R140 (original) (r140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: R140 (original) (r140-il) Reynolds number: 1,000,000 Max Cl/Cd: 71.72 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-r140-il-1000000-n5.txt Download as CSV file: xf-r140-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: R140 (original)
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5918 0.08724 0.08571 -0.0300 1.0000 0.0008
-10.750 -0.6074 0.07645 0.07491 -0.0385 1.0000 0.0008
-10.500 -0.6301 0.06811 0.06649 -0.0446 1.0000 0.0008
-10.250 -0.6460 0.06309 0.06139 -0.0473 1.0000 0.0008
-10.000 -0.6683 0.05820 0.05640 -0.0480 1.0000 0.0007
-9.750 -0.6918 0.05398 0.05206 -0.0463 1.0000 0.0007
-9.500 -0.7195 0.05043 0.04839 -0.0412 0.9932 0.0007
-9.250 -0.7250 0.04285 0.04047 -0.0419 0.9680 0.0007
-9.000 -0.7273 0.03222 0.02922 -0.0421 0.9584 0.0006
-8.750 -0.7167 0.02670 0.02314 -0.0416 0.9481 0.0006
-8.500 -0.7024 0.02386 0.01994 -0.0403 0.9340 0.0006
-8.250 -0.6871 0.02161 0.01734 -0.0387 0.9129 0.0006
-8.000 -0.6703 0.01991 0.01534 -0.0370 0.8998 0.0007
-7.750 -0.6527 0.01852 0.01371 -0.0354 0.8909 0.0009
-7.500 -0.6339 0.01744 0.01244 -0.0340 0.8801 0.0010
-7.250 -0.6153 0.01665 0.01146 -0.0324 0.8430 0.0012
-7.000 -0.5972 0.01603 0.01061 -0.0306 0.8224 0.0014
-6.750 -0.5785 0.01523 0.00961 -0.0290 0.8115 0.0014
-6.500 -0.5561 0.01486 0.00916 -0.0282 0.8043 0.0016
-6.250 -0.5336 0.01444 0.00865 -0.0273 0.7962 0.0017
-6.000 -0.5125 0.01398 0.00805 -0.0262 0.7658 0.0020
-5.750 -0.4997 0.01290 0.00673 -0.0234 0.7367 0.0022
-5.500 -0.4824 0.01223 0.00591 -0.0215 0.7214 0.0024
-5.250 -0.4646 0.01158 0.00519 -0.0199 0.7088 0.0034
-5.000 -0.4441 0.01114 0.00465 -0.0185 0.6958 0.0039
-4.750 -0.4232 0.01075 0.00413 -0.0172 0.6833 0.0041
-4.500 -0.4009 0.01041 0.00366 -0.0161 0.6740 0.0040
-4.250 -0.3778 0.01017 0.00329 -0.0152 0.6638 0.0039
-4.000 -0.3539 0.00995 0.00297 -0.0145 0.6539 0.0037
-3.750 -0.3294 0.00974 0.00270 -0.0139 0.6464 0.0036
-3.500 -0.3048 0.00958 0.00246 -0.0133 0.6353 0.0035
-3.250 -0.2798 0.00945 0.00223 -0.0128 0.6223 0.0035
-3.000 -0.2546 0.00933 0.00207 -0.0123 0.6129 0.0035
-2.750 -0.2291 0.00924 0.00192 -0.0120 0.6056 0.0035
-2.500 -0.2034 0.00916 0.00179 -0.0117 0.5999 0.0037
-2.250 -0.1775 0.00907 0.00167 -0.0114 0.5954 0.0045
-2.000 -0.1522 0.00893 0.00154 -0.0110 0.5909 0.0205
-1.750 -0.1260 0.00889 0.00141 -0.0108 0.5862 0.0176
-1.500 -0.0998 0.00881 0.00135 -0.0107 0.5816 0.0221
-1.250 -0.0763 0.00854 0.00124 -0.0100 0.5744 0.0870
