GOE 12K AIRFOIL (goe12k-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 12K AIRFOIL (goe12k-il) Reynolds number: 500,000 Max Cl/Cd: 114.04 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe12k-il-500000.txt Download as CSV file: xf-goe12k-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 12K AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2685 0.09487 0.09223 -0.1026 0.9655 0.0372
-10.500 -0.2850 0.08966 0.08704 -0.1035 0.9602 0.0370
-10.250 -0.2851 0.08491 0.08229 -0.1060 0.9580 0.0371
-10.000 -0.2754 0.08224 0.07962 -0.1077 0.9567 0.0374
-9.750 -0.2630 0.07993 0.07730 -0.1095 0.9556 0.0379
-9.500 -0.2781 0.07019 0.06756 -0.1178 0.9540 0.0347
-9.250 -0.3223 0.06287 0.06025 -0.1212 0.9448 0.0345
-9.000 -0.5341 0.02937 0.02487 -0.1107 0.9243 0.0365
-8.750 -0.5273 0.02785 0.02320 -0.1077 0.9208 0.0374
-8.500 -0.4957 0.02862 0.02411 -0.1085 0.9198 0.0382
-8.250 -0.4696 0.02845 0.02393 -0.1087 0.9186 0.0389
-8.000 -0.4406 0.02849 0.02396 -0.1092 0.9177 0.0404
-7.750 -0.4219 0.02654 0.02161 -0.1083 0.9165 0.0424
-7.500 -0.4028 0.02442 0.01913 -0.1075 0.9156 0.0442
-7.250 -0.4142 0.02458 0.01928 -0.0997 0.9076 0.0446
-7.000 -0.3891 0.02443 0.01917 -0.0996 0.9059 0.0457
-6.750 -0.3618 0.02420 0.01894 -0.0998 0.9048 0.0470
-6.500 -0.3362 0.02353 0.01814 -0.0996 0.9036 0.0487
-6.250 -0.3093 0.02284 0.01724 -0.0996 0.9027 0.0504
-6.000 -0.2788 0.02282 0.01705 -0.1000 0.9020 0.0515
-5.750 -0.2568 0.02016 0.01418 -0.0997 0.9014 0.0535
-5.500 -0.2647 0.02038 0.01437 -0.0924 0.8932 0.0540
-5.250 -0.2410 0.01991 0.01385 -0.0917 0.8912 0.0552
-5.000 -0.2135 0.01932 0.01319 -0.0918 0.8900 0.0564
-4.750 -0.1849 0.01881 0.01260 -0.0920 0.8890 0.0581
-4.500 -0.1553 0.01824 0.01192 -0.0924 0.8882 0.0594
-4.250 -0.1247 0.01766 0.01123 -0.0930 0.8876 0.0602
-4.000 -0.0930 0.01727 0.01077 -0.0938 0.8870 0.0610
-3.750 -0.0615 0.01636 0.00976 -0.0947 0.8865 0.0623
-3.500 -0.0290 0.01551 0.00889 -0.0959 0.8861 0.0636
-3.250 -0.0406 0.01592 0.00928 -0.0875 0.8768 0.0639
-3.000 -0.0128 0.01549 0.00884 -0.0875 0.8754 0.0649
-2.750 0.0188 0.01503 0.00837 -0.0883 0.8743 0.0662
-2.500 0.0523 0.01459 0.00794 -0.0895 0.8734 0.0679
-2.250 0.0875 0.01411 0.00745 -0.0910 0.8727 0.0693
-2.000 0.1229 0.01367 0.00699 -0.0926 0.8720 0.0704
-1.750 0.1589 0.01327 0.00659 -0.0943 0.8714 0.0718
-1.500 0.1940 0.01298 0.00628 -0.0959 0.8708 0.0729
-1.250 0.2294 0.01254 0.00585 -0.0976 0.8701 0.0751
-1.000 0.2092 0.01305 0.00635 -0.0870 0.8603 0.0756
-0.750 0.2394 0.01276 0.00610 -0.0875 0.8587 0.0789
-0.500 0.2727 0.01249 0.00583 -0.0887 0.8576 0.0824
0.000 0.3454 0.01185 0.00531 -0.0923 0.8560 0.1026
0.250 0.3791 0.01127 0.00517 -0.0938 0.8551 0.2218
0.500 0.4040 0.01019 0.00515 -0.0936 0.8540 0.5638
0.750 0.4035 0.00983 0.00581 -0.0876 0.8469 0.8575
1.000 0.7757 0.00947 0.00562 -0.1651 0.8702 0.9932
1.250 0.8329 0.00919 0.00534 -0.1715 0.8658 0.9986
1.500 0.8525 0.00904 0.00519 -0.1697 0.8589 1.0000
1.750 0.8835 0.00872 0.00483 -0.1701 0.8503 1.0000
2.000 0.8971 0.00845 0.00452 -0.1667 0.8393 1.0000
2.250 0.8844 0.00842 0.00450 -0.1575 0.8296 1.0000
2.500 0.8935 0.00827 0.00434 -0.1531 0.8204 1.0000
2.750 0.8927 0.00823 0.00429 -0.1466 0.8106 1.0000
3.000 0.8962 0.00823 0.00431 -0.1410 0.8007 1.0000
3.250 0.9081 0.00820 0.00427 -0.1373 0.7897 1.0000
3.500 0.9189 0.00819 0.00424 -0.1333 0.7748 1.0000
