WORTMANN FX 60-126 AIRFOIL (fx60126-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: WORTMANN FX 60-126 AIRFOIL (fx60126-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.45 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx60126-il-1000000-n5.txt Download as CSV file: xf-fx60126-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 60-126 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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.6372 0.11813 0.11597 -0.0324 1.0000 0.0047
-15.500 -0.6643 0.10804 0.10576 -0.0373 1.0000 0.0046
-15.250 -0.6905 0.09856 0.09617 -0.0422 1.0000 0.0046
-15.000 -0.7132 0.09007 0.08757 -0.0467 1.0000 0.0046
-14.750 -0.7297 0.08296 0.08036 -0.0507 1.0000 0.0045
-14.500 -0.7462 0.07607 0.07337 -0.0546 1.0000 0.0045
-14.250 -0.7619 0.06951 0.06672 -0.0586 1.0000 0.0045
-14.000 -0.7766 0.06339 0.06049 -0.0623 1.0000 0.0045
-13.750 -0.7913 0.05766 0.05467 -0.0658 1.0000 0.0045
-13.500 -0.8003 0.05298 0.04990 -0.0687 1.0000 0.0045
-13.250 -0.8128 0.04803 0.04485 -0.0717 1.0000 0.0045
-13.000 -0.8288 0.04294 0.03965 -0.0747 1.0000 0.0046
-12.750 -0.8357 0.03933 0.03595 -0.0765 1.0000 0.0045
-12.500 -0.8509 0.03538 0.03190 -0.0778 1.0000 0.0045
-12.250 -0.8553 0.03242 0.02887 -0.0792 0.9987 0.0045
-12.000 -0.8380 0.02821 0.02451 -0.0870 0.9871 0.0046
-11.750 -0.8069 0.02479 0.02092 -0.0959 0.9810 0.0047
-11.500 -0.7769 0.02272 0.01871 -0.1008 0.9748 0.0047
-11.250 -0.7460 0.02117 0.01703 -0.1044 0.9700 0.0048
-11.000 -0.7189 0.01988 0.01563 -0.1065 0.9623 0.0049
-10.500 -0.6663 0.01782 0.01335 -0.1091 0.9457 0.0050
-10.250 -0.6416 0.01696 0.01239 -0.1097 0.9364 0.0051
-10.000 -0.6172 0.01620 0.01152 -0.1099 0.9262 0.0051
-9.750 -0.5927 0.01549 0.01071 -0.1100 0.9163 0.0052
-9.500 -0.5677 0.01486 0.00998 -0.1101 0.9072 0.0053
-9.250 -0.5420 0.01426 0.00930 -0.1103 0.8983 0.0054
-9.000 -0.5161 0.01370 0.00864 -0.1104 0.8898 0.0055
-8.750 -0.4897 0.01319 0.00803 -0.1105 0.8813 0.0057
-8.500 -0.4629 0.01271 0.00747 -0.1106 0.8738 0.0058
-8.250 -0.4357 0.01227 0.00695 -0.1108 0.8664 0.0059
-8.000 -0.4083 0.01188 0.00649 -0.1109 0.8599 0.0061
-7.750 -0.3806 0.01151 0.00605 -0.1110 0.8523 0.0062
-7.500 -0.3529 0.01118 0.00564 -0.1112 0.8451 0.0063
-7.250 -0.3248 0.01073 0.00513 -0.1114 0.8390 0.0066
-7.000 -0.2967 0.01040 0.00475 -0.1116 0.8330 0.0069
-6.750 -0.2683 0.01012 0.00442 -0.1118 0.8269 0.0072
-6.500 -0.2399 0.00986 0.00411 -0.1119 0.8198 0.0076
-6.250 -0.2114 0.00963 0.00382 -0.1120 0.8126 0.0080
-6.000 -0.1828 0.00942 0.00356 -0.1122 0.8044 0.0084
