R140 (original) (r140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: R140 (original) (r140-il) Reynolds number: 1,000,000 Max Cl/Cd: 50.79 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-r140-il-1000000.txt Download as CSV file: xf-r140-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4617 0.09433 0.09284 -0.0315 1.0000 0.0065
-11.250 -0.4805 0.08513 0.08366 -0.0348 1.0000 0.0061
-11.000 -0.5001 0.07272 0.07126 -0.0398 1.0000 0.0056
-10.750 -0.5082 0.06500 0.06349 -0.0435 1.0000 0.0054
-10.500 -0.5129 0.06024 0.05868 -0.0458 1.0000 0.0053
-10.250 -0.5220 0.05557 0.05395 -0.0479 1.0000 0.0052
-10.000 -0.5367 0.05086 0.04916 -0.0496 1.0000 0.0052
-9.750 -0.5551 0.04655 0.04475 -0.0506 1.0000 0.0052
-9.500 -0.5769 0.04255 0.04065 -0.0503 1.0000 0.0052
-9.250 -0.5983 0.03929 0.03729 -0.0486 1.0000 0.0052
-9.000 -0.6190 0.03642 0.03430 -0.0453 1.0000 0.0052
-8.750 -0.6389 0.03405 0.03183 -0.0403 1.0000 0.0052
-8.500 -0.6557 0.03193 0.02961 -0.0348 1.0000 0.0052
-8.250 -0.6622 0.02852 0.02600 -0.0316 0.9982 0.0052
-6.000 -0.5144 0.01283 0.00759 -0.0280 0.9510 0.0065
-5.750 -0.4844 0.01238 0.00705 -0.0284 0.9431 0.0054
-5.500 -0.4680 0.01129 0.00580 -0.0261 0.9301 0.0047
-5.250 -0.4495 0.01052 0.00486 -0.0241 0.9164 0.0043
-5.000 -0.4276 0.01005 0.00421 -0.0228 0.9047 0.0041
-4.750 -0.4050 0.00968 0.00370 -0.0217 0.8935 0.0041
-4.500 -0.3821 0.00940 0.00330 -0.0206 0.8815 0.0042
-4.250 -0.3594 0.00912 0.00290 -0.0195 0.8658 0.0049
-4.000 -0.3366 0.00895 0.00261 -0.0184 0.8386 0.0055
-3.750 -0.3137 0.00887 0.00238 -0.0174 0.8195 0.0072
-3.500 -0.2911 0.00868 0.00221 -0.0164 0.8063 0.0244
-3.250 -0.2671 0.00852 0.00207 -0.0157 0.7919 0.0407
-2.750 -0.2182 0.00837 0.00179 -0.0145 0.7526 0.0486
-2.500 -0.1942 0.00827 0.00167 -0.0138 0.7393 0.0615
-2.250 -0.1712 0.00808 0.00156 -0.0130 0.7281 0.1015
-1.750 -0.1471 0.00610 0.00101 -0.0076 0.7050 0.5067
-1.500 -0.1250 0.00589 0.00098 -0.0066 0.6940 0.5640
-1.250 -0.1001 0.00585 0.00095 -0.0060 0.6825 0.5908
-1.000 -0.0750 0.00583 0.00094 -0.0056 0.6724 0.6088
-0.750 -0.0493 0.00583 0.00093 -0.0052 0.6631 0.6270
-0.500 -0.0228 0.00582 0.00092 -0.0050 0.6545 0.6379
-0.250 0.0035 0.00583 0.00091 -0.0048 0.6467 0.6484
0.000 0.0303 0.00582 0.00090 -0.0047 0.6377 0.6570
0.250 0.0565 0.00581 0.00089 -0.0044 0.6258 0.6648
0.750 0.1089 0.00583 0.00088 -0.0040 0.6069 0.6797
1.000 0.1355 0.00584 0.00089 -0.0038 0.6001 0.6871
1.250 0.1611 0.00583 0.00091 -0.0035 0.5932 0.6970
1.500 0.1865 0.00579 0.00094 -0.0031 0.5861 0.7103
1.750 0.2108 0.00576 0.00100 -0.0024 0.5764 0.7314
2.000 0.2339 0.00572 0.00106 -0.0014 0.5629 0.7692
2.250 0.2579 0.00572 0.00113 -0.0007 0.5477 0.7994
2.500 0.2826 0.00575 0.00118 -0.0001 0.5291 0.8190
2.750 0.2972 0.00638 0.00131 0.0024 0.3965 0.8336
3.000 0.2978 0.00810 0.00193 0.0071 0.0977 0.8506
3.250 0.3157 0.00868 0.00219 0.0089 0.0074 0.8646
3.500 0.3404 0.00880 0.00232 0.0094 0.0058 0.8772
3.750 0.3658 0.00890 0.00253 0.0099 0.0056 0.8909
4.000 0.3922 0.00904 0.00277 0.0101 0.0055 0.9059
4.250 0.4203 0.00920 0.00305 0.0100 0.0056 0.9229
4.500 0.4495 0.00942 0.00339 0.0095 0.0058 0.9366
4.750 0.4816 0.00971 0.00376 0.0084 0.0061 0.9465
5.000 0.5135 0.01013 0.00429 0.0074 0.0065 0.9553
5.250 0.5485 0.01080 0.00510 0.0056 0.0070 0.9602
5.500 0.5772 0.01195 0.00642 0.0050 0.0074 0.9673
5.750 0.6095 0.01292 0.00748 0.0036 0.0073 0.9721
6.000 0.6382 0.01374 0.00837 0.0031 0.0070 0.9784
6.750 0.7241 0.01811 0.01310 0.0018 0.0067 0.9894
7.000 0.7532 0.01902 0.01411 0.0011 0.0056 0.9925
7.250 0.7810 0.02018 0.01537 0.0003 0.0046 0.9950
7.500 0.8083 0.02226 0.01764 -0.0003 0.0042 0.9970
8.000 0.8174 0.03264 0.02898 0.0059 0.0036 1.0000
8.250 0.8144 0.03502 0.03158 0.0107 0.0036 1.0000
8.500 0.8119 0.03725 0.03401 0.0151 0.0036 1.0000
8.750 0.8049 0.03995 0.03692 0.0199 0.0036 1.0000
9.000 0.7951 0.04271 0.03988 0.0246 0.0036 1.0000
9.250 0.7825 0.04506 0.04238 0.0297 0.0036 1.0000
9.500 0.7660 0.04737 0.04483 0.0347 0.0036 1.0000
9.750 0.7512 0.05002 0.04761 0.0380 0.0036 1.0000
10.000 0.7359 0.05312 0.05085 0.0402 0.0036 1.0000
10.250 0.7196 0.05679 0.05465 0.0411 0.0036 1.0000
10.500 0.7005 0.06140 0.05939 0.0407 0.0036 1.0000
10.750 0.6859 0.06586 0.06395 0.0391 0.0036 1.0000
11.000 0.6668 0.07203 0.07023 0.0361 0.0036 1.0000
11.250 0.6501 0.07876 0.07705 0.0320 0.0036 1.0000
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Polar data table (+)
Polar graphs
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