WORTMANN FX 60-126 AIRFOIL (fx60126-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 60-126 AIRFOIL (fx60126-il) Reynolds number: 500,000 Max Cl/Cd: 103.99 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx60126-il-500000.txt Download as CSV file: xf-fx60126-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5976 0.05469 0.05172 -0.0736 1.0000 0.0145
-11.000 -0.6111 0.05069 0.04762 -0.0763 1.0000 0.0144
-10.750 -0.6283 0.04752 0.04438 -0.0771 1.0000 0.0144
-10.500 -0.6616 0.04570 0.04256 -0.0735 1.0000 0.0144
-10.250 -0.6680 0.04275 0.03962 -0.0733 0.9983 0.0140
-10.000 -0.6465 0.03554 0.03197 -0.0871 0.9910 0.0138
-9.750 -0.6219 0.03118 0.02722 -0.0936 0.9859 0.0137
-9.500 -0.5915 0.02768 0.02335 -0.0986 0.9831 0.0136
-9.250 -0.5645 0.02497 0.02035 -0.1012 0.9780 0.0135
-9.000 -0.5330 0.02260 0.01772 -0.1040 0.9746 0.0133
-8.750 -0.4985 0.02073 0.01565 -0.1067 0.9723 0.0133
-8.500 -0.4627 0.01916 0.01392 -0.1094 0.9706 0.0134
-8.250 -0.4323 0.01795 0.01259 -0.1107 0.9660 0.0136
-8.000 -0.4011 0.01690 0.01144 -0.1120 0.9612 0.0139
-7.750 -0.3680 0.01596 0.01040 -0.1137 0.9575 0.0142
-7.500 -0.3381 0.01495 0.00931 -0.1147 0.9526 0.0145
-7.250 -0.3109 0.01390 0.00820 -0.1154 0.9456 0.0153
-7.000 -0.2808 0.01322 0.00746 -0.1161 0.9405 0.0160
-6.750 -0.2542 0.01267 0.00684 -0.1161 0.9331 0.0169
-6.500 -0.2259 0.01218 0.00625 -0.1163 0.9270 0.0179
-6.250 -0.1979 0.01156 0.00558 -0.1165 0.9210 0.0201
-6.000 -0.1702 0.01106 0.00508 -0.1166 0.9143 0.0254
-5.750 -0.1417 0.01031 0.00447 -0.1170 0.9088 0.0586
-5.500 -0.1143 0.00993 0.00414 -0.1170 0.9011 0.0788
-5.250 -0.0862 0.00955 0.00382 -0.1171 0.8945 0.1041
-5.000 -0.0583 0.00917 0.00353 -0.1172 0.8868 0.1371
-4.750 -0.0301 0.00874 0.00324 -0.1175 0.8799 0.1841
-4.500 -0.0017 0.00833 0.00303 -0.1178 0.8728 0.2439
-4.250 0.0267 0.00807 0.00288 -0.1179 0.8657 0.2875
-4.000 0.0553 0.00793 0.00276 -0.1179 0.8591 0.3166
-3.750 0.0838 0.00782 0.00266 -0.1179 0.8510 0.3368
-3.500 0.1123 0.00776 0.00257 -0.1178 0.8434 0.3548
-3.250 0.1407 0.00770 0.00248 -0.1177 0.8345 0.3701
-3.000 0.1692 0.00766 0.00240 -0.1176 0.8260 0.3841
-2.750 0.1978 0.00764 0.00233 -0.1175 0.8172 0.3967
-2.500 0.2263 0.00761 0.00229 -0.1175 0.8083 0.4094
-2.250 0.2548 0.00760 0.00225 -0.1174 0.7995 0.4236
-2.000 0.2832 0.00758 0.00222 -0.1173 0.7890 0.4363
-1.750 0.3117 0.00758 0.00218 -0.1172 0.7789 0.4468
-1.500 0.3400 0.00759 0.00214 -0.1170 0.7683 0.4556
-1.250 0.3683 0.00758 0.00211 -0.1169 0.7558 0.4644
-1.000 0.3965 0.00761 0.00208 -0.1168 0.7422 0.4744
-0.750 0.4244 0.00763 0.00207 -0.1166 0.7273 0.4841
-0.500 0.4524 0.00768 0.00206 -0.1164 0.7114 0.4940
-0.250 0.4802 0.00773 0.00207 -0.1162 0.6956 0.5035
0.000 0.5081 0.00778 0.00208 -0.1160 0.6803 0.5119
0.250 0.5360 0.00786 0.00210 -0.1158 0.6649 0.5205
0.500 0.5637 0.00792 0.00213 -0.1157 0.6490 0.5280
0.750 0.5913 0.00803 0.00217 -0.1155 0.6320 0.5365
1.000 0.6189 0.00812 0.00222 -0.1153 0.6163 0.5445
1.250 0.6467 0.00823 0.00229 -0.1151 0.6021 0.5539
1.500 0.6742 0.00832 0.00237 -0.1150 0.5878 0.5622
1.750 0.7019 0.00844 0.00244 -0.1148 0.5739 0.5713
2.000 0.7293 0.00855 0.00254 -0.1147 0.5598 0.5803
2.250 0.7565 0.00868 0.00264 -0.1145 0.5450 0.5900
2.500 0.7838 0.00882 0.00275 -0.1143 0.5305 0.6000
2.750 0.8110 0.00894 0.00287 -0.1141 0.5166 0.6090
3.250 0.8653 0.00920 0.00312 -0.1137 0.4881 0.6291
