R140 12.04% (smoothed) (r140sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: R140 12.04% (smoothed) (r140sm-il) Reynolds number: 200,000 Max Cl/Cd: 46.55 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-r140sm-il-200000-n5.txt Download as CSV file: xf-r140sm-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5579 0.11377 0.11012 -0.0222 1.0000 0.0109
-12.000 -0.5629 0.10826 0.10465 -0.0244 1.0000 0.0107
-11.750 -0.5679 0.10273 0.09915 -0.0268 1.0000 0.0105
-11.500 -0.5754 0.09611 0.09257 -0.0300 1.0000 0.0104
-11.250 -0.5835 0.08876 0.08526 -0.0342 1.0000 0.0102
-11.000 -0.6011 0.07894 0.07541 -0.0408 1.0000 0.0100
-10.750 -0.6202 0.07190 0.06829 -0.0452 1.0000 0.0099
-10.500 -0.6369 0.06696 0.06327 -0.0477 1.0000 0.0097
-10.250 -0.6572 0.06214 0.05832 -0.0488 1.0000 0.0097
-10.000 -0.6755 0.05841 0.05446 -0.0482 1.0000 0.0096
-9.750 -0.6939 0.05510 0.05102 -0.0460 1.0000 0.0096
-9.500 -0.7122 0.05216 0.04792 -0.0421 1.0000 0.0096
-9.250 -0.7288 0.04934 0.04493 -0.0375 1.0000 0.0095
-9.000 -0.7397 0.04632 0.04168 -0.0334 1.0000 0.0095
-8.750 -0.7481 0.04320 0.03830 -0.0292 1.0000 0.0094
-8.500 -0.7527 0.04026 0.03507 -0.0250 1.0000 0.0094
-8.250 -0.7549 0.03734 0.03183 -0.0208 1.0000 0.0095
-8.000 -0.7544 0.03458 0.02873 -0.0167 1.0000 0.0095
-7.750 -0.7506 0.03214 0.02596 -0.0129 1.0000 0.0097
-7.500 -0.7440 0.02996 0.02345 -0.0094 1.0000 0.0099
-7.250 -0.7349 0.02793 0.02110 -0.0062 1.0000 0.0102
-7.000 -0.7088 0.02582 0.01865 -0.0063 0.9968 0.0106
-6.750 -0.6800 0.02347 0.01595 -0.0070 0.9926 0.0115
-6.500 -0.6512 0.02188 0.01426 -0.0080 0.9876 0.0131
-6.250 -0.6208 0.02071 0.01297 -0.0091 0.9827 0.0147
-6.000 -0.5924 0.01933 0.01146 -0.0096 0.9765 0.0160
-5.750 -0.5629 0.01816 0.01016 -0.0104 0.9711 0.0174
-5.500 -0.5363 0.01715 0.00904 -0.0106 0.9636 0.0194
-5.250 -0.5059 0.01619 0.00801 -0.0118 0.9581 0.0238
-5.000 -0.4784 0.01549 0.00713 -0.0120 0.9497 0.0274
-4.750 -0.4489 0.01473 0.00633 -0.0127 0.9426 0.0379
-4.500 -0.4220 0.01395 0.00570 -0.0130 0.9339 0.0738
-4.250 -0.3986 0.01306 0.00513 -0.0128 0.9238 0.1508
-4.000 -0.3878 0.01134 0.00446 -0.0106 0.9116 0.3778
-3.750 -0.3737 0.01051 0.00435 -0.0080 0.8997 0.5440
-3.500 -0.3473 0.01032 0.00417 -0.0075 0.8899 0.5954
-3.250 -0.3214 0.01020 0.00400 -0.0070 0.8783 0.6240
-3.000 -0.2962 0.01007 0.00386 -0.0063 0.8664 0.6530
-2.750 -0.2702 0.00994 0.00374 -0.0057 0.8546 0.6767
-2.500 -0.2434 0.00984 0.00359 -0.0054 0.8427 0.6943
-2.250 -0.2159 0.00975 0.00342 -0.0052 0.8308 0.7071
-2.000 -0.1881 0.00968 0.00328 -0.0052 0.8190 0.7170
-1.750 -0.1605 0.00962 0.00314 -0.0051 0.8073 0.7266
-1.500 -0.1333 0.00958 0.00303 -0.0050 0.7955 0.7362
