R140 12.04% (smoothed) (r140sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: R140 12.04% (smoothed) (r140sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 59.85 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-r140sm-il-1000000-n5.txt Download as CSV file: xf-r140sm-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: R140 12.04% (smoothed)
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.8353 0.07414 0.07249 -0.0344 1.0000 0.0016
-13.750 -0.8753 0.06212 0.06028 -0.0422 1.0000 0.0016
-13.500 -0.8983 0.05520 0.05319 -0.0459 1.0000 0.0016
-13.250 -0.9206 0.04925 0.04705 -0.0481 1.0000 0.0016
-13.000 -0.9119 0.04780 0.04556 -0.0485 1.0000 0.0015
-12.750 -0.9786 0.03792 0.03515 -0.0477 1.0000 0.0016
-12.500 -0.9829 0.03557 0.03264 -0.0462 1.0000 0.0016
-12.250 -0.9975 0.03242 0.02923 -0.0434 1.0000 0.0017
-12.000 -0.9984 0.03067 0.02734 -0.0409 1.0000 0.0018
-11.750 -0.9997 0.02892 0.02539 -0.0379 1.0000 0.0018
-11.500 -0.9993 0.02741 0.02372 -0.0347 1.0000 0.0018
-11.250 -1.0032 0.02556 0.02164 -0.0304 1.0000 0.0018
-11.000 -0.9849 0.02607 0.02225 -0.0290 1.0000 0.0020
-10.750 -0.9819 0.02486 0.02088 -0.0254 1.0000 0.0020
-10.500 -0.9808 0.02288 0.01864 -0.0214 1.0000 0.0020
-10.250 -0.9631 0.02294 0.01873 -0.0200 1.0000 0.0021
-10.000 -0.9566 0.02159 0.01720 -0.0167 1.0000 0.0022
-9.500 -0.9141 0.01948 0.01482 -0.0160 0.9950 0.0024
-9.250 -0.8904 0.01854 0.01376 -0.0160 0.9897 0.0025
-9.000 -0.8653 0.01749 0.01258 -0.0162 0.9852 0.0026
-8.750 -0.8397 0.01673 0.01169 -0.0165 0.9796 0.0028
-8.500 -0.8122 0.01575 0.01058 -0.0172 0.9748 0.0029
-8.250 -0.7819 0.01495 0.00967 -0.0184 0.9705 0.0030
-8.000 -0.7503 0.01436 0.00900 -0.0198 0.9649 0.0032
-7.750 -0.7177 0.01360 0.00815 -0.0215 0.9594 0.0033
-7.500 -0.6886 0.01276 0.00721 -0.0225 0.9503 0.0040
-7.250 -0.6575 0.01237 0.00679 -0.0237 0.9411 0.0045
-7.000 -0.6303 0.01195 0.00630 -0.0240 0.9301 0.0049
-6.750 -0.6053 0.01163 0.00588 -0.0237 0.9183 0.0055
-6.500 -0.5827 0.01126 0.00542 -0.0229 0.9056 0.0059
-6.250 -0.5595 0.01101 0.00509 -0.0221 0.8927 0.0062
-6.000 -0.5387 0.01059 0.00456 -0.0209 0.8792 0.0070
-5.750 -0.5168 0.01028 0.00417 -0.0198 0.8647 0.0079
-5.250 -0.4709 0.00989 0.00364 -0.0181 0.8316 0.0101
-5.000 -0.4478 0.00973 0.00336 -0.0173 0.8131 0.0107
-4.750 -0.4250 0.00955 0.00306 -0.0163 0.7951 0.0120
-4.500 -0.4021 0.00936 0.00281 -0.0154 0.7776 0.0160
-4.250 -0.3788 0.00918 0.00260 -0.0146 0.7614 0.0230
-4.000 -0.3558 0.00897 0.00240 -0.0138 0.7466 0.0400
-3.750 -0.3324 0.00877 0.00222 -0.0131 0.7337 0.0580
-3.500 -0.3088 0.00858 0.00203 -0.0124 0.7217 0.0807
-3.250 -0.2876 0.00819 0.00183 -0.0114 0.7105 0.1423
-3.000 -0.2686 0.00760 0.00157 -0.0099 0.7006 0.2389
-2.750 -0.2553 0.00664 0.00127 -0.0075 0.6917 0.4202
-2.500 -0.2338 0.00632 0.00115 -0.0065 0.6830 0.4857
-2.250 -0.2094 0.00616 0.00106 -0.0059 0.6746 0.5205
-2.000 -0.1852 0.00603 0.00101 -0.0053 0.6673 0.5584
-1.750 -0.1597 0.00596 0.00098 -0.0049 0.6602 0.5852
-1.500 -0.1341 0.00591 0.00095 -0.0045 0.6537 0.6048
-1.250 -0.1072 0.00590 0.00091 -0.0044 0.6467 0.6147
