 1.0000
5.500 1.1783 0.01018 0.00431 -0.1321 0.2121 1.0000
5.750 1.2017 0.01053 0.00457 -0.1313 0.1957 1.0000
6.000 1.2252 0.01086 0.00484 -0.1305 0.1808 1.0000
6.250 1.2485 0.01120 0.00510 -0.1297 0.1660 1.0000
6.500 1.2716 0.01154 0.00538 -0.1289 0.1519 1.0000
6.750 1.2937 0.01194 0.00569 -0.1279 0.1353 1.0000
7.000 1.3128 0.01256 0.00615 -0.1265 0.1060 1.0000
7.250 1.3296 0.01332 0.00671 -0.1246 0.0750 1.0000
7.500 1.3483 0.01392 0.00721 -0.1231 0.0581 1.0000
7.750 1.3678 0.01442 0.00766 -0.1217 0.0474 1.0000
8.000 1.3868 0.01493 0.00812 -0.1202 0.0383 1.0000
8.250 1.4053 0.01545 0.00860 -0.1187 0.0303 1.0000
8.500 1.4228 0.01597 0.00908 -0.1169 0.0238 1.0000
8.750 1.4385 0.01649 0.00958 -0.1148 0.0187 1.0000
9.000 1.4542 0.01698 0.01007 -0.1128 0.0161 1.0000
9.250 1.4701 0.01746 0.01056 -0.1108 0.0143 1.0000
9.500 1.4856 0.01797 0.01110 -0.1088 0.0129 1.0000
9.750 1.5002 0.01853 0.01168 -0.1067 0.0118 1.0000
10.000 1.5148 0.01910 0.01228 -0.1046 0.0110 1.0000
10.250 1.5298 0.01966 0.01288 -0.1027 0.0105 1.0000
10.500 1.5440 0.02028 0.01353 -0.1007 0.0100 1.0000
10.750 1.5573 0.02096 0.01425 -0.0987 0.0095 1.0000
11.000 1.5697 0.02171 0.01505 -0.0966 0.0090 1.0000
11.250 1.5806 0.02259 0.01597 -0.0944 0.0084 1.0000
11.500 1.5928 0.02340 0.01683 -0.0925 0.0081 1.0000
11.750 1.6049 0.02424 0.01772 -0.0906 0.0078 1.0000
12.000 1.6160 0.02517 0.01871 -0.0888 0.0076 1.0000
12.250 1.6265 0.02618 0.01977 -0.0869 0.0073 1.0000
12.500 1.6361 0.02728 0.02093 -0.0851 0.0070 1.0000
12.750 1.6449 0.02850 0.02220 -0.0834 0.0067 1.0000
13.000 1.6525 0.02985 0.02361 -0.0816 0.0065 1.0000
13.250 1.6586 0.03138 0.02521 -0.0799 0.0062 1.0000
13.500 1.6645 0.03299 0.02688 -0.0782 0.0060 1.0000
13.750 1.6714 0.03457 0.02854 -0.0769 0.0059 1.0000
14.000 1.6774 0.03628 0.03033 -0.0755 0.0058 1.0000
14.250 1.6828 0.03809 0.03222 -0.0743 0.0057 1.0000
14.500 1.6869 0.04012 0.03433 -0.0732 0.0056 1.0000
14.750 1.6910 0.04221 0.03651 -0.0722 0.0055 1.0000
15.000 1.6936 0.04454 0.03892 -0.0714 0.0054 1.0000
15.250 1.6959 0.04698 0.04145 -0.0707 0.0052 1.0000
15.500 1.6979 0.04954 0.04409 -0.0702 0.0051 1.0000
15.750 1.6987 0.05235 0.04698 -0.0698 0.0050 1.0000
16.000 1.6984 0.05537 0.05010 -0.0696 0.0049 1.0000
16.250 1.6976 0.05859 0.05340 -0.0696 0.0048 1.0000
16.500 1.6954 0.06209 0.05700 -0.0698 0.0047 1.0000
16.750 1.6920 0.06590 0.06091 -0.0702 0.0046 1.0000
17.000 1.6871 0.07002 0.06513 -0.0709 0.0045 1.0000
17.250 1.6801 0.07463 0.06985 -0.0718 0.0044 1.0000
17.500 1.6699 0.07989 0.07523 -0.0732 0.0043 1.0000
17.750 1.6639 0.08461 0.08007 -0.0746 0.0043 1.0000
18.000 1.6566 0.08967 0.08525 -0.0762 0.0043 1.0000
18.250 1.6485 0.09499 0.09069 -0.0781 0.0042 1.0000
18.500 1.6394 0.10060 0.09642 -0.0802 0.0042 1.0000
18.750 1.6292 0.10652 0.10246 -0.0827 0.0042 1.0000
19.000 1.6180 0.11274 0.10881 -0.0854 0.0041 1.0000
19.250 1.6064 0.11918 0.11537 -0.0884 0.0041 1.0000
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Polar data table (+)
Polar graphs
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