3.750 0.9324 0.00821 0.00419 -0.1300 0.7534 1.0000
4.000 0.9465 0.00830 0.00418 -0.1267 0.7260 1.0000
4.250 0.9499 0.00858 0.00425 -0.1211 0.6813 1.0000
4.500 0.9267 0.00933 0.00456 -0.1098 0.5869 1.0000
4.750 0.8974 0.01049 0.00522 -0.0978 0.4985 1.0000
5.000 0.8902 0.01138 0.00582 -0.0907 0.4450 1.0000
5.250 0.8955 0.01200 0.00627 -0.0863 0.4113 1.0000
5.500 0.9043 0.01255 0.00669 -0.0826 0.3792 1.0000
5.750 0.9124 0.01316 0.00712 -0.0789 0.3377 1.0000
6.000 0.9147 0.01407 0.00766 -0.0743 0.2633 1.0000
6.250 0.9161 0.01518 0.00833 -0.0697 0.1859 1.0000
6.500 0.9238 0.01611 0.00894 -0.0663 0.1298 1.0000
6.750 0.9369 0.01678 0.00946 -0.0639 0.1061 1.0000
7.000 0.9517 0.01736 0.00995 -0.0617 0.0947 1.0000
7.250 0.9692 0.01778 0.01038 -0.0600 0.0886 1.0000
7.500 0.9845 0.01835 0.01091 -0.0580 0.0830 1.0000
7.750 1.0018 0.01880 0.01140 -0.0563 0.0793 1.0000
8.000 1.0194 0.01924 0.01185 -0.0547 0.0758 1.0000
8.250 1.0348 0.01982 0.01242 -0.0528 0.0721 1.0000
8.500 1.0493 0.02047 0.01309 -0.0507 0.0689 1.0000
8.750 1.0679 0.02085 0.01351 -0.0494 0.0660 1.0000
9.000 1.0845 0.02135 0.01404 -0.0478 0.0633 1.0000
9.250 1.0985 0.02206 0.01474 -0.0457 0.0601 1.0000
9.500 1.1134 0.02271 0.01543 -0.0439 0.0573 1.0000
9.750 1.1313 0.02314 0.01591 -0.0425 0.0544 1.0000
10.000 1.1475 0.02369 0.01646 -0.0410 0.0515 1.0000
10.250 1.1593 0.02457 0.01736 -0.0388 0.0483 1.0000
10.500 1.1774 0.02500 0.01785 -0.0375 0.0458 1.0000
10.750 1.1940 0.02552 0.01837 -0.0361 0.0428 1.0000
11.000 1.2040 0.02654 0.01940 -0.0338 0.0404 1.0000
11.250 1.2213 0.02703 0.01996 -0.0325 0.0380 1.0000
11.500 1.2367 0.02765 0.02060 -0.0310 0.0359 1.0000
11.750 1.2448 0.02882 0.02176 -0.0285 0.0338 1.0000
12.000 1.2595 0.02951 0.02255 -0.0270 0.0325 1.0000
12.250 1.2740 0.03021 0.02330 -0.0255 0.0307 1.0000
12.500 1.2854 0.03115 0.02425 -0.0236 0.0294 1.0000
12.750 1.2905 0.03261 0.02573 -0.0211 0.0280 1.0000
13.000 1.3038 0.03343 0.02666 -0.0195 0.0269 1.0000
13.250 1.3138 0.03450 0.02782 -0.0177 0.0259 1.0000
13.500 1.3235 0.03561 0.02899 -0.0159 0.0251 1.0000
13.750 1.3317 0.03686 0.03028 -0.0140 0.0244 1.0000
14.000 1.3331 0.03873 0.03218 -0.0115 0.0232 1.0000
14.250 1.3407 0.04009 0.03367 -0.0097 0.0228 1.0000
14.500 1.3497 0.04132 0.03501 -0.0082 0.0220 1.0000
14.750 1.3558 0.04284 0.03664 -0.0064 0.0213 1.0000
15.000 1.3621 0.04436 0.03823 -0.0048 0.0208 1.0000
15.250 1.3661 0.04612 0.04008 -0.0031 0.0204 1.0000
15.500 1.3686 0.04804 0.04206 -0.0015 0.0198 1.0000
15.750 1.3690 0.05024 0.04433 0.0002 0.0195 1.0000
16.000 1.3651 0.05300 0.04721 0.0021 0.0190 1.0000
16.250 1.3671 0.05514 0.04951 0.0033 0.0187 1.0000
16.500 1.3671 0.05757 0.05209 0.0044 0.0184 1.0000
16.750 1.3646 0.06035 0.05502 0.0056 0.0182 1.0000
17.000 1.3647 0.06288 0.05767 0.0062 0.0176 1.0000
17.250 1.3605 0.06604 0.06097 0.0069 0.0174 1.0000
17.500 1.3574 0.06915 0.06419 0.0071 0.0170 1.0000
17.750 1.3514 0.07274 0.06792 0.0073 0.0169 1.0000
18.000 1.3452 0.07648 0.07176 0.0071 0.0166 1.0000
18.250 1.3386 0.08042 0.07581 0.0065 0.0164 1.0000
18.500 1.3327 0.08440 0.07987 0.0056 0.0161 1.0000
18.750 1.3230 0.08910 0.08470 0.0044 0.0160 1.0000
19.000 1.3082 0.09466 0.09039 0.0028 0.0158 1.0000
19.250 1.2959 0.10009 0.09597 0.0009 0.0158 1.0000
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