GOE 652 AIRFOIL (goe652-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 652 AIRFOIL (goe652-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.74 at α=0.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe652-il-1000000-n5.txt Download as CSV file: xf-goe652-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 652 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.1787 0.09170 0.08870 -0.1394 0.8952 0.0428
-14.500 -0.1595 0.08765 0.08456 -0.1461 0.8861 0.0434
-14.250 -0.1436 0.08454 0.08137 -0.1506 0.8740 0.0439
-14.000 -0.1378 0.08047 0.07719 -0.1552 0.8627 0.0443
-13.750 -0.1359 0.07653 0.07314 -0.1590 0.8510 0.0447
-13.500 -0.1343 0.07294 0.06945 -0.1623 0.8409 0.0450
-13.250 -0.1293 0.07012 0.06655 -0.1646 0.8309 0.0454
-13.000 -0.1263 0.06720 0.06354 -0.1669 0.8208 0.0457
-12.750 -0.1218 0.06459 0.06087 -0.1689 0.8122 0.0461
-12.500 -0.1156 0.06235 0.05855 -0.1704 0.8039 0.0463
-12.250 -0.1119 0.05983 0.05596 -0.1722 0.7975 0.0466
-12.000 -0.1047 0.05775 0.05385 -0.1735 0.7917 0.0468
-11.750 -0.0978 0.05574 0.05179 -0.1748 0.7855 0.0471
-11.500 -0.0941 0.05352 0.04950 -0.1760 0.7787 0.0473
-11.250 -0.0861 0.05173 0.04768 -0.1770 0.7740 0.0474
-11.000 -0.0777 0.05008 0.04602 -0.1778 0.7691 0.0478
-10.750 -0.0711 0.04838 0.04431 -0.1784 0.7637 0.0481
-10.500 -0.0688 0.04647 0.04235 -0.1789 0.7579 0.0484
-10.250 -0.0669 0.04467 0.04056 -0.1790 0.7531 0.0488
-10.000 -0.0666 0.04305 0.03893 -0.1787 0.7480 0.0490
-9.750 -0.0637 0.04096 0.03681 -0.1800 0.7423 0.0494
-9.500 -0.0560 0.03912 0.03492 -0.1814 0.7365 0.0497
-9.250 -0.0456 0.03714 0.03291 -0.1835 0.7321 0.0502
-9.000 -0.0327 0.03492 0.03067 -0.1866 0.7278 0.0505
-8.750 -0.0152 0.03296 0.02868 -0.1898 0.7231 0.0510
-8.500 0.0046 0.03066 0.02631 -0.1942 0.7181 0.0514
-8.250 0.0291 0.02869 0.02427 -0.1986 0.7132 0.0519
-8.000 0.0592 0.02640 0.02191 -0.2046 0.7092 0.0524
-7.750 0.0983 0.02338 0.01880 -0.2140 0.7034 0.0533
-7.500 0.1451 0.02033 0.01563 -0.2246 0.6964 0.0542
-7.250 0.1947 0.01774 0.01290 -0.2344 0.6897 0.0553
-7.000 0.2442 0.01556 0.01060 -0.2428 0.6837 0.0563
-6.750 0.2894 0.01388 0.00878 -0.2491 0.6761 0.0573
-6.500 0.3324 0.01240 0.00716 -0.2544 0.6695 0.0584
-6.250 0.3704 0.01158 0.00626 -0.2575 0.6646 0.0599
-6.000 0.4047 0.01115 0.00577 -0.2592 0.6591 0.0613
-5.750 0.4374 0.01086 0.00542 -0.2602 0.6531 0.0628
-5.500 0.4699 0.01059 0.00509 -0.2612 0.6475 0.0645
-5.250 0.5025 0.01033 0.00479 -0.2622 0.6409 0.0670
