GOE 439 AIRFOIL (goe439-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 439 AIRFOIL (goe439-il) Reynolds number: 100,000 Max Cl/Cd: 61.12 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe439-il-100000-n5.txt Download as CSV file: xf-goe439-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 439 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2765 0.09548 0.09110 -0.0298 1.0000 0.0355
-7.250 -0.2841 0.09393 0.08966 -0.0279 1.0000 0.0358
-7.000 -0.2960 0.09279 0.08864 -0.0251 1.0000 0.0362
-6.750 -0.2964 0.09068 0.08659 -0.0256 0.9972 0.0367
-6.500 -0.2644 0.08640 0.08227 -0.0376 0.9858 0.0412
-6.250 -0.2257 0.08208 0.07787 -0.0527 0.9733 0.0423
-6.000 -0.1931 0.07726 0.07297 -0.0615 0.9640 0.0425
-5.750 -0.1630 0.07230 0.06793 -0.0681 0.9555 0.0426
-5.500 -0.1410 0.06477 0.06036 -0.0714 0.9498 0.0312
-5.250 -0.1246 0.06109 0.05669 -0.0718 0.9411 0.0292
-5.000 -0.0934 0.05633 0.05182 -0.0781 0.9322 0.0277
-4.750 -0.0567 0.05106 0.04639 -0.0854 0.9246 0.0267
-4.500 -0.0215 0.04598 0.04110 -0.0914 0.9152 0.0262
-4.250 0.0135 0.04130 0.03615 -0.0965 0.9056 0.0276
-4.000 0.0542 0.03575 0.03015 -0.1019 0.8990 0.0289
-3.750 0.0865 0.03097 0.02486 -0.1045 0.8888 0.0291
-3.500 0.1221 0.02624 0.01936 -0.1068 0.8812 0.0301
-3.250 0.1540 0.02351 0.01605 -0.1080 0.8723 0.0334
-3.000 0.1844 0.02195 0.01414 -0.1085 0.8625 0.0375
-2.750 0.2182 0.02001 0.01156 -0.1091 0.8547 0.0423
-2.500 0.2470 0.01892 0.01033 -0.1092 0.8441 0.0506
-2.250 0.2764 0.01782 0.00895 -0.1092 0.8337 0.0595
-2.000 0.3064 0.01716 0.00810 -0.1092 0.8237 0.0704
-1.750 0.3359 0.01668 0.00751 -0.1093 0.8132 0.0808
-1.500 0.3635 0.01631 0.00706 -0.1089 0.8013 0.0935
-1.250 0.3912 0.01585 0.00650 -0.1086 0.7898 0.1070
-1.000 0.4194 0.01547 0.00602 -0.1083 0.7785 0.1273
-0.750 0.4472 0.01519 0.00568 -0.1081 0.7671 0.1552
-0.500 0.4744 0.01496 0.00541 -0.1078 0.7549 0.1822
-0.250 0.5015 0.01468 0.00524 -0.1076 0.7421 0.2305
0.000 0.5262 0.01381 0.00518 -0.1071 0.7297 0.4975
0.500 0.5893 0.01302 0.00482 -0.1077 0.7041 1.0000
0.750 0.6155 0.01314 0.00475 -0.1071 0.6911 1.0000
1.000 0.6416 0.01328 0.00470 -0.1066 0.6778 1.0000
1.250 0.6675 0.01342 0.00469 -0.1060 0.6643 1.0000
1.500 0.6932 0.01358 0.00470 -0.1054 0.6505 1.0000
1.750 0.7186 0.01374 0.00475 -0.1048 0.6363 1.0000
2.000 0.7440 0.01391 0.00482 -0.1042 0.6222 1.0000
2.250 0.7693 0.01409 0.00491 -0.1036 0.6080 1.0000
2.500 0.7946 0.01429 0.00501 -0.1030 0.5940 1.0000
2.750 0.8197 0.01450 0.00514 -0.1024 0.5803 1.0000
3.000 0.8448 0.01473 0.00532 -0.1018 0.5667 1.0000
3.250 0.8698 0.01497 0.00550 -0.1013 0.5536 1.0000
