FX 61-140 AIRFOIL (fx61140-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 61-140 AIRFOIL (fx61140-il) Reynolds number: 500,000 Max Cl/Cd: 96.49 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61140-il-500000-n5.txt Download as CSV file: xf-fx61140-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-140 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4693 0.08258 0.08039 -0.0437 1.0000 0.0039
-10.250 -0.4944 0.06981 0.06761 -0.0521 1.0000 0.0038
-10.000 -0.5229 0.06170 0.05940 -0.0569 1.0000 0.0037
-9.750 -0.5482 0.05639 0.05401 -0.0583 1.0000 0.0037
-9.500 -0.5728 0.05240 0.04992 -0.0578 0.9999 0.0037
-9.250 -0.5846 0.04560 0.04284 -0.0634 0.9937 0.0036
-9.000 -0.5913 0.03554 0.03218 -0.0699 0.9850 0.0035
-8.750 -0.5928 0.02734 0.02315 -0.0712 0.9756 0.0035
-8.500 -0.5736 0.02400 0.01937 -0.0719 0.9690 0.0036
-8.250 -0.5503 0.02161 0.01662 -0.0725 0.9619 0.0037
-8.000 -0.5273 0.01991 0.01469 -0.0726 0.9534 0.0039
-7.500 -0.4698 0.01732 0.01174 -0.0745 0.9371 0.0042
-7.250 -0.4354 0.01604 0.01035 -0.0768 0.9285 0.0046
-7.000 -0.3931 0.01523 0.00947 -0.0805 0.9194 0.0051
-6.750 -0.3443 0.01434 0.00846 -0.0855 0.9077 0.0057
-6.500 -0.2859 0.01346 0.00741 -0.0928 0.8910 0.0064
-6.250 -0.2379 0.01286 0.00668 -0.0977 0.8632 0.0078
-6.000 -0.2031 0.01252 0.00618 -0.0996 0.8317 0.0090
-5.750 -0.1751 0.01225 0.00571 -0.1000 0.8010 0.0100
-5.500 -0.1491 0.01182 0.00511 -0.1002 0.7736 0.0114
-5.250 -0.1230 0.01161 0.00478 -0.1001 0.7498 0.0135
-5.000 -0.0965 0.01139 0.00441 -0.1001 0.7284 0.0155
-4.750 -0.0695 0.01110 0.00400 -0.1003 0.7083 0.0196
-4.500 -0.0422 0.01091 0.00370 -0.1005 0.6897 0.0250
-4.250 -0.0142 0.01065 0.00343 -0.1009 0.6731 0.0428
-4.000 0.0150 0.01022 0.00311 -0.1019 0.6574 0.0914
-3.750 0.0477 0.00936 0.00269 -0.1042 0.6431 0.2292
-3.500 0.0842 0.00840 0.00228 -0.1075 0.6294 0.4028
-3.250 0.1178 0.00800 0.00214 -0.1094 0.6165 0.5071
-3.000 0.1486 0.00791 0.00217 -0.1102 0.6046 0.5701
-2.750 0.1778 0.00797 0.00224 -0.1104 0.5940 0.6012
-2.500 0.2066 0.00806 0.00225 -0.1106 0.5837 0.6142
-2.000 0.2642 0.00822 0.00224 -0.1110 0.5639 0.6286
-1.750 0.2929 0.00831 0.00226 -0.1112 0.5551 0.6344
-1.500 0.3220 0.00839 0.00223 -0.1115 0.5459 0.6398
-1.250 0.3504 0.00846 0.00226 -0.1116 0.5376 0.6435
-1.000 0.3789 0.00856 0.00229 -0.1118 0.5296 0.6479
-0.750 0.4081 0.00863 0.00229 -0.1121 0.5218 0.6523
-0.500 0.4367 0.00872 0.00232 -0.1123 0.5147 0.6555
-0.250 0.4653 0.00879 0.00237 -0.1125 0.5079 0.6585
0.000 0.4938 0.00889 0.00242 -0.1127 0.5018 0.6620
0.250 0.5228 0.00897 0.00246 -0.1130 0.4955 0.6660
0.500 0.5515 0.00906 0.00250 -0.1132 0.4889 0.6691
0.750 0.5798 0.00914 0.00258 -0.1134 0.4830 0.6714
1.000 0.6083 0.00923 0.00266 -0.1136 0.4769 0.6740
1.250 0.6367 0.00933 0.00273 -0.1137 0.4711 0.6767
