GOE 14K AIRFOIL (goe14k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 14K AIRFOIL (goe14k-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.07 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe14k-il-1000000-n5.txt Download as CSV file: xf-goe14k-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 14K 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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.6069 0.10688 0.10473 -0.0881 0.9833 0.0051
-16.000 -0.6798 0.08976 0.08748 -0.0965 0.9823 0.0049
-15.750 -0.8279 0.06021 0.05757 -0.1126 0.9809 0.0045
-15.500 -0.8648 0.04685 0.04392 -0.1242 0.9800 0.0043
-15.250 -0.8959 0.03805 0.03485 -0.1319 0.9788 0.0045
-15.000 -0.9006 0.03485 0.03148 -0.1330 0.9781 0.0042
-14.750 -0.9193 0.03260 0.02910 -0.1287 0.9742 0.0045
-14.500 -0.9173 0.03109 0.02745 -0.1270 0.9720 0.0043
-14.250 -0.9182 0.02917 0.02540 -0.1250 0.9704 0.0044
-14.000 -0.9148 0.02746 0.02354 -0.1232 0.9691 0.0045
-13.750 -0.9066 0.02599 0.02193 -0.1218 0.9683 0.0046
-13.500 -0.9085 0.02534 0.02123 -0.1168 0.9638 0.0048
-13.250 -0.9028 0.02435 0.02013 -0.1138 0.9607 0.0048
-13.000 -0.8881 0.02350 0.01919 -0.1124 0.9590 0.0050
-12.750 -0.8757 0.02237 0.01793 -0.1107 0.9576 0.0050
-12.500 -0.8557 0.02167 0.01715 -0.1101 0.9567 0.0053
-12.250 -0.8620 0.02120 0.01659 -0.1035 0.9494 0.0053
-12.000 -0.8496 0.02037 0.01563 -0.1012 0.9468 0.0054
-11.750 -0.8319 0.01970 0.01486 -0.0998 0.9452 0.0056
-11.500 -0.8137 0.01901 0.01409 -0.0985 0.9439 0.0057
-11.250 -0.8166 0.01866 0.01365 -0.0923 0.9359 0.0058
-11.000 -0.8017 0.01794 0.01283 -0.0902 0.9332 0.0059
-10.750 -0.7808 0.01723 0.01204 -0.0893 0.9316 0.0063
-10.500 -0.7576 0.01651 0.01124 -0.0890 0.9303 0.0065
-10.250 -0.7444 0.01616 0.01084 -0.0862 0.9248 0.0068
-10.000 -0.7230 0.01561 0.01022 -0.0853 0.9216 0.0070
-9.750 -0.6974 0.01506 0.00959 -0.0852 0.9196 0.0074
-9.500 -0.6693 0.01456 0.00899 -0.0858 0.9179 0.0077
-9.250 -0.6405 0.01398 0.00835 -0.0865 0.9164 0.0082
-9.000 -0.6155 0.01352 0.00784 -0.0863 0.9136 0.0085
-8.750 -0.5927 0.01315 0.00741 -0.0856 0.9098 0.0089
-8.500 -0.5651 0.01275 0.00695 -0.0859 0.9070 0.0096
-8.250 -0.5346 0.01237 0.00650 -0.0869 0.9049 0.0102
-8.000 -0.5027 0.01192 0.00602 -0.0883 0.9030 0.0115
-7.750 -0.4696 0.01155 0.00560 -0.0899 0.9013 0.0124
-7.500 -0.4475 0.01131 0.00530 -0.0889 0.8973 0.0129
-7.250 -0.4226 0.01097 0.00495 -0.0885 0.8936 0.0148
-7.000 -0.3937 0.01070 0.00464 -0.0891 0.8908 0.0164
-6.750 -0.3628 0.01039 0.00430 -0.0902 0.8884 0.0188
-6.500 -0.3300 0.01008 0.00399 -0.0917 0.8865 0.0236
-6.250 -0.3099 0.00988 0.00381 -0.0902 0.8826 0.0287