3.500 0.8947 0.01523 0.00571 -0.1007 0.5407 1.0000
3.750 0.9195 0.01551 0.00597 -0.1001 0.5285 1.0000
4.000 0.9443 0.01580 0.00622 -0.0995 0.5168 1.0000
4.250 0.9689 0.01611 0.00652 -0.0989 0.5047 1.0000
4.500 0.9934 0.01643 0.00687 -0.0983 0.4930 1.0000
4.750 1.0178 0.01676 0.00726 -0.0977 0.4819 1.0000
5.000 1.0422 0.01711 0.00762 -0.0971 0.4715 1.0000
5.250 1.0664 0.01747 0.00805 -0.0965 0.4608 1.0000
5.500 1.0904 0.01784 0.00850 -0.0958 0.4499 1.0000
5.750 1.1142 0.01823 0.00899 -0.0952 0.4395 1.0000
6.000 1.1379 0.01863 0.00946 -0.0945 0.4293 1.0000
6.250 1.1611 0.01903 0.01001 -0.0937 0.4182 1.0000
6.500 1.1836 0.01944 0.01054 -0.0928 0.4055 1.0000
6.750 1.2034 0.01981 0.01100 -0.0914 0.3865 1.0000
7.000 1.2208 0.02020 0.01143 -0.0897 0.3597 1.0000
7.250 1.2351 0.02072 0.01187 -0.0875 0.3223 1.0000
7.500 1.2486 0.02145 0.01249 -0.0854 0.2779 1.0000
7.750 1.2553 0.02281 0.01341 -0.0824 0.1989 1.0000
8.000 1.2422 0.02616 0.01561 -0.0777 0.0506 1.0000
8.250 1.2427 0.02831 0.01756 -0.0742 0.0345 1.0000
8.500 1.2475 0.02982 0.01923 -0.0710 0.0295 1.0000
8.750 1.2517 0.03133 0.02096 -0.0680 0.0269 1.0000
9.000 1.2520 0.03312 0.02296 -0.0649 0.0249 1.0000
9.250 1.2464 0.03540 0.02551 -0.0617 0.0232 1.0000
9.500 1.2443 0.03753 0.02782 -0.0592 0.0219 1.0000
9.750 1.2440 0.03967 0.03017 -0.0572 0.0208 1.0000
10.000 1.2411 0.04218 0.03287 -0.0554 0.0202 1.0000
10.250 1.2377 0.04492 0.03578 -0.0539 0.0196 1.0000
10.500 1.2353 0.04773 0.03874 -0.0527 0.0190 1.0000
10.750 1.2345 0.05050 0.04165 -0.0516 0.0185 1.0000
11.000 1.2360 0.05314 0.04440 -0.0505 0.0176 1.0000
11.250 1.2396 0.05567 0.04702 -0.0495 0.0166 1.0000
11.500 1.2439 0.05821 0.04965 -0.0486 0.0155 1.0000
11.750 1.2518 0.06056 0.05207 -0.0474 0.0147 1.0000
12.000 1.2652 0.06280 0.05438 -0.0458 0.0141 1.0000
12.250 1.2827 0.06534 0.05705 -0.0442 0.0137 1.0000
12.500 1.2981 0.06874 0.06065 -0.0429 0.0133 1.0000
12.750 1.3037 0.07289 0.06508 -0.0422 0.0131 1.0000
13.000 1.3013 0.07762 0.07010 -0.0418 0.0130 1.0000
13.250 1.2920 0.08183 0.07454 -0.0422 0.0129 1.0000
13.500 1.2814 0.08612 0.07909 -0.0429 0.0127 1.0000
13.750 1.2705 0.09080 0.08403 -0.0441 0.0127 1.0000
14.000 1.2582 0.09571 0.08919 -0.0458 0.0126 1.0000
14.250 1.2458 0.10103 0.09474 -0.0479 0.0125 1.0000
14.500 1.2326 0.10673 0.10067 -0.0506 0.0124 1.0000
14.750 1.2194 0.11280 0.10696 -0.0537 0.0124 1.0000
15.000 1.2061 0.11924 0.11361 -0.0572 0.0124 1.0000
15.250 1.1927 0.12606 0.12062 -0.0611 0.0125 1.0000
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Polar data table (+)
Polar graphs
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