3.500 0.8924 0.00934 0.00325 -0.1135 0.4740 0.6394
3.750 0.9192 0.00950 0.00340 -0.1133 0.4587 0.6511
4.000 0.9460 0.00964 0.00357 -0.1130 0.4438 0.6640
4.250 0.9725 0.00981 0.00374 -0.1128 0.4282 0.6785
4.500 0.9986 0.01000 0.00392 -0.1124 0.4114 0.6942
4.750 1.0243 0.01021 0.00414 -0.1120 0.3934 0.7116
5.000 1.0501 0.01040 0.00435 -0.1117 0.3744 0.7318
5.250 1.0754 0.01060 0.00458 -0.1112 0.3566 0.7583
5.500 1.0998 0.01078 0.00484 -0.1106 0.3394 0.7951
5.750 1.1168 0.01074 0.00503 -0.1081 0.3228 0.8997
6.000 1.1418 0.01104 0.00526 -0.1077 0.3025 1.0000
6.250 1.1666 0.01143 0.00556 -0.1073 0.2833 1.0000
6.500 1.1909 0.01186 0.00590 -0.1068 0.2594 1.0000
6.750 1.2136 0.01241 0.00629 -0.1061 0.2313 1.0000
7.000 1.2363 0.01296 0.00670 -0.1054 0.2064 1.0000
7.250 1.2582 0.01356 0.00716 -0.1046 0.1824 1.0000
7.500 1.2804 0.01411 0.00763 -0.1039 0.1650 1.0000
7.750 1.3027 0.01463 0.00808 -0.1031 0.1485 1.0000
8.000 1.3242 0.01519 0.00858 -0.1022 0.1357 1.0000
8.250 1.3448 0.01580 0.00913 -0.1012 0.1253 1.0000
8.500 1.3672 0.01624 0.00960 -0.1004 0.1163 1.0000
8.750 1.3877 0.01680 0.01013 -0.0994 0.1069 1.0000
9.000 1.4067 0.01743 0.01072 -0.0982 0.0978 1.0000
9.250 1.4255 0.01805 0.01133 -0.0969 0.0911 1.0000
9.500 1.4422 0.01876 0.01204 -0.0953 0.0846 1.0000
9.750 1.4607 0.01925 0.01259 -0.0939 0.0790 1.0000
10.000 1.4736 0.01999 0.01331 -0.0918 0.0734 1.0000
10.250 1.4897 0.02053 0.01389 -0.0901 0.0690 1.0000
10.500 1.5013 0.02134 0.01467 -0.0878 0.0640 1.0000
10.750 1.5135 0.02212 0.01551 -0.0858 0.0605 1.0000
11.000 1.5238 0.02305 0.01646 -0.0836 0.0573 1.0000
11.250 1.5283 0.02439 0.01780 -0.0810 0.0535 1.0000
11.500 1.5391 0.02538 0.01887 -0.0791 0.0515 1.0000
11.750 1.5514 0.02630 0.01988 -0.0776 0.0494 1.0000
12.000 1.5617 0.02739 0.02104 -0.0760 0.0471 1.0000
12.250 1.5687 0.02878 0.02249 -0.0742 0.0452 1.0000
12.500 1.5694 0.03074 0.02450 -0.0721 0.0432 1.0000
12.750 1.5792 0.03204 0.02589 -0.0709 0.0421 1.0000
13.000 1.5909 0.03322 0.02717 -0.0699 0.0407 1.0000
13.250 1.6010 0.03458 0.02860 -0.0689 0.0392 1.0000
13.500 1.6082 0.03623 0.03031 -0.0678 0.0380 1.0000
13.750 1.6135 0.03815 0.03228 -0.0669 0.0366 1.0000
14.000 1.6135 0.04066 0.03486 -0.0660 0.0353 1.0000
14.250 1.6189 0.04272 0.03703 -0.0653 0.0343 1.0000
14.500 1.6260 0.04466 0.03908 -0.0649 0.0333 1.0000
14.750 1.6318 0.04680 0.04131 -0.0645 0.0321 1.0000
15.000 1.6359 0.04921 0.04378 -0.0644 0.0308 1.0000
15.250 1.6362 0.05217 0.04680 -0.0644 0.0296 1.0000
15.500 1.6310 0.05596 0.05067 -0.0647 0.0283 1.0000
15.750 1.6356 0.05859 0.05342 -0.0649 0.0274 1.0000
16.000 1.6399 0.06134 0.05628 -0.0653 0.0260 1.0000
16.250 1.6406 0.06466 0.05969 -0.0660 0.0245 1.0000
16.500 1.6354 0.06895 0.06405 -0.0671 0.0229 1.0000
16.750 1.6358 0.07250 0.06772 -0.0680 0.0213 1.0000
17.000 1.6332 0.07656 0.07187 -0.0692 0.0188 1.0000
17.250 1.6268 0.08138 0.07677 -0.0708 0.0163 1.0000
17.500 1.6162 0.08702 0.08248 -0.0729 0.0137 1.0000
17.750 1.6042 0.09304 0.08861 -0.0753 0.0117 1.0000
18.000 1.5897 0.09966 0.09532 -0.0781 0.0106 1.0000
18.250 1.5756 0.10642 0.10221 -0.0812 0.0098 1.0000
18.500 1.5607 0.11344 0.10936 -0.0846 0.0093 1.0000
18.750 1.5445 0.12089 0.11693 -0.0884 0.0089 1.0000
19.000 1.5286 0.12843 0.12461 -0.0925 0.0086 1.0000
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