GOE 497 AIRFOIL (goe497-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 497 AIRFOIL (goe497-il) Reynolds number: 1,000,000 Max Cl/Cd: 135.19 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe497-il-1000000.txt Download as CSV file: xf-goe497-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 497 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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.6675 0.10838 0.10614 -0.0612 1.0000 0.0198
-16.500 -0.6823 0.10226 0.10000 -0.0645 1.0000 0.0203
-16.250 -0.6988 0.09597 0.09367 -0.0678 1.0000 0.0206
-16.000 -0.7189 0.08922 0.08686 -0.0715 1.0000 0.0208
-15.750 -0.7407 0.08252 0.08009 -0.0752 1.0000 0.0210
-15.500 -0.7609 0.07633 0.07383 -0.0785 1.0000 0.0212
-15.250 -0.7836 0.07013 0.06756 -0.0818 1.0000 0.0213
-15.000 -0.8093 0.06405 0.06141 -0.0848 1.0000 0.0214
-14.750 -0.8427 0.05799 0.05529 -0.0873 1.0000 0.0214
-14.500 -0.8855 0.05243 0.04967 -0.0878 1.0000 0.0213
-14.250 -0.9033 0.04504 0.04217 -0.0962 0.9971 0.0215
-14.000 -0.9058 0.03623 0.03318 -0.1105 0.9893 0.0217
-13.750 -0.8826 0.02849 0.02522 -0.1262 0.9846 0.0222
-13.500 -0.8474 0.02496 0.02148 -0.1350 0.9828 0.0228
-13.250 -0.8197 0.02359 0.01998 -0.1376 0.9784 0.0232
-13.000 -0.7920 0.02125 0.01753 -0.1421 0.9745 0.0242
-12.750 -0.7592 0.02023 0.01646 -0.1448 0.9725 0.0248
-12.500 -0.7260 0.01941 0.01558 -0.1471 0.9706 0.0256
-12.250 -0.6968 0.01865 0.01473 -0.1485 0.9666 0.0262
-12.000 -0.6693 0.01802 0.01401 -0.1493 0.9613 0.0268
-11.750 -0.6376 0.01758 0.01348 -0.1506 0.9577 0.0273
-11.500 -0.6138 0.01631 0.01213 -0.1515 0.9513 0.0284
-11.250 -0.5878 0.01574 0.01150 -0.1517 0.9447 0.0291
-11.000 -0.5591 0.01526 0.01096 -0.1524 0.9396 0.0298
-10.750 -0.5349 0.01483 0.01047 -0.1520 0.9323 0.0306
-10.500 -0.5079 0.01445 0.01000 -0.1522 0.9264 0.0313
-10.250 -0.4811 0.01416 0.00963 -0.1521 0.9206 0.0319
-10.000 -0.4574 0.01341 0.00880 -0.1519 0.9137 0.0328
-9.750 -0.4312 0.01291 0.00823 -0.1520 0.9079 0.0337
-9.500 -0.4051 0.01259 0.00788 -0.1518 0.9018 0.0347
-9.250 -0.3784 0.01229 0.00752 -0.1516 0.8957 0.0356
-9.000 -0.3512 0.01201 0.00715 -0.1516 0.8902 0.0365
-8.750 -0.3245 0.01174 0.00683 -0.1514 0.8843 0.0371
-8.500 -0.2984 0.01124 0.00625 -0.1513 0.8781 0.0383
-8.250 -0.2717 0.01088 0.00584 -0.1512 0.8720 0.0396
-8.000 -0.2447 0.01061 0.00553 -0.1510 0.8655 0.0407
-7.750 -0.2173 0.01038 0.00523 -0.1509 0.8594 0.0419
-7.500 -0.1897 0.01019 0.00499 -0.1508 0.8538 0.0430
-7.250 -0.1626 0.00985 0.00459 -0.1506 0.8474 0.0445
