R140 (original) (r140-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: R140 (original) (r140-il) Reynolds number: 200,000 Max Cl/Cd: 33.42 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-r140-il-200000-n5.txt Download as CSV file: xf-r140-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5627 0.08702 0.08358 -0.0340 1.0000 0.0046
-10.500 -0.5749 0.07817 0.07473 -0.0401 1.0000 0.0045
-10.250 -0.5895 0.07166 0.06816 -0.0444 1.0000 0.0044
-10.000 -0.6074 0.06603 0.06245 -0.0472 1.0000 0.0044
-9.750 -0.6264 0.06134 0.05764 -0.0481 1.0000 0.0044
-9.500 -0.6458 0.05721 0.05338 -0.0472 1.0000 0.0044
-9.250 -0.6621 0.05427 0.05032 -0.0447 1.0000 0.0043
-9.000 -0.6796 0.05155 0.04747 -0.0406 1.0000 0.0043
-8.750 -0.6945 0.04846 0.04421 -0.0361 1.0000 0.0043
-8.500 -0.7044 0.04554 0.04109 -0.0320 1.0000 0.0042
-8.250 -0.7121 0.04244 0.03775 -0.0277 1.0000 0.0042
-8.000 -0.7177 0.03927 0.03428 -0.0231 1.0000 0.0043
-7.750 -0.7204 0.03640 0.03109 -0.0186 1.0000 0.0044
-7.500 -0.7201 0.03390 0.02828 -0.0143 1.0000 0.0044
-7.250 -0.7120 0.03171 0.02576 -0.0113 0.9991 0.0047
-7.000 -0.6922 0.02765 0.02112 -0.0111 0.9931 0.0060
-6.750 -0.6655 0.02589 0.01910 -0.0117 0.9874 0.0068
-6.500 -0.6370 0.02431 0.01728 -0.0124 0.9822 0.0078
-6.250 -0.6088 0.02205 0.01473 -0.0125 0.9769 0.0077
-6.000 -0.5788 0.02019 0.01267 -0.0132 0.9725 0.0076
-5.750 -0.5523 0.01879 0.01110 -0.0132 0.9659 0.0075
-5.500 -0.5223 0.01759 0.00972 -0.0140 0.9607 0.0075
-5.250 -0.4937 0.01665 0.00858 -0.0145 0.9540 0.0075
-5.000 -0.4629 0.01589 0.00757 -0.0154 0.9475 0.0076
-4.750 -0.4347 0.01534 0.00684 -0.0156 0.9388 0.0078
-4.500 -0.4054 0.01488 0.00622 -0.0161 0.9301 0.0080
-4.250 -0.3773 0.01452 0.00569 -0.0163 0.9198 0.0083
-4.000 -0.3488 0.01412 0.00518 -0.0166 0.9100 0.0093
-3.750 -0.3210 0.01357 0.00470 -0.0168 0.9004 0.0361
-3.500 -0.2907 0.01331 0.00433 -0.0174 0.8901 0.0471
-3.250 -0.2662 0.01294 0.00397 -0.0170 0.8761 0.0905
-3.000 -0.2453 0.01251 0.00371 -0.0158 0.8586 0.1253
-2.750 -0.2474 0.01042 0.00319 -0.0109 0.8401 0.4725
-2.500 -0.2278 0.01000 0.00314 -0.0091 0.8281 0.5824
-2.250 -0.2002 0.00992 0.00298 -0.0090 0.8180 0.6033
-2.000 -0.1733 0.00987 0.00285 -0.0088 0.8078 0.6209
-1.750 -0.1474 0.00985 0.00264 -0.0084 0.7964 0.6363
-1.500 -0.1235 0.00976 0.00259 -0.0076 0.7827 0.6582
-1.250 -0.0988 0.00967 0.00252 -0.0070 0.7700 0.6791
-1.000 -0.0728 0.00960 0.00245 -0.0065 0.7593 0.6956
-0.750 -0.0461 0.00956 0.00240 -0.0063 0.7494 0.7065
-0.500 -0.0194 0.00955 0.00239 -0.0061 0.7400 0.7161