-6.000 -0.2860 0.00970 0.00367 -0.0895 0.8790 0.0370
-5.750 -0.2583 0.00955 0.00351 -0.0898 0.8761 0.0407
-5.500 -0.2277 0.00942 0.00333 -0.0906 0.8737 0.0419
-5.250 -0.1950 0.00923 0.00312 -0.0920 0.8717 0.0460
-5.000 -0.1744 0.00912 0.00301 -0.0905 0.8687 0.0492
-4.750 -0.1531 0.00902 0.00290 -0.0892 0.8656 0.0512
-4.500 -0.1286 0.00893 0.00278 -0.0887 0.8630 0.0533
-4.250 -0.1017 0.00886 0.00267 -0.0887 0.8607 0.0551
-4.000 -0.0723 0.00873 0.00253 -0.0892 0.8587 0.0573
-3.750 -0.0406 0.00858 0.00236 -0.0904 0.8571 0.0603
-3.500 -0.0159 0.00848 0.00226 -0.0898 0.8550 0.0619
-3.250 0.0029 0.00841 0.00219 -0.0879 0.8524 0.0636
-3.000 0.0250 0.00834 0.00211 -0.0867 0.8500 0.0653
-2.750 0.0496 0.00827 0.00203 -0.0862 0.8478 0.0673
-2.500 0.0769 0.00815 0.00194 -0.0862 0.8458 0.0745
-2.250 0.1070 0.00797 0.00184 -0.0870 0.8441 0.0958
-2.000 0.1392 0.00771 0.00175 -0.0884 0.8428 0.1468
-1.750 0.1718 0.00750 0.00168 -0.0899 0.8415 0.1911
-1.500 0.1889 0.00739 0.00167 -0.0876 0.8386 0.2188
-1.250 0.2064 0.00725 0.00166 -0.0854 0.8352 0.2567
-1.000 0.2294 0.00713 0.00164 -0.0844 0.8321 0.2909
-0.750 0.2561 0.00701 0.00161 -0.0844 0.8289 0.3233
-0.250 0.3010 0.00674 0.00161 -0.0823 0.8226 0.4093
0.000 0.3204 0.00661 0.00162 -0.0806 0.8198 0.4530
0.250 0.3413 0.00643 0.00162 -0.0792 0.8165 0.5112
0.500 0.3516 0.00585 0.00160 -0.0755 0.8134 0.6841
1.000 0.5242 0.00616 0.00269 -0.1029 0.7998 0.9257
1.250 0.5372 0.00638 0.00291 -0.0993 0.7920 0.9417
1.500 0.5629 0.00654 0.00304 -0.0989 0.7823 0.9454
1.750 0.5690 0.00673 0.00321 -0.0937 0.7688 0.9544
2.000 0.5939 0.00695 0.00336 -0.0931 0.7444 0.9570
2.250 0.5770 0.00743 0.00361 -0.0826 0.6858 0.9656
2.500 0.5827 0.00827 0.00404 -0.0779 0.5967 0.9684
2.750 0.5736 0.00942 0.00462 -0.0701 0.4636 0.9730
3.000 0.5806 0.01005 0.00501 -0.0657 0.4069 0.9770
3.250 0.6091 0.01042 0.00523 -0.0664 0.3688 0.9782
3.500 0.6335 0.01081 0.00545 -0.0661 0.3272 0.9796
3.750 0.6543 0.01128 0.00571 -0.0650 0.2765 0.9816
4.000 0.6694 0.01189 0.00616 -0.0626 0.2371 0.9860
4.250 0.6960 0.01231 0.00636 -0.0629 0.1875 0.9868
4.500 0.7230 0.01260 0.00654 -0.0633 0.1606 0.9877
4.750 0.7429 0.01304 0.00678 -0.0621 0.1181 0.9886
5.000 0.7630 0.01342 0.00702 -0.0610 0.0895 0.9895
5.250 0.7848 0.01372 0.00726 -0.0601 0.0743 0.9905
5.750 0.8283 0.01422 0.00772 -0.0582 0.0621 0.9923
6.000 0.8486 0.01450 0.00797 -0.0571 0.0569 0.9931
6.250 0.8691 0.01479 0.00825 -0.0559 0.0496 0.9941
6.500 0.8912 0.01506 0.00852 -0.0551 0.0462 0.9949
6.750 0.9132 0.01532 0.00875 -0.0543 0.0365 0.9953
7.000 0.9326 0.01572 0.00906 -0.0531 0.0247 0.9957