-4.750 0.5649 0.01000 0.00435 -0.2634 0.6228 0.0727
-4.500 0.5958 0.00988 0.00419 -0.2638 0.6146 0.0757
-4.000 0.6575 0.00966 0.00389 -0.2646 0.6019 0.0828
-3.750 0.6882 0.00956 0.00377 -0.2650 0.5949 0.0869
-3.500 0.7179 0.00953 0.00369 -0.2651 0.5874 0.0904
-3.250 0.7484 0.00946 0.00359 -0.2654 0.5804 0.0948
-3.000 0.7781 0.00944 0.00353 -0.2655 0.5719 0.0987
-2.750 0.8077 0.00943 0.00348 -0.2656 0.5645 0.1033
-2.500 0.8375 0.00941 0.00344 -0.2656 0.5574 0.1069
-2.250 0.8667 0.00943 0.00342 -0.2656 0.5487 0.1112
-2.000 0.8958 0.00946 0.00341 -0.2656 0.5408 0.1150
-1.750 0.9251 0.00947 0.00340 -0.2656 0.5325 0.1196
-1.250 0.9831 0.00954 0.00342 -0.2654 0.5189 0.1295
-1.000 1.0120 0.00958 0.00344 -0.2653 0.5124 0.1343
-0.750 1.0403 0.00966 0.00348 -0.2651 0.5052 0.1388
-0.500 1.0692 0.00971 0.00352 -0.2650 0.4994 0.1450
-0.250 1.0978 0.00976 0.00357 -0.2648 0.4922 0.1515
0.000 1.1252 0.00990 0.00365 -0.2645 0.4831 0.1572
0.250 1.1530 0.01000 0.00372 -0.2641 0.4720 0.1610
0.500 1.1794 0.01019 0.00384 -0.2636 0.4569 0.1656
0.750 1.2050 0.01043 0.00399 -0.2629 0.4385 0.1697
1.000 1.2301 0.01070 0.00415 -0.2621 0.4189 0.1724
1.250 1.2544 0.01102 0.00435 -0.2612 0.3959 0.1764
1.500 1.2782 0.01136 0.00458 -0.2603 0.3753 0.1804
1.750 1.3025 0.01166 0.00479 -0.2594 0.3604 0.1837
2.000 1.3267 0.01195 0.00501 -0.2585 0.3481 0.1865
2.250 1.3520 0.01216 0.00518 -0.2577 0.3401 0.1899
2.500 1.3769 0.01239 0.00538 -0.2569 0.3325 0.1937
2.750 1.4012 0.01263 0.00559 -0.2561 0.3254 0.1974
3.000 1.4266 0.01280 0.00575 -0.2553 0.3217 0.2008
3.250 1.4513 0.01300 0.00593 -0.2545 0.3174 0.2033
3.500 1.4755 0.01321 0.00613 -0.2536 0.3132 0.2075
3.750 1.4992 0.01343 0.00635 -0.2526 0.3095 0.2118
4.000 1.5224 0.01365 0.00657 -0.2515 0.3059 0.2156
4.250 1.5456 0.01381 0.00675 -0.2504 0.3043 0.2189
4.500 1.5675 0.01399 0.00694 -0.2490 0.3026 0.2214
4.750 1.5893 0.01417 0.00715 -0.2476 0.3006 0.2262
5.000 1.6104 0.01438 0.00738 -0.2462 0.2985 0.2305
5.250 1.6311 0.01462 0.00764 -0.2447 0.2962 0.2351
5.500 1.6515 0.01490 0.00792 -0.2431 0.2937 0.2390
5.750 1.6708 0.01521 0.00824 -0.2414 0.2910 0.2422
6.000 1.6895 0.01557 0.00860 -0.2397 0.2874 0.2477
6.250 1.7098 0.01586 0.00892 -0.2382 0.2852 0.2532
6.500 1.7303 0.01614 0.00924 -0.2368 0.2836 0.2585
6.750 1.7501 0.01646 0.00959 -0.2353 0.2817 0.2626
7.000 1.7696 0.01681 0.00997 -0.2338 0.2790 0.2689
7.250 1.7874 0.01724 0.01042 -0.2320 0.2755 0.2747
7.500 1.8042 0.01775 0.01093 -0.2302 0.2719 0.2798
