FX 61-147 AIRFOIL (fx61147-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 61-147 AIRFOIL (fx61147-il) Reynolds number: 500,000 Max Cl/Cd: 98.7 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61147-il-500000-n5.txt Download as CSV file: xf-fx61147-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-147 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6120 0.04387 0.04100 -0.0772 0.9947 0.0039
-10.500 -0.6310 0.03645 0.03309 -0.0826 0.9869 0.0039
-10.250 -0.6362 0.03143 0.02763 -0.0851 0.9769 0.0039
-10.000 -0.6263 0.02783 0.02363 -0.0866 0.9684 0.0039
-9.500 -0.5892 0.02329 0.01850 -0.0882 0.9555 0.0040
-9.250 -0.5645 0.02159 0.01658 -0.0892 0.9505 0.0041
-9.000 -0.5417 0.02025 0.01504 -0.0895 0.9438 0.0042
-8.750 -0.5141 0.01885 0.01349 -0.0907 0.9383 0.0044
-8.500 -0.4822 0.01789 0.01244 -0.0925 0.9336 0.0047
-8.250 -0.4511 0.01708 0.01152 -0.0939 0.9261 0.0049
-8.000 -0.4122 0.01620 0.01054 -0.0970 0.9209 0.0053
-7.750 -0.3753 0.01537 0.00960 -0.0996 0.9126 0.0058
-7.500 -0.3301 0.01451 0.00862 -0.1039 0.9057 0.0065
-7.250 -0.2862 0.01393 0.00798 -0.1080 0.8959 0.0073
-7.000 -0.2453 0.01342 0.00735 -0.1112 0.8839 0.0086
-6.750 -0.2076 0.01294 0.00678 -0.1139 0.8682 0.0098
-6.500 -0.1728 0.01261 0.00634 -0.1157 0.8498 0.0111
-6.250 -0.1424 0.01235 0.00596 -0.1166 0.8293 0.0126
-6.000 -0.1147 0.01212 0.00565 -0.1170 0.8079 0.0147
-5.750 -0.0880 0.01196 0.00536 -0.1170 0.7873 0.0164
-5.500 -0.0627 0.01163 0.00492 -0.1168 0.7665 0.0185
-5.250 -0.0373 0.01142 0.00459 -0.1166 0.7462 0.0202
-5.000 -0.0117 0.01124 0.00427 -0.1164 0.7270 0.0217
-4.750 0.0141 0.01103 0.00394 -0.1162 0.7085 0.0246
-4.500 0.0401 0.01086 0.00370 -0.1160 0.6903 0.0295
-4.250 0.0664 0.01069 0.00346 -0.1160 0.6733 0.0389
-4.000 0.0933 0.01051 0.00324 -0.1161 0.6582 0.0544
-3.750 0.1209 0.01024 0.00302 -0.1164 0.6449 0.0877
-3.500 0.1503 0.00963 0.00272 -0.1176 0.6325 0.1934
-3.250 0.1825 0.00879 0.00238 -0.1198 0.6205 0.3578
-3.000 0.2149 0.00823 0.00223 -0.1216 0.6088 0.4988
-2.750 0.2445 0.00813 0.00227 -0.1221 0.5983 0.5623
-2.500 0.2729 0.00819 0.00234 -0.1223 0.5891 0.5949
-2.000 0.3292 0.00839 0.00242 -0.1223 0.5705 0.6264
-1.750 0.3570 0.00849 0.00245 -0.1223 0.5617 0.6321
-1.500 0.3852 0.00857 0.00246 -0.1224 0.5530 0.6377
-1.250 0.4135 0.00866 0.00246 -0.1225 0.5447 0.6428
-1.000 0.4411 0.00875 0.00250 -0.1225 0.5360 0.6464
-0.750 0.4693 0.00884 0.00253 -0.1226 0.5283 0.6506
-0.500 0.4974 0.00894 0.00255 -0.1227 0.5210 0.6551
-0.250 0.5255 0.00902 0.00259 -0.1228 0.5142 0.6585
0.000 0.5532 0.00912 0.00265 -0.1228 0.5071 0.6616
0.250 0.5812 0.00921 0.00270 -0.1228 0.5010 0.6649
0.500 0.6094 0.00930 0.00275 -0.1230 0.4949 0.6684
0.750 0.6374 0.00941 0.00280 -0.1231 0.4893 0.6717
1.000 0.6653 0.00948 0.00288 -0.1232 0.4833 0.6739
1.250 0.6927 0.00959 0.00296 -0.1231 0.4771 0.6764
1.500 0.7204 0.00970 0.00305 -0.1232 0.4712 0.6792
1.750 0.7482 0.00980 0.00313 -0.1233 0.4646 0.6822
2.000 0.7757 0.00993 0.00321 -0.1233 0.4584 0.6852
2.250 0.8035 0.01002 0.00331 -0.1234 0.4521 0.6876
2.500 0.8304 0.01014 0.00343 -0.1233 0.4462 0.6896