-7.000 -0.1353 0.00957 0.00425 -0.1505 0.8412 0.0464
-6.750 -0.1076 0.00934 0.00401 -0.1504 0.8354 0.0482
-6.500 -0.0798 0.00918 0.00379 -0.1503 0.8295 0.0499
-6.250 -0.0522 0.00893 0.00348 -0.1502 0.8239 0.0528
-6.000 -0.0243 0.00870 0.00326 -0.1502 0.8179 0.0558
-5.750 0.0036 0.00857 0.00307 -0.1500 0.8115 0.0583
-5.500 0.0313 0.00833 0.00282 -0.1500 0.8055 0.0637
-5.250 0.0594 0.00817 0.00265 -0.1499 0.7991 0.0688
-5.000 0.0872 0.00801 0.00249 -0.1498 0.7929 0.0769
-4.750 0.1153 0.00785 0.00236 -0.1497 0.7867 0.0871
-4.500 0.1433 0.00772 0.00224 -0.1496 0.7798 0.0962
-4.250 0.1713 0.00767 0.00214 -0.1495 0.7732 0.1026
-4.000 0.1994 0.00753 0.00203 -0.1494 0.7658 0.1112
-3.750 0.2271 0.00749 0.00193 -0.1493 0.7581 0.1174
-3.500 0.2553 0.00736 0.00183 -0.1492 0.7500 0.1263
-3.250 0.2830 0.00731 0.00174 -0.1490 0.7425 0.1344
-3.000 0.3112 0.00721 0.00167 -0.1490 0.7353 0.1451
-2.750 0.3390 0.00713 0.00160 -0.1488 0.7274 0.1601
-2.500 0.3669 0.00704 0.00155 -0.1487 0.7192 0.1783
-2.250 0.3944 0.00699 0.00151 -0.1485 0.7103 0.1966
-2.000 0.4223 0.00693 0.00148 -0.1484 0.7018 0.2139
-1.500 0.4778 0.00689 0.00145 -0.1481 0.6851 0.2440
-1.000 0.5332 0.00688 0.00146 -0.1477 0.6688 0.2735
-0.500 0.5884 0.00691 0.00148 -0.1473 0.6521 0.2974
0.000 0.6435 0.00695 0.00153 -0.1469 0.6358 0.3214
0.250 0.6707 0.00700 0.00156 -0.1467 0.6279 0.3333
0.750 0.7256 0.00706 0.00164 -0.1462 0.6120 0.3598
1.000 0.7531 0.00708 0.00169 -0.1460 0.6029 0.3747
1.250 0.7797 0.00715 0.00175 -0.1457 0.5922 0.3913
1.500 0.8067 0.00719 0.00181 -0.1454 0.5807 0.4094
1.750 0.8335 0.00725 0.00188 -0.1451 0.5690 0.4278
2.000 0.8597 0.00734 0.00196 -0.1446 0.5542 0.4463
2.250 0.8853 0.00745 0.00205 -0.1441 0.5350 0.4649
2.500 0.9097 0.00763 0.00217 -0.1434 0.5116 0.4809
2.750 0.9342 0.00782 0.00230 -0.1426 0.4883 0.4974
3.000 0.9588 0.00800 0.00244 -0.1420 0.4710 0.5166
3.250 0.9838 0.00814 0.00258 -0.1414 0.4585 0.5395
4.250 1.0823 0.00803 0.00328 -0.1386 0.4191 1.0000
4.500 1.1072 0.00823 0.00342 -0.1380 0.4088 1.0000
4.750 1.1322 0.00842 0.00357 -0.1374 0.4002 1.0000
5.000 1.1577 0.00858 0.00372 -0.1369 0.3935 1.0000
5.250 1.1829 0.00875 0.00387 -0.1364 0.3853 1.0000
5.500 1.2076 0.00894 0.00403 -0.1357 0.3763 1.0000
5.750 1.2316 0.00916 0.00420 -0.1350 0.3650 1.0000
6.000 1.2558 0.00936 0.00437 -0.1343 0.3520 1.0000
6.250 1.2788 0.00962 0.00456 -0.1334 0.3364 1.0000
6.500 1.2994 0.00998 0.00481 -0.1321 0.3122 1.0000
6.750 1.3172 0.01048 0.00514 -0.1303 0.2818 1.0000
7.000 1.3344 0.01099 0.00551 -0.1284 0.2580 1.0000
