GOE 629 AIRFOIL (goe629-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 629 AIRFOIL (goe629-il) Reynolds number: 100,000 Max Cl/Cd: 50.33 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe629-il-100000.txt Download as CSV file: xf-goe629-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 629 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3892 0.09675 0.09121 -0.0333 1.0000 0.2082
-9.000 -0.3872 0.09478 0.08927 -0.0317 1.0000 0.2137
-8.750 -0.4740 0.09373 0.08849 -0.0319 1.0000 0.2199
-8.500 -0.6580 0.06672 0.06132 -0.0403 1.0000 0.1539
-8.250 -0.6672 0.06286 0.05739 -0.0383 1.0000 0.1534
-8.000 -0.6784 0.05870 0.05311 -0.0363 1.0000 0.1527
-7.750 -0.6909 0.05410 0.04828 -0.0344 1.0000 0.1522
-7.500 -0.7027 0.04929 0.04309 -0.0325 1.0000 0.1525
-7.250 -0.7088 0.04512 0.03840 -0.0304 1.0000 0.1537
-7.000 -0.7049 0.04194 0.03490 -0.0286 1.0000 0.1553
-6.750 -0.6890 0.04085 0.03392 -0.0273 1.0000 0.1575
-6.500 -0.6755 0.03966 0.03265 -0.0258 1.0000 0.1599
-6.250 -0.6634 0.03805 0.03084 -0.0242 1.0000 0.1629
-6.000 -0.6517 0.03608 0.02853 -0.0228 1.0000 0.1657
-5.750 -0.6391 0.03420 0.02620 -0.0212 1.0000 0.1684
-5.500 -0.6204 0.03256 0.02421 -0.0207 0.9987 0.1716
-5.250 -0.5809 0.03184 0.02353 -0.0238 0.9920 0.1762
-5.000 -0.5438 0.03085 0.02230 -0.0263 0.9846 0.1810
-4.750 -0.5086 0.03002 0.02096 -0.0282 0.9769 0.1867
-4.500 -0.4701 0.02915 0.02018 -0.0310 0.9701 0.1924
-4.250 -0.4370 0.02852 0.01940 -0.0324 0.9615 0.1984
-4.000 -0.3958 0.02785 0.01854 -0.0353 0.9549 0.2062
-3.750 -0.3658 0.02740 0.01810 -0.0361 0.9452 0.2137
-3.500 -0.3229 0.02687 0.01744 -0.0391 0.9392 0.2234
-3.250 -0.2955 0.02648 0.01705 -0.0393 0.9289 0.2325
-3.000 -0.2505 0.02607 0.01667 -0.0427 0.9230 0.2454
-2.750 -0.2245 0.02573 0.01625 -0.0425 0.9118 0.2566
-2.250 -0.1557 0.02511 0.01577 -0.0452 0.8950 0.2836
-2.000 -0.1100 0.02470 0.01543 -0.0484 0.8898 0.3013
-1.750 -0.0868 0.02448 0.01529 -0.0477 0.8780 0.3158
-1.500 -0.0416 0.02403 0.01495 -0.0507 0.8731 0.3401
-1.250 -0.0202 0.02386 0.01490 -0.0497 0.8612 0.3620
-1.000 0.0242 0.02319 0.01455 -0.0524 0.8565 0.4019
-0.750 0.0436 0.02292 0.01459 -0.0508 0.8447 0.4466
-0.500 0.0856 0.02187 0.01427 -0.0528 0.8403 0.5680
-0.250 0.2189 0.02083 0.01446 -0.0702 0.8426 0.9428
0.000 0.3634 0.02003 0.01347 -0.0910 0.8436 0.9986
0.250 0.4172 0.01930 0.01261 -0.0952 0.8375 1.0000
0.500 0.4382 0.01915 0.01237 -0.0939 0.8246 1.0000
0.750 0.4593 0.01908 0.01222 -0.0925 0.8124 1.0000
1.000 0.5019 0.01855 0.01161 -0.0946 0.8056 1.0000
1.250 0.5183 0.01862 0.01162 -0.0923 0.7922 1.0000
1.500 0.5435 0.01854 0.01148 -0.0915 0.7814 1.0000
1.750 0.5775 0.01824 0.01112 -0.0920 0.7723 1.0000
2.000 0.5953 0.01837 0.01121 -0.0899 0.7595 1.0000
2.250 0.6234 0.01826 0.01106 -0.0895 0.7493 1.0000
2.500 0.6522 0.01813 0.01087 -0.0891 0.7385 1.0000
2.750 0.6710 0.01828 0.01101 -0.0871 0.7256 1.0000
3.000 0.6969 0.01828 0.01096 -0.0863 0.7144 1.0000