-5.750 -0.1543 0.00920 0.00329 -0.1123 0.7965 0.0093
-5.500 -0.1255 0.00899 0.00304 -0.1125 0.7882 0.0112
-5.250 -0.0968 0.00871 0.00277 -0.1127 0.7812 0.0185
-5.000 -0.0679 0.00843 0.00254 -0.1130 0.7731 0.0346
-4.750 -0.0391 0.00826 0.00234 -0.1131 0.7643 0.0414
-4.500 -0.0104 0.00810 0.00218 -0.1133 0.7536 0.0492
-4.250 0.0185 0.00789 0.00200 -0.1135 0.7428 0.0700
-4.000 0.0472 0.00774 0.00185 -0.1137 0.7320 0.0819
-3.750 0.0760 0.00757 0.00171 -0.1139 0.7208 0.1060
-3.500 0.1049 0.00736 0.00157 -0.1141 0.7084 0.1358
-3.250 0.1337 0.00721 0.00145 -0.1143 0.6944 0.1635
-3.000 0.1624 0.00707 0.00135 -0.1145 0.6798 0.1950
-2.750 0.1911 0.00700 0.00127 -0.1146 0.6658 0.2142
-2.500 0.2196 0.00694 0.00121 -0.1147 0.6493 0.2394
-2.250 0.2477 0.00696 0.00117 -0.1147 0.6251 0.2572
-2.000 0.2757 0.00699 0.00114 -0.1147 0.5996 0.2762
-1.750 0.3038 0.00701 0.00113 -0.1148 0.5776 0.3017
-1.500 0.3323 0.00703 0.00113 -0.1148 0.5609 0.3181
-1.250 0.3607 0.00705 0.00114 -0.1149 0.5460 0.3373
-1.000 0.3892 0.00707 0.00116 -0.1149 0.5325 0.3598
-0.750 0.4178 0.00711 0.00118 -0.1150 0.5196 0.3739
-0.500 0.4463 0.00715 0.00120 -0.1151 0.5069 0.3848
-0.250 0.4748 0.00722 0.00123 -0.1151 0.4939 0.3950
0.000 0.5032 0.00729 0.00128 -0.1151 0.4819 0.4053
0.250 0.5314 0.00736 0.00133 -0.1151 0.4695 0.4181
0.500 0.5597 0.00745 0.00138 -0.1151 0.4559 0.4293
0.750 0.5879 0.00753 0.00144 -0.1151 0.4419 0.4369
1.000 0.6158 0.00767 0.00151 -0.1151 0.4253 0.4439
1.250 0.6435 0.00781 0.00159 -0.1150 0.4065 0.4516
1.500 0.6713 0.00795 0.00168 -0.1149 0.3888 0.4586
1.750 0.6991 0.00808 0.00177 -0.1149 0.3739 0.4657
2.000 0.7268 0.00822 0.00187 -0.1148 0.3594 0.4738
2.250 0.7545 0.00836 0.00198 -0.1147 0.3467 0.4822
2.500 0.7821 0.00851 0.00209 -0.1146 0.3333 0.4908
2.750 0.8094 0.00868 0.00222 -0.1145 0.3155 0.4992
3.250 0.8634 0.00910 0.00253 -0.1142 0.2794 0.5157
3.500 0.8898 0.00937 0.00271 -0.1140 0.2568 0.5231
3.750 0.9161 0.00965 0.00290 -0.1137 0.2348 0.5305
4.000 0.9427 0.00988 0.00309 -0.1135 0.2198 0.5381
4.500 0.9944 0.01050 0.00355 -0.1129 0.1794 0.5540
4.750 1.0207 0.01074 0.00377 -0.1127 0.1676 0.5626
5.000 1.0471 0.01097 0.00398 -0.1124 0.1550 0.5717
5.250 1.0725 0.01130 0.00425 -0.1121 0.1395 0.5822
5.500 1.0988 0.01152 0.00449 -0.1118 0.1324 0.5926
6.000 1.1501 0.01206 0.00501 -0.1112 0.1132 0.6134
6.250 1.1743 0.01248 0.00535 -0.1106 0.0967 0.6234
6.750 1.2250 0.01302 0.00591 -0.1099 0.0879 0.6447
7.000 1.2506 0.01324 0.00618 -0.1095 0.0850 0.6568
7.250 1.2763 0.01345 0.00645 -0.1092 0.0823 0.6712