-0.250 0.0073 0.00956 0.00239 -0.0058 0.7311 0.7282
0.000 0.0336 0.00958 0.00239 -0.0056 0.7224 0.7415
0.250 0.0598 0.00961 0.00243 -0.0053 0.7139 0.7551
0.500 0.0868 0.00964 0.00248 -0.0051 0.7062 0.7688
0.750 0.1133 0.00967 0.00255 -0.0049 0.6975 0.7846
1.000 0.1391 0.00972 0.00260 -0.0045 0.6894 0.8025
1.250 0.1661 0.00977 0.00269 -0.0043 0.6815 0.8163
1.500 0.1943 0.00982 0.00279 -0.0044 0.6735 0.8287
1.750 0.2226 0.00989 0.00288 -0.0045 0.6662 0.8411
2.000 0.2497 0.00994 0.00298 -0.0044 0.6562 0.8538
2.250 0.2762 0.00999 0.00302 -0.0041 0.6378 0.8662
2.500 0.2983 0.01014 0.00296 -0.0027 0.5766 0.8780
2.750 0.3283 0.01030 0.00308 -0.0032 0.5431 0.8878
3.000 0.3369 0.01176 0.00329 0.0000 0.2777 0.9003
3.250 0.3497 0.01363 0.00409 0.0017 0.0187 0.9126
3.500 0.3800 0.01401 0.00441 0.0010 0.0074 0.9227
3.750 0.4095 0.01430 0.00489 0.0005 0.0061 0.9329
4.000 0.4412 0.01466 0.00546 -0.0005 0.0057 0.9398
4.250 0.4705 0.01504 0.00601 -0.0010 0.0055 0.9473
4.500 0.5024 0.01551 0.00666 -0.0021 0.0055 0.9532
4.750 0.5310 0.01607 0.00738 -0.0025 0.0054 0.9602
5.000 0.5605 0.01677 0.00827 -0.0032 0.0055 0.9656
5.250 0.5860 0.01761 0.00926 -0.0031 0.0055 0.9732
5.500 0.6138 0.01868 0.01049 -0.0036 0.0056 0.9812
5.750 0.6407 0.01996 0.01191 -0.0039 0.0058 0.9888
6.000 0.6714 0.02149 0.01359 -0.0050 0.0060 0.9961
6.250 0.7005 0.02321 0.01554 -0.0055 0.0062 1.0000
6.500 0.7161 0.02487 0.01738 -0.0031 0.0065 1.0000
6.750 0.7322 0.02663 0.01935 -0.0009 0.0067 1.0000
7.000 0.7473 0.02876 0.02173 0.0015 0.0070 1.0000
7.250 0.7595 0.03114 0.02440 0.0042 0.0073 1.0000
7.500 0.7685 0.03365 0.02721 0.0072 0.0075 1.0000
7.750 0.7741 0.03637 0.03022 0.0105 0.0078 1.0000
8.000 0.7754 0.03953 0.03366 0.0142 0.0080 1.0000
8.250 0.7775 0.04246 0.03684 0.0174 0.0083 1.0000
8.500 0.7871 0.04346 0.03798 0.0201 0.0086 1.0000
8.750 0.7929 0.04497 0.03969 0.0232 0.0089 1.0000
9.000 0.7920 0.04836 0.04346 0.0273 0.0098 1.0000
9.250 0.7773 0.05280 0.04825 0.0323 0.0107 1.0000
9.500 0.7606 0.05578 0.05142 0.0369 0.0111 1.0000
9.750 0.7436 0.05874 0.05453 0.0404 0.0113 1.0000
10.000 0.7244 0.06229 0.05825 0.0425 0.0116 1.0000
10.250 0.7085 0.06566 0.06174 0.0432 0.0116 1.0000
10.500 0.6894 0.07000 0.06621 0.0426 0.0116 1.0000
10.750 0.6696 0.07518 0.07149 0.0406 0.0117 1.0000
11.000 0.6532 0.08058 0.07698 0.0376 0.0115 1.0000
11.250 0.6349 0.08790 0.08435 0.0328 0.0114 1.0000
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Polar data table (+)
Polar graphs
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