3.250 0.7275 0.01815 0.01078 -0.0861 0.7034 1.0000
3.500 0.7464 0.01832 0.01095 -0.0841 0.6896 1.0000
3.750 0.7685 0.01845 0.01106 -0.0826 0.6764 1.0000
4.000 0.7942 0.01850 0.01108 -0.0817 0.6635 1.0000
4.250 0.8215 0.01848 0.01099 -0.0809 0.6496 1.0000
4.500 0.8459 0.01849 0.01093 -0.0796 0.6334 1.0000
4.750 0.8683 0.01856 0.01095 -0.0780 0.6164 1.0000
5.000 0.8905 0.01869 0.01102 -0.0763 0.5995 1.0000
5.250 0.9128 0.01887 0.01114 -0.0748 0.5829 1.0000
5.500 0.9332 0.01908 0.01131 -0.0730 0.5655 1.0000
5.750 0.9525 0.01932 0.01150 -0.0710 0.5477 1.0000
6.000 0.9714 0.01957 0.01172 -0.0689 0.5299 1.0000
6.250 0.9901 0.01985 0.01197 -0.0668 0.5125 1.0000
6.500 1.0091 0.02015 0.01224 -0.0649 0.4958 1.0000
6.750 1.0273 0.02046 0.01252 -0.0628 0.4791 1.0000
7.000 1.0446 0.02076 0.01282 -0.0606 0.4624 1.0000
7.250 1.0600 0.02106 0.01313 -0.0580 0.4450 1.0000
7.500 1.0731 0.02134 0.01342 -0.0551 0.4263 1.0000
7.750 1.0850 0.02163 0.01370 -0.0520 0.4065 1.0000
8.000 1.0962 0.02193 0.01396 -0.0487 0.3858 1.0000
8.250 1.1074 0.02233 0.01422 -0.0456 0.3649 1.0000
8.500 1.1150 0.02286 0.01470 -0.0420 0.3427 1.0000
8.750 1.1216 0.02346 0.01523 -0.0383 0.3205 1.0000
9.000 1.1279 0.02414 0.01578 -0.0347 0.2995 1.0000
9.250 1.1308 0.02485 0.01642 -0.0306 0.2795 1.0000
9.500 1.1334 0.02560 0.01716 -0.0266 0.2603 1.0000
9.750 1.1361 0.02642 0.01796 -0.0228 0.2417 1.0000
10.000 1.1389 0.02735 0.01883 -0.0192 0.2240 1.0000
10.250 1.1417 0.02839 0.01981 -0.0160 0.2074 1.0000
10.500 1.1441 0.02958 0.02091 -0.0128 0.1913 1.0000
10.750 1.1460 0.03093 0.02217 -0.0099 0.1757 1.0000
11.000 1.1475 0.03249 0.02362 -0.0071 0.1601 1.0000
11.250 1.1490 0.03423 0.02522 -0.0046 0.1448 1.0000
11.500 1.1517 0.03605 0.02695 -0.0022 0.1310 1.0000
11.750 1.1573 0.03784 0.02874 -0.0002 0.1196 1.0000
12.000 1.1686 0.03960 0.03048 0.0013 0.1110 1.0000
12.250 1.1867 0.04114 0.03182 0.0021 0.1040 1.0000
12.500 1.1961 0.04293 0.03381 0.0037 0.0990 1.0000
12.750 1.2101 0.04448 0.03536 0.0048 0.0944 1.0000
13.000 1.2369 0.04634 0.03717 0.0049 0.0904 1.0000
13.250 1.2446 0.04837 0.03945 0.0064 0.0879 1.0000
13.500 1.2527 0.05039 0.04163 0.0077 0.0853 1.0000
13.750 1.2670 0.05220 0.04346 0.0085 0.0826 1.0000
14.000 1.2891 0.05472 0.04598 0.0086 0.0801 1.0000
14.250 1.2817 0.05747 0.04906 0.0106 0.0792 1.0000
14.500 1.2735 0.06052 0.05241 0.0122 0.0784 1.0000
14.750 1.2622 0.06387 0.05605 0.0136 0.0776 1.0000
15.000 1.2479 0.06762 0.06008 0.0145 0.0769 1.0000
15.250 1.2307 0.07179 0.06451 0.0150 0.0765 1.0000
15.500 1.2088 0.07663 0.06962 0.0148 0.0762 1.0000
15.750 1.1805 0.08248 0.07575 0.0138 0.0763 1.0000
16.000 1.1448 0.08977 0.08333 0.0114 0.0767 1.0000
16.250 1.1012 0.09904 0.09286 0.0072 0.0776 1.0000
16.500 1.0493 0.11102 0.10509 0.0007 0.0789 1.0000
16.750 0.9977 0.12501 0.11923 -0.0073 0.0802 1.0000
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