-1.000 -0.0509 0.00860 0.00120 -0.0096 0.5489 0.0906
-0.750 -0.0287 0.00882 0.00115 -0.0087 0.4808 0.0938
-0.500 -0.0086 0.00924 0.00120 -0.0075 0.3779 0.0959
-0.250 0.0126 0.00963 0.00129 -0.0064 0.2847 0.0966
0.000 0.0381 0.00968 0.00130 -0.0061 0.2683 0.0977
0.250 0.0616 0.00988 0.00135 -0.0055 0.2137 0.0997
0.500 0.0872 0.00993 0.00137 -0.0052 0.2005 0.1006
0.750 0.1107 0.01017 0.00144 -0.0046 0.1401 0.1010
1.000 0.1356 0.01030 0.00150 -0.0043 0.1171 0.1011
1.250 0.1614 0.01037 0.00154 -0.0040 0.0990 0.1011
1.500 0.1839 0.01069 0.00166 -0.0032 0.0282 0.1013
1.750 0.2089 0.01080 0.00171 -0.0028 0.0077 0.1045
2.000 0.2348 0.01084 0.00180 -0.0026 0.0033 0.1127
2.250 0.2606 0.01090 0.00188 -0.0023 0.0025 0.1150
2.500 0.2861 0.01098 0.00198 -0.0020 0.0023 0.1183
2.750 0.3116 0.01106 0.00213 -0.0017 0.0024 0.1200
3.000 0.3369 0.01119 0.00230 -0.0012 0.0023 0.1204
3.250 0.3619 0.01132 0.00248 -0.0008 0.0023 0.1207
3.500 0.3867 0.01147 0.00270 -0.0003 0.0024 0.1218
3.750 0.4109 0.01167 0.00298 0.0004 0.0025 0.1223
4.000 0.4347 0.01192 0.00334 0.0012 0.0027 0.1223
4.250 0.4577 0.01222 0.00376 0.0021 0.0029 0.1224
4.500 0.4796 0.01258 0.00424 0.0033 0.0031 0.1252
4.750 0.4994 0.01311 0.00490 0.0049 0.0034 0.1258
6.250 0.5974 0.00833 0.00121 0.0148 0.0040 0.1851
6.500 0.6185 0.00981 0.00286 0.0159 0.0040 0.1896
6.750 0.6325 0.01057 0.00436 0.0180 0.0040 0.4367
7.000 0.6486 0.01213 0.00622 0.0198 0.0040 0.4744
7.250 0.6598 0.01355 0.00815 0.0223 0.0040 0.5858
7.500 0.6716 0.01558 0.01043 0.0245 0.0040 0.5928
7.750 0.6805 0.01776 0.01286 0.0271 0.0040 0.6019
8.000 0.6859 0.02000 0.01539 0.0302 0.0039 0.6304
8.250 0.6891 0.02241 0.01802 0.0332 0.0039 0.6352
8.500 0.6873 0.02504 0.02089 0.0369 0.0039 0.6476
8.750 0.6826 0.02760 0.02364 0.0407 0.0039 0.6512
9.000 0.6707 0.02975 0.02596 0.0456 0.0039 0.6572
9.250 0.6565 0.03219 0.02851 0.0500 0.0039 0.6527
9.500 0.6414 0.03470 0.03114 0.0534 0.0039 0.6507
9.750 0.6252 0.03746 0.03404 0.0560 0.0039 0.6545
10.000 0.6068 0.04069 0.03742 0.0577 0.0039 0.6619
10.250 0.5895 0.04420 0.04105 0.0583 0.0039 0.6663
10.500 0.5694 0.04845 0.04548 0.0582 0.0039 0.6896
10.750 0.5488 0.05380 0.05091 0.0567 0.0039 0.6862
11.000 0.5299 0.05974 0.05690 0.0543 0.0039 0.6746
11.250 0.5088 0.06709 0.06431 0.0506 0.0039 0.6677
11.500 0.4902 0.07520 0.07251 0.0461 0.0039 0.6679
11.750 0.4750 0.08563 0.08295 0.0402 0.0039 0.6560
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Polar data table (+)
Polar graphs
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