7.500 1.3008 0.01374 0.00678 -0.1087 0.0759 0.6880
7.750 1.3245 0.01410 0.00715 -0.1082 0.0669 0.7082
8.000 1.3478 0.01447 0.00755 -0.1075 0.0609 0.7365
8.250 1.3712 0.01477 0.00794 -0.1069 0.0578 0.7794
8.500 1.3876 0.01477 0.00828 -0.1046 0.0548 1.0000
8.750 1.4109 0.01513 0.00866 -0.1040 0.0523 1.0000
9.000 1.4342 0.01546 0.00901 -0.1033 0.0506 1.0000
9.250 1.4565 0.01585 0.00943 -0.1025 0.0477 1.0000
9.500 1.4771 0.01635 0.00992 -0.1015 0.0440 1.0000
9.750 1.4984 0.01677 0.01035 -0.1006 0.0415 1.0000
10.000 1.5185 0.01724 0.01082 -0.0995 0.0377 1.0000
10.250 1.5368 0.01780 0.01137 -0.0981 0.0340 1.0000
10.500 1.5542 0.01831 0.01188 -0.0966 0.0319 1.0000
10.750 1.5688 0.01887 0.01245 -0.0946 0.0298 1.0000
11.000 1.5828 0.01944 0.01304 -0.0925 0.0279 1.0000
11.250 1.5971 0.02001 0.01365 -0.0906 0.0268 1.0000
11.500 1.6105 0.02064 0.01431 -0.0886 0.0255 1.0000
11.750 1.6227 0.02138 0.01508 -0.0866 0.0241 1.0000
12.000 1.6337 0.02222 0.01595 -0.0846 0.0224 1.0000
12.250 1.6464 0.02298 0.01676 -0.0829 0.0216 1.0000
12.500 1.6579 0.02386 0.01768 -0.0811 0.0203 1.0000
12.750 1.6678 0.02488 0.01873 -0.0793 0.0190 1.0000
13.000 1.6767 0.02601 0.01990 -0.0775 0.0177 1.0000
13.250 1.6870 0.02709 0.02103 -0.0759 0.0166 1.0000
13.500 1.6943 0.02845 0.02243 -0.0743 0.0145 1.0000
13.750 1.6992 0.03006 0.02406 -0.0726 0.0113 1.0000
14.250 1.6947 0.03482 0.02889 -0.0690 0.0049 1.0000
14.500 1.6967 0.03700 0.03114 -0.0679 0.0042 1.0000
14.750 1.6987 0.03928 0.03350 -0.0669 0.0037 1.0000
15.000 1.6992 0.04182 0.03613 -0.0662 0.0033 1.0000
15.250 1.7012 0.04430 0.03869 -0.0656 0.0032 1.0000
15.500 1.7018 0.04703 0.04152 -0.0653 0.0030 1.0000
15.750 1.7017 0.04997 0.04455 -0.0651 0.0029 1.0000
16.000 1.7005 0.05318 0.04787 -0.0652 0.0028 1.0000
16.250 1.6979 0.05672 0.05151 -0.0656 0.0026 1.0000
16.500 1.6939 0.06056 0.05546 -0.0662 0.0025 1.0000
16.750 1.6896 0.06462 0.05962 -0.0670 0.0024 1.0000
17.000 1.6839 0.06904 0.06415 -0.0682 0.0024 1.0000
17.250 1.6764 0.07385 0.06908 -0.0696 0.0023 1.0000
17.500 1.6685 0.07887 0.07422 -0.0712 0.0022 1.0000
17.750 1.6604 0.08409 0.07956 -0.0731 0.0022 1.0000
18.000 1.6513 0.08960 0.08519 -0.0753 0.0022 1.0000
18.250 1.6410 0.09544 0.09116 -0.0777 0.0022 1.0000
18.500 1.6294 0.10166 0.09750 -0.0804 0.0021 1.0000
18.750 1.6174 0.10807 0.10405 -0.0834 0.0021 1.0000
19.000 1.6038 0.11491 0.11101 -0.0868 0.0021 1.0000
19.250 1.5899 0.12190 0.11813 -0.0904 0.0021 1.0000
|
Polar data table (+)
Polar graphs
<< Back to WORTMANN FX 60-126 AIRFOIL (fx60126-il)