7.250 0.9531 0.01603 0.00937 -0.0521 0.0204 0.9962
7.500 0.9742 0.01638 0.00970 -0.0512 0.0174 0.9968
7.750 0.9960 0.01669 0.01004 -0.0505 0.0157 0.9975
8.000 1.0154 0.01710 0.01043 -0.0493 0.0132 0.9980
8.250 1.0354 0.01743 0.01079 -0.0482 0.0123 0.9984
8.500 1.0557 0.01783 0.01120 -0.0472 0.0112 0.9989
8.750 1.0769 0.01823 0.01163 -0.0464 0.0100 0.9995
9.000 1.0972 0.01865 0.01208 -0.0455 0.0091 0.9999
9.250 1.1144 0.01906 0.01252 -0.0440 0.0091 1.0000
9.500 1.1294 0.01952 0.01299 -0.0419 0.0085 1.0000
9.750 1.1438 0.02002 0.01354 -0.0398 0.0079 1.0000
10.000 1.1590 0.02046 0.01402 -0.0378 0.0073 1.0000
10.250 1.1736 0.02096 0.01456 -0.0358 0.0073 1.0000
10.500 1.1878 0.02150 0.01514 -0.0337 0.0069 1.0000
10.750 1.2003 0.02217 0.01584 -0.0314 0.0063 1.0000
11.000 1.2145 0.02270 0.01642 -0.0294 0.0063 1.0000
11.250 1.2279 0.02331 0.01709 -0.0273 0.0062 1.0000
11.500 1.2405 0.02398 0.01782 -0.0251 0.0060 1.0000
11.750 1.2540 0.02455 0.01844 -0.0232 0.0056 1.0000
12.000 1.2669 0.02519 0.01915 -0.0212 0.0054 1.0000
12.250 1.2783 0.02594 0.01996 -0.0189 0.0052 1.0000
12.500 1.2889 0.02674 0.02081 -0.0167 0.0050 1.0000
12.750 1.2985 0.02766 0.02179 -0.0143 0.0048 1.0000
13.000 1.3064 0.02867 0.02289 -0.0118 0.0048 1.0000
13.250 1.3173 0.02947 0.02375 -0.0098 0.0046 1.0000
13.500 1.3278 0.03028 0.02462 -0.0077 0.0046 1.0000
13.750 1.3323 0.03158 0.02603 -0.0050 0.0046 1.0000
14.000 1.3413 0.03254 0.02707 -0.0029 0.0045 1.0000
14.250 1.3509 0.03347 0.02807 -0.0010 0.0042 1.0000
14.500 1.3595 0.03450 0.02917 0.0010 0.0041 1.0000
14.750 1.3627 0.03598 0.03075 0.0035 0.0040 1.0000
15.000 1.3700 0.03713 0.03198 0.0055 0.0039 1.0000
15.250 1.3715 0.03878 0.03374 0.0079 0.0040 1.0000
15.500 1.3771 0.04013 0.03518 0.0098 0.0039 1.0000
15.750 1.3811 0.04165 0.03679 0.0117 0.0037 1.0000
16.000 1.3816 0.04352 0.03876 0.0138 0.0036 1.0000
16.250 1.3843 0.04523 0.04055 0.0155 0.0036 1.0000
16.500 1.3791 0.04774 0.04318 0.0176 0.0036 1.0000
16.750 1.3714 0.05062 0.04617 0.0195 0.0034 1.0000
17.000 1.3694 0.05306 0.04874 0.0210 0.0035 1.0000
17.250 1.3649 0.05584 0.05162 0.0221 0.0034 1.0000
17.500 1.3567 0.05921 0.05511 0.0231 0.0034 1.0000
17.750 1.3579 0.06160 0.05762 0.0236 0.0032 1.0000
18.000 1.3344 0.06727 0.06345 0.0238 0.0034 1.0000
18.250 1.3288 0.07092 0.06723 0.0236 0.0033 1.0000
18.500 1.3182 0.07541 0.07185 0.0228 0.0032 1.0000
18.750 1.2971 0.08186 0.07848 0.0211 0.0032 1.0000
19.000 1.2818 0.08774 0.08448 0.0190 0.0032 1.0000
19.250 1.2563 0.09586 0.09278 0.0155 0.0032 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 14K AIRFOIL (goe14k-il)