2.750 0.8579 0.01025 0.00354 -0.1233 0.4407 0.6917
3.000 0.8852 0.01036 0.00367 -0.1233 0.4351 0.6940
3.250 0.9121 0.01051 0.00380 -0.1232 0.4297 0.6965
3.500 0.9398 0.01062 0.00392 -0.1233 0.4239 0.6989
3.750 0.9669 0.01076 0.00405 -0.1233 0.4183 0.7013
4.000 0.9936 0.01089 0.00421 -0.1232 0.4135 0.7031
4.250 1.0205 0.01101 0.00437 -0.1232 0.4081 0.7050
4.500 1.0468 0.01117 0.00454 -0.1230 0.4025 0.7069
4.750 1.0735 0.01131 0.00472 -0.1229 0.3969 0.7090
5.000 1.1001 0.01146 0.00490 -0.1228 0.3909 0.7113
5.250 1.1260 0.01164 0.00509 -0.1226 0.3857 0.7136
5.500 1.1528 0.01179 0.00529 -0.1225 0.3791 0.7157
5.750 1.1778 0.01199 0.00550 -0.1222 0.3705 0.7175
6.000 1.2026 0.01219 0.00571 -0.1218 0.3592 0.7193
6.250 1.2269 0.01243 0.00595 -0.1213 0.3463 0.7211
6.500 1.2511 0.01268 0.00622 -0.1208 0.3346 0.7231
6.750 1.2747 0.01296 0.00649 -0.1202 0.3218 0.7253
7.000 1.2956 0.01340 0.00683 -0.1192 0.2977 0.7274
7.250 1.3145 0.01397 0.00725 -0.1179 0.2662 0.7296
7.500 1.3327 0.01459 0.00772 -0.1165 0.2362 0.7315
7.750 1.3498 0.01524 0.00827 -0.1149 0.2087 0.7333
8.000 1.3607 0.01623 0.00902 -0.1124 0.1648 0.7350
8.250 1.3665 0.01734 0.00990 -0.1089 0.1237 0.7368
8.500 1.3724 0.01845 0.01082 -0.1056 0.0915 0.7390
8.750 1.3809 0.01941 0.01168 -0.1027 0.0682 0.7412
9.000 1.3905 0.02030 0.01251 -0.1001 0.0538 0.7434
9.250 1.4005 0.02117 0.01335 -0.0976 0.0420 0.7454
9.500 1.4089 0.02212 0.01431 -0.0950 0.0317 0.7471
9.750 1.4174 0.02308 0.01528 -0.0926 0.0249 0.7489
10.000 1.4248 0.02414 0.01637 -0.0901 0.0194 0.7509
10.250 1.4336 0.02517 0.01745 -0.0879 0.0156 0.7532
10.500 1.4400 0.02639 0.01872 -0.0857 0.0116 0.7554
10.750 1.4431 0.02791 0.02025 -0.0833 0.0065 0.7575
11.000 1.4450 0.02961 0.02200 -0.0811 0.0042 0.7595
11.250 1.4483 0.03132 0.02379 -0.0792 0.0035 0.7613
11.500 1.4523 0.03307 0.02565 -0.0777 0.0031 0.7632
11.750 1.4558 0.03499 0.02768 -0.0763 0.0029 0.7653
12.000 1.4582 0.03712 0.02994 -0.0752 0.0027 0.7677
12.250 1.4593 0.03950 0.03244 -0.0742 0.0025 0.7700
12.500 1.4600 0.04207 0.03513 -0.0735 0.0024 0.7723
12.750 1.4597 0.04489 0.03806 -0.0730 0.0023 0.7744
13.000 1.4582 0.04796 0.04127 -0.0728 0.0022 0.7762
13.250 1.4577 0.05106 0.04449 -0.0727 0.0021 0.7781
13.500 1.4569 0.05429 0.04785 -0.0729 0.0021 0.7801
13.750 1.4554 0.05772 0.05140 -0.0732 0.0021 0.7823
14.000 1.4533 0.06135 0.05516 -0.0736 0.0020 0.7846
14.250 1.4505 0.06518 0.05911 -0.0743 0.0020 0.7870
14.500 1.4475 0.06915 0.06321 -0.0751 0.0020 0.7892
14.750 1.4438 0.07331 0.06750 -0.0761 0.0019 0.7913
15.000 1.4397 0.07764 0.07196 -0.0772 0.0019 0.7934
15.250 1.4354 0.08212 0.07657 -0.0785 0.0018 0.7955
15.500 1.4307 0.08676 0.08136 -0.0800 0.0018 0.7977
15.750 1.4257 0.09155 0.08628 -0.0816 0.0018 0.7999
16.000 1.4203 0.09651 0.09136 -0.0834 0.0017 0.8021
16.500 1.4102 0.10654 0.10165 -0.0873 0.0017 0.8066
16.750 1.4047 0.11174 0.10698 -0.0895 0.0016 0.8090
17.000 1.3996 0.11697 0.11233 -0.0918 0.0016 0.8117
17.250 1.3942 0.12231 0.11780 -0.0942 0.0016 0.8148
17.500 1.3889 0.12764 0.12325 -0.0968 0.0016 0.8179
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