7.250 1.3524 0.01139 0.00584 -0.1266 0.2438 1.0000
7.500 1.3701 0.01175 0.00615 -0.1247 0.2330 1.0000
7.750 1.3867 0.01215 0.00650 -0.1227 0.2225 1.0000
8.000 1.4050 0.01247 0.00681 -0.1210 0.2138 1.0000
8.250 1.4224 0.01285 0.00716 -0.1191 0.2051 1.0000
8.500 1.4397 0.01323 0.00751 -0.1173 0.1953 1.0000
8.750 1.4569 0.01363 0.00788 -0.1155 0.1832 1.0000
9.000 1.4700 0.01423 0.00836 -0.1131 0.1632 1.0000
9.250 1.4751 0.01523 0.00913 -0.1096 0.1278 1.0000
9.500 1.4822 0.01616 0.00993 -0.1065 0.1082 1.0000
9.750 1.4939 0.01689 0.01062 -0.1042 0.0982 1.0000
10.000 1.5070 0.01755 0.01127 -0.1021 0.0908 1.0000
10.250 1.5187 0.01832 0.01200 -0.0999 0.0838 1.0000
10.500 1.5334 0.01893 0.01263 -0.0982 0.0799 1.0000
10.750 1.5448 0.01975 0.01343 -0.0961 0.0743 1.0000
11.000 1.5588 0.02044 0.01415 -0.0944 0.0709 1.0000
11.250 1.5718 0.02121 0.01492 -0.0927 0.0678 1.0000
11.500 1.5831 0.02211 0.01582 -0.0908 0.0642 1.0000
11.750 1.5962 0.02292 0.01667 -0.0892 0.0617 1.0000
12.000 1.6089 0.02377 0.01755 -0.0876 0.0592 1.0000
12.250 1.6193 0.02480 0.01858 -0.0859 0.0560 1.0000
12.500 1.6302 0.02583 0.01964 -0.0842 0.0532 1.0000
12.750 1.6417 0.02683 0.02067 -0.0828 0.0506 1.0000
13.000 1.6499 0.02812 0.02195 -0.0811 0.0470 1.0000
13.250 1.6601 0.02929 0.02316 -0.0797 0.0438 1.0000
13.500 1.6658 0.03084 0.02469 -0.0780 0.0390 1.0000
13.750 1.6700 0.03256 0.02641 -0.0763 0.0328 1.0000
14.000 1.6710 0.03464 0.02846 -0.0746 0.0260 1.0000
14.250 1.6714 0.03687 0.03069 -0.0730 0.0218 1.0000
14.500 1.6724 0.03913 0.03298 -0.0717 0.0195 1.0000
14.750 1.6750 0.04131 0.03522 -0.0705 0.0182 1.0000
15.000 1.6752 0.04384 0.03780 -0.0695 0.0170 1.0000
15.250 1.6776 0.04623 0.04026 -0.0686 0.0162 1.0000
15.500 1.6804 0.04863 0.04274 -0.0679 0.0157 1.0000
15.750 1.6816 0.05131 0.04549 -0.0674 0.0151 1.0000
16.000 1.6807 0.05431 0.04856 -0.0669 0.0145 1.0000
16.250 1.6784 0.05758 0.05191 -0.0667 0.0141 1.0000
16.500 1.6733 0.06129 0.05572 -0.0666 0.0137 1.0000
16.750 1.6740 0.06437 0.05888 -0.0666 0.0134 1.0000
17.000 1.6733 0.06771 0.06231 -0.0668 0.0132 1.0000
17.250 1.6713 0.07131 0.06601 -0.0672 0.0129 1.0000
17.500 1.6683 0.07513 0.06993 -0.0678 0.0126 1.0000
17.750 1.6643 0.07920 0.07409 -0.0685 0.0124 1.0000
18.000 1.6593 0.08355 0.07853 -0.0695 0.0122 1.0000
18.250 1.6524 0.08828 0.08337 -0.0708 0.0119 1.0000
18.500 1.6438 0.09339 0.08857 -0.0723 0.0117 1.0000
18.750 1.6333 0.09892 0.09421 -0.0741 0.0115 1.0000
19.000 1.6209 0.10488 0.10028 -0.0763 0.0113 1.0000
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