7.750 1.8202 0.01831 0.01149 -0.2282 0.2680 0.2840
8.000 1.8389 0.01873 0.01196 -0.2267 0.2657 0.2915
8.250 1.8571 0.01921 0.01247 -0.2252 0.2624 0.2979
8.500 1.8732 0.01980 0.01308 -0.2234 0.2583 0.3029
8.750 1.8883 0.02049 0.01376 -0.2215 0.2539 0.3069
9.000 1.9028 0.02122 0.01451 -0.2197 0.2500 0.3129
9.250 1.9194 0.02185 0.01518 -0.2181 0.2461 0.3195
9.500 1.9335 0.02266 0.01600 -0.2162 0.2399 0.3251
9.750 1.9449 0.02368 0.01699 -0.2141 0.2332 0.3294
10.000 1.9570 0.02468 0.01799 -0.2122 0.2241 0.3350
10.250 1.9633 0.02614 0.01939 -0.2098 0.2103 0.3398
10.500 1.9645 0.02804 0.02120 -0.2069 0.1937 0.3439
10.750 1.9691 0.02977 0.02288 -0.2045 0.1829 0.3478
11.000 1.9745 0.03149 0.02459 -0.2023 0.1755 0.3521
11.250 1.9842 0.03291 0.02603 -0.2006 0.1710 0.3583
11.500 1.9922 0.03452 0.02766 -0.1988 0.1668 0.3637
11.750 2.0003 0.03616 0.02931 -0.1970 0.1627 0.3682
12.000 2.0107 0.03762 0.03082 -0.1956 0.1606 0.3724
12.250 2.0220 0.03904 0.03229 -0.1942 0.1585 0.3789
12.500 2.0310 0.04071 0.03400 -0.1928 0.1561 0.3854
12.750 2.0394 0.04247 0.03579 -0.1913 0.1537 0.3907
13.000 2.0472 0.04433 0.03769 -0.1899 0.1512 0.3971
13.250 2.0552 0.04622 0.03963 -0.1886 0.1490 0.4041
13.500 2.0667 0.04775 0.04123 -0.1875 0.1477 0.4107
13.750 2.0758 0.04959 0.04313 -0.1864 0.1460 0.4174
14.000 2.0847 0.05147 0.04506 -0.1853 0.1439 0.4264
14.250 2.0924 0.05350 0.04714 -0.1842 0.1417 0.4348
14.500 2.0975 0.05589 0.04958 -0.1831 0.1393 0.4445
15.000 2.1111 0.06038 0.05420 -0.1813 0.1350 0.4675
15.250 2.1194 0.06250 0.05639 -0.1805 0.1326 0.4864
15.500 2.1247 0.06501 0.05897 -0.1797 0.1297 0.5118
15.750 2.1277 0.06790 0.06193 -0.1790 0.1264 0.5484
16.000 2.1332 0.07053 0.06469 -0.1784 0.1237 0.6178
16.500 2.1410 0.07589 0.07042 -0.1772 0.1168 1.0000
16.750 2.1403 0.07939 0.07396 -0.1767 0.1131 1.0000
17.000 2.1413 0.08265 0.07724 -0.1763 0.1081 1.0000
17.250 2.1372 0.08674 0.08135 -0.1760 0.1033 1.0000
17.500 2.1345 0.09066 0.08529 -0.1758 0.0986 1.0000
17.750 2.1297 0.09490 0.08956 -0.1757 0.0944 1.0000
18.000 2.1256 0.09910 0.09381 -0.1758 0.0911 1.0000
18.250 2.1220 0.10323 0.09796 -0.1759 0.0880 1.0000
18.500 2.1167 0.10766 0.10246 -0.1763 0.0856 1.0000
18.750 2.1154 0.11142 0.10627 -0.1766 0.0834 1.0000
19.000 2.1100 0.11589 0.11079 -0.1772 0.0815 1.0000
19.250 2.1059 0.12010 0.11505 -0.1778 0.0796 1.0000
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Polar data table (+)
Polar graphs
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