-1.000 -0.0806 0.00589 0.00089 -0.0043 0.6405 0.6244
-0.750 -0.0538 0.00587 0.00087 -0.0042 0.6345 0.6334
-0.500 -0.0268 0.00587 0.00085 -0.0041 0.6289 0.6410
-0.250 0.0001 0.00585 0.00084 -0.0040 0.6234 0.6468
0.000 0.0272 0.00586 0.00083 -0.0040 0.6174 0.6529
0.250 0.0542 0.00586 0.00083 -0.0039 0.6123 0.6586
0.500 0.0813 0.00585 0.00084 -0.0039 0.6070 0.6648
0.750 0.1082 0.00586 0.00085 -0.0038 0.6018 0.6710
1.000 0.1351 0.00585 0.00086 -0.0037 0.5968 0.6782
1.250 0.1618 0.00585 0.00088 -0.0036 0.5901 0.6859
1.500 0.1883 0.00586 0.00092 -0.0034 0.5822 0.6950
1.750 0.2141 0.00587 0.00095 -0.0031 0.5721 0.7057
2.000 0.2396 0.00589 0.00098 -0.0027 0.5574 0.7183
2.250 0.2648 0.00590 0.00103 -0.0023 0.5440 0.7339
2.500 0.2899 0.00593 0.00110 -0.0018 0.5283 0.7516
2.750 0.3141 0.00598 0.00117 -0.0012 0.5068 0.7704
3.000 0.3372 0.00613 0.00126 -0.0003 0.4686 0.7883
3.250 0.3588 0.00641 0.00139 0.0008 0.4128 0.8042
3.750 0.3911 0.00781 0.00201 0.0047 0.1920 0.8325
4.000 0.4071 0.00852 0.00237 0.0067 0.0890 0.8461
4.250 0.4290 0.00882 0.00259 0.0077 0.0571 0.8591
4.500 0.4496 0.00922 0.00286 0.0089 0.0189 0.8728
4.750 0.4733 0.00942 0.00311 0.0096 0.0127 0.8861
5.000 0.4983 0.00958 0.00335 0.0100 0.0117 0.8996
5.250 0.5242 0.00979 0.00365 0.0102 0.0104 0.9133
5.500 0.5517 0.01007 0.00397 0.0100 0.0086 0.9263
5.750 0.5809 0.01051 0.00451 0.0093 0.0073 0.9381
6.000 0.6144 0.01079 0.00483 0.0077 0.0068 0.9475
6.250 0.6484 0.01120 0.00529 0.0059 0.0061 0.9549
6.500 0.6813 0.01159 0.00573 0.0043 0.0054 0.9609
6.750 0.7152 0.01195 0.00610 0.0025 0.0046 0.9648
7.000 0.7418 0.01272 0.00695 0.0021 0.0038 0.9710
7.250 0.7714 0.01313 0.00740 0.0012 0.0037 0.9751
7.500 0.7980 0.01373 0.00807 0.0009 0.0036 0.9801
7.750 0.8224 0.01429 0.00869 0.0011 0.0033 0.9856
8.000 0.8487 0.01507 0.00957 0.0007 0.0032 0.9895
8.250 0.8748 0.01571 0.01027 0.0004 0.0030 0.9934
8.500 0.9015 0.01636 0.01098 -0.0001 0.0027 0.9967
8.750 0.9276 0.01732 0.01208 -0.0006 0.0026 0.9991
9.000 0.9512 0.01785 0.01265 -0.0004 0.0024 1.0000
9.250 0.9655 0.01824 0.01307 0.0017 0.0023 1.0000
9.500 0.9771 0.01888 0.01378 0.0044 0.0022 1.0000
9.750 0.9866 0.01973 0.01472 0.0073 0.0021 1.0000
10.000 0.9847 0.02152 0.01673 0.0121 0.0019 1.0000
10.250 0.9938 0.02202 0.01729 0.0151 0.0019 1.0000
10.500 0.9905 0.02430 0.01985 0.0197 0.0018 1.0000
10.750 0.9912 0.02614 0.02192 0.0234 0.0018 1.0000
11.000 0.9941 0.02771 0.02366 0.0264 0.0018 1.0000
11.250 0.9904 0.03005 0.02626 0.0299 0.0018 1.0000
11.500 0.9906 0.03192 0.02833 0.0325 0.0017 1.0000
11.750 0.9774 0.03527 0.03197 0.0358 0.0017 1.0000
12.000 0.9643 0.03864 0.03560 0.0383 0.0017 1.0000
12.250 0.9467 0.04270 0.03991 0.0400 0.0017 1.0000
12.500 0.9174 0.04847 0.04598 0.0407 0.0017 1.0000
12.750 0.8842 0.05546 0.05323 0.0396 0.0017 1.0000
13.000 0.8669 0.06077 0.05869 0.0377 0.0017 1.0000
13.250 0.8350 0.06919 0.06730 0.0337 0.0018 1.0000
13.500 0.8130 0.07702 0.07527 0.0291 0.0018 1.0000
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Polar data table (+)
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