1.500 0.6654 0.00942 0.00280 -0.1140 0.4644 0.6794
2.000 0.7223 0.00961 0.00297 -0.1144 0.4525 0.6843
2.250 0.7503 0.00972 0.00308 -0.1145 0.4465 0.6862
2.500 0.7785 0.00982 0.00319 -0.1147 0.4409 0.6884
2.750 0.8068 0.00993 0.00332 -0.1149 0.4352 0.6909
3.000 0.8349 0.01006 0.00344 -0.1150 0.4301 0.6935
3.250 0.8635 0.01016 0.00355 -0.1153 0.4245 0.6961
3.500 0.8914 0.01028 0.00370 -0.1154 0.4184 0.6980
3.750 0.9190 0.01041 0.00386 -0.1154 0.4130 0.6998
4.000 0.9468 0.01052 0.00402 -0.1155 0.4067 0.7018
4.250 0.9742 0.01068 0.00418 -0.1156 0.4000 0.7039
4.500 1.0022 0.01080 0.00436 -0.1157 0.3930 0.7060
4.750 1.0295 0.01098 0.00454 -0.1157 0.3865 0.7082
5.000 1.0574 0.01112 0.00471 -0.1159 0.3784 0.7105
5.250 1.0843 0.01129 0.00491 -0.1158 0.3687 0.7122
5.500 1.1106 0.01151 0.00514 -0.1157 0.3536 0.7138
5.750 1.1344 0.01192 0.00540 -0.1152 0.3182 0.7156
6.000 1.1571 0.01249 0.00577 -0.1145 0.2766 0.7175
6.250 1.1796 0.01310 0.00620 -0.1139 0.2377 0.7196
6.500 1.1981 0.01413 0.00687 -0.1128 0.1766 0.7216
6.750 1.2153 0.01528 0.00770 -0.1115 0.1179 0.7237
7.000 1.2337 0.01627 0.00849 -0.1103 0.0773 0.7256
7.250 1.2517 0.01721 0.00927 -0.1090 0.0466 0.7272
7.500 1.2699 0.01809 0.01005 -0.1077 0.0248 0.7290
7.750 1.2884 0.01891 0.01082 -0.1065 0.0126 0.7309
8.000 1.3069 0.01968 0.01158 -0.1052 0.0048 0.7327
8.250 1.3260 0.02038 0.01232 -0.1040 0.0034 0.7346
8.500 1.3453 0.02101 0.01303 -0.1029 0.0030 0.7366
8.750 1.3632 0.02171 0.01383 -0.1016 0.0028 0.7387
9.000 1.3793 0.02247 0.01468 -0.1000 0.0025 0.7404
9.250 1.3920 0.02325 0.01557 -0.0978 0.0024 0.7420
9.500 1.4021 0.02412 0.01655 -0.0952 0.0022 0.7437
9.750 1.4089 0.02522 0.01779 -0.0923 0.0021 0.7456
10.000 1.4154 0.02639 0.01906 -0.0896 0.0020 0.7477
10.250 1.4223 0.02758 0.02037 -0.0872 0.0020 0.7499
10.500 1.4279 0.02892 0.02182 -0.0848 0.0020 0.7520
10.750 1.4319 0.03047 0.02348 -0.0826 0.0019 0.7539
11.000 1.4342 0.03226 0.02540 -0.0807 0.0019 0.7555
11.250 1.4354 0.03430 0.02757 -0.0790 0.0019 0.7572
11.500 1.4357 0.03662 0.03003 -0.0777 0.0019 0.7591
11.750 1.4350 0.03926 0.03282 -0.0768 0.0018 0.7612
12.000 1.4340 0.04213 0.03582 -0.0762 0.0018 0.7633
12.250 1.4323 0.04528 0.03911 -0.0760 0.0018 0.7654
12.500 1.4293 0.04876 0.04272 -0.0761 0.0018 0.7672
12.750 1.4258 0.05246 0.04656 -0.0765 0.0018 0.7687
13.000 1.4223 0.05629 0.05052 -0.0770 0.0018 0.7702
13.250 1.4174 0.06041 0.05478 -0.0777 0.0018 0.7717
13.500 1.4123 0.06469 0.05920 -0.0786 0.0017 0.7733
13.750 1.4073 0.06906 0.06371 -0.0797 0.0017 0.7749
14.000 1.4016 0.07366 0.06844 -0.0809 0.0017 0.7765
14.250 1.3967 0.07830 0.07321 -0.0823 0.0017 0.7782
14.500 1.3910 0.08318 0.07822 -0.0838 0.0017 0.7799
14.750 1.3855 0.08814 0.08331 -0.0855 0.0017 0.7815
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