-1.250 -0.1060 0.00955 0.00294 -0.0048 0.7840 0.7459
-1.000 -0.0790 0.00953 0.00288 -0.0047 0.7732 0.7563
-0.750 -0.0520 0.00953 0.00282 -0.0045 0.7630 0.7674
-0.500 -0.0249 0.00954 0.00279 -0.0043 0.7534 0.7787
-0.250 0.0022 0.00955 0.00278 -0.0042 0.7438 0.7900
0.000 0.0296 0.00958 0.00279 -0.0041 0.7350 0.8015
0.250 0.0570 0.00961 0.00281 -0.0040 0.7266 0.8131
0.500 0.0844 0.00965 0.00286 -0.0039 0.7184 0.8249
1.000 0.1397 0.00975 0.00297 -0.0039 0.7030 0.8484
1.250 0.1696 0.00982 0.00305 -0.0044 0.6965 0.8588
1.500 0.1995 0.00989 0.00319 -0.0049 0.6891 0.8692
1.750 0.2297 0.00999 0.00329 -0.0054 0.6829 0.8796
2.000 0.2592 0.01007 0.00344 -0.0059 0.6757 0.8904
2.250 0.2934 0.01020 0.00360 -0.0073 0.6698 0.8981
2.500 0.3250 0.01030 0.00381 -0.0082 0.6628 0.9070
2.750 0.3575 0.01043 0.00399 -0.0092 0.6563 0.9152
3.000 0.3903 0.01054 0.00416 -0.0103 0.6440 0.9221
3.250 0.4195 0.01063 0.00428 -0.0106 0.6260 0.9305
3.500 0.4528 0.01074 0.00448 -0.0118 0.6069 0.9360
3.750 0.4831 0.01086 0.00464 -0.0123 0.5876 0.9430
4.000 0.5125 0.01101 0.00471 -0.0126 0.5353 0.9489
4.250 0.5313 0.01172 0.00478 -0.0111 0.3851 0.9575
4.500 0.5437 0.01385 0.00564 -0.0098 0.1306 0.9657
4.750 0.5657 0.01493 0.00640 -0.0095 0.0507 0.9737
5.000 0.5949 0.01576 0.00715 -0.0104 0.0269 0.9791
5.250 0.6220 0.01656 0.00802 -0.0108 0.0205 0.9857
5.500 0.6520 0.01732 0.00895 -0.0118 0.0185 0.9908
5.750 0.6798 0.01827 0.01003 -0.0124 0.0168 0.9963
6.000 0.7044 0.01923 0.01105 -0.0126 0.0146 1.0000
6.250 0.7094 0.02036 0.01224 -0.0088 0.0132 1.0000
6.500 0.7186 0.02140 0.01334 -0.0056 0.0124 1.0000
6.750 0.7311 0.02237 0.01445 -0.0029 0.0119 1.0000
7.000 0.7453 0.02357 0.01576 -0.0005 0.0114 1.0000
7.250 0.7614 0.02496 0.01730 0.0016 0.0109 1.0000
7.500 0.7785 0.02656 0.01908 0.0034 0.0106 1.0000
7.750 0.7952 0.02842 0.02117 0.0054 0.0103 1.0000
8.000 0.8100 0.03047 0.02349 0.0075 0.0101 1.0000
8.250 0.8221 0.03225 0.02551 0.0099 0.0096 1.0000
8.500 0.8324 0.03347 0.02688 0.0123 0.0088 1.0000
8.750 0.8404 0.03527 0.02890 0.0150 0.0084 1.0000
9.000 0.8451 0.03663 0.03036 0.0177 0.0078 1.0000
9.250 0.8423 0.03969 0.03369 0.0213 0.0074 1.0000
9.500 0.8384 0.04242 0.03670 0.0250 0.0074 1.0000
9.750 0.8298 0.04498 0.03951 0.0293 0.0073 1.0000
10.000 0.8143 0.04761 0.04237 0.0341 0.0072 1.0000
10.500 0.7871 0.05304 0.04827 0.0402 0.0071 1.0000
10.750 0.7716 0.05649 0.05188 0.0417 0.0072 1.0000
11.000 0.7567 0.06014 0.05567 0.0423 0.0073 1.0000
11.500 0.7222 0.06909 0.06495 0.0406 0.0072 1.0000
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Polar data table (+)
Polar graphs
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