R140 (original) (r140-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: R140 (original) (r140-il) Reynolds number: 100,000 Max Cl/Cd: 43.22 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-r140-il-100000.txt Download as CSV file: xf-r140-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.6972 0.05537 0.04940 -0.0288 1.0000 0.0401
-7.750 -0.6972 0.05113 0.04511 -0.0263 1.0000 0.0377
-7.500 -0.6998 0.04762 0.04135 -0.0225 1.0000 0.0354
-7.250 -0.7031 0.04356 0.03680 -0.0177 1.0000 0.0321
-7.000 -0.6980 0.04195 0.03450 -0.0125 1.0000 0.0293
-6.750 -0.6906 0.03897 0.03121 -0.0092 1.0000 0.0288
-6.500 -0.6836 0.03667 0.02855 -0.0056 1.0000 0.0292
-6.250 -0.6726 0.03426 0.02583 -0.0027 1.0000 0.0291
-6.000 -0.6619 0.03088 0.02233 -0.0006 1.0000 0.0320
-5.750 -0.6477 0.02934 0.02067 0.0017 1.0000 0.0349
-5.500 -0.6299 0.02751 0.01858 0.0040 1.0000 0.0371
-5.250 -0.6097 0.02567 0.01650 0.0061 1.0000 0.0395
-5.000 -0.5918 0.02382 0.01457 0.0083 1.0000 0.0426
-4.750 -0.5812 0.02226 0.01311 0.0113 1.0000 0.0496
-4.500 -0.5771 0.02075 0.01165 0.0155 1.0000 0.0614
-4.250 -0.5735 0.01948 0.01054 0.0196 1.0000 0.0985
-4.000 -0.5659 0.01871 0.00978 0.0226 1.0000 0.1278
-3.750 -0.5625 0.01741 0.00912 0.0260 1.0000 0.2169
-3.500 -0.5713 0.01559 0.00929 0.0323 0.9989 0.5805
-3.250 -0.5397 0.01583 0.00986 0.0329 0.9891 0.7112
-3.000 -0.5023 0.01662 0.01065 0.0326 0.9808 0.7759
-2.750 -0.4660 0.01707 0.01092 0.0315 0.9715 0.8083
-2.500 -0.4265 0.01757 0.01125 0.0299 0.9636 0.8344
-2.250 -0.3803 0.01812 0.01156 0.0270 0.9573 0.8561
-2.000 -0.3205 0.01921 0.01248 0.0225 0.9543 0.8827
-1.750 -0.2558 0.02021 0.01329 0.0166 0.9507 0.9022
-1.500 -0.1861 0.02064 0.01348 0.0083 0.9474 0.9095
-1.250 -0.1238 0.02078 0.01348 0.0011 0.9433 0.9167
-1.000 -0.0673 0.02085 0.01345 -0.0052 0.9370 0.9233
-0.750 -0.0116 0.02080 0.01330 -0.0115 0.9315 0.9303
-0.500 0.0514 0.02067 0.01312 -0.0191 0.9281 0.9352
-0.250 0.0970 0.02056 0.01298 -0.0235 0.9196 0.9430
0.000 0.1609 0.02027 0.01270 -0.0313 0.9160 0.9472
0.250 0.2030 0.02013 0.01258 -0.0350 0.9069 0.9554
0.500 0.2647 0.01975 0.01225 -0.0423 0.9028 0.9599
0.750 0.3077 0.01960 0.01219 -0.0461 0.8935 0.9687
1.000 0.3648 0.01915 0.01184 -0.0525 0.8869 0.9744
1.250 0.4091 0.01890 0.01170 -0.0565 0.8778 0.9825
1.500 0.4546 0.01858 0.01152 -0.0609 0.8679 0.9897
1.750 0.4998 0.01821 0.01134 -0.0651 0.8584 0.9970
2.000 0.5301 0.01791 0.01116 -0.0661 0.8462 1.0000
2.250 0.5478 0.01773 0.01106 -0.0644 0.8326 1.0000
2.500 0.5656 0.01757 0.01098 -0.0626 0.8192 1.0000
2.750 0.5811 0.01745 0.01094 -0.0603 0.8038 1.0000
3.000 0.5949 0.01703 0.01055 -0.0566 0.7797 1.0000
3.250 0.6079 0.01613 0.00960 -0.0515 0.7420 1.0000
3.500 0.6230 0.01587 0.00936 -0.0483 0.7157 1.0000
3.750 0.6378 0.01575 0.00936 -0.0454 0.6914 1.0000
4.000 0.6531 0.01557 0.00924 -0.0422 0.6619 1.0000
4.250 0.6574 0.01521 0.00870 -0.0363 0.5838 1.0000
4.500 0.6490 0.01596 0.00826 -0.0289 0.3439 1.0000
4.750 0.6348 0.01862 0.00936 -0.0226 0.0994 1.0000
5.000 0.6315 0.02056 0.01089 -0.0170 0.0467 1.0000
5.250 0.6391 0.02148 0.01193 -0.0132 0.0398 1.0000
5.500 0.6429 0.02269 0.01316 -0.0090 0.0362 1.0000
5.750 0.6505 0.02394 0.01445 -0.0053 0.0346 1.0000
6.000 0.6647 0.02537 0.01592 -0.0026 0.0334 1.0000
6.250 0.6862 0.02718 0.01780 -0.0010 0.0324 1.0000
6.500 0.7116 0.02932 0.02019 0.0000 0.0322 1.0000
6.750 0.7362 0.03189 0.02301 0.0012 0.0326 1.0000
7.000 0.7560 0.03464 0.02605 0.0030 0.0333 1.0000
7.250 0.7719 0.03774 0.02945 0.0051 0.0343 1.0000
7.500 0.7853 0.04217 0.03409 0.0071 0.0355 1.0000
7.750 0.7952 0.04355 0.03625 0.0120 0.0401 1.0000
8.000 0.7996 0.04761 0.04070 0.0155 0.0443 1.0000
8.250 0.8044 0.05289 0.04649 0.0195 0.0581 1.0000
10.750 0.6945 0.09713 0.09241 0.0371 0.1116 1.0000
11.000 0.6538 0.10313 0.09841 0.0314 0.1114 1.0000
11.250 0.6030 0.11191 0.10704 0.0194 0.1059 1.0000
11.500 0.6049 0.11591 0.11103 0.0186 0.1024 1.0000
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Polar data table (+)
Polar graphs
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