cr001sm (cr001sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: cr001sm (cr001sm-il) Reynolds number: 200,000 Max Cl/Cd: 89.27 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cr001sm-il-200000.txt Download as CSV file: xf-cr001sm-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: cr001sm
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3624 0.10032 0.09693 -0.0309 1.0000 0.0302
-7.750 -0.3698 0.09862 0.09529 -0.0294 1.0000 0.0303
-7.500 -0.3767 0.09675 0.09350 -0.0284 1.0000 0.0303
-7.250 -0.3793 0.09437 0.09117 -0.0285 1.0000 0.0304
-7.000 -0.3809 0.09186 0.08870 -0.0291 1.0000 0.0304
-6.750 -0.3890 0.08672 0.08364 -0.0275 1.0000 0.0310
-6.500 -0.3906 0.08391 0.08084 -0.0241 1.0000 0.0317
-6.250 -0.3911 0.08151 0.07848 -0.0229 1.0000 0.0321
-6.000 -0.3909 0.07918 0.07618 -0.0219 1.0000 0.0329
-5.750 -0.3895 0.07669 0.07372 -0.0218 1.0000 0.0337
-5.500 -0.3858 0.07395 0.07099 -0.0229 1.0000 0.0346
-5.250 -0.3561 0.06919 0.06619 -0.0307 0.9967 0.0369
-5.000 -0.2882 0.06148 0.05819 -0.0517 0.9911 0.0416
-4.750 -0.2534 0.05359 0.05014 -0.0608 0.9870 0.0433
-4.500 -0.2332 0.05172 0.04836 -0.0609 0.9829 0.0465
-4.250 -0.1908 0.04703 0.04345 -0.0686 0.9778 0.0523
-4.000 -0.1423 0.04068 0.03667 -0.0778 0.9744 0.0575
-3.750 -0.1094 0.03808 0.03401 -0.0808 0.9703 0.0619
-3.500 -0.0684 0.03397 0.02945 -0.0859 0.9650 0.0716
-3.250 -0.0265 0.03130 0.02639 -0.0902 0.9615 0.0846
-3.000 0.0140 0.02884 0.02374 -0.0940 0.9592 0.0991
-2.750 0.0424 0.02692 0.02171 -0.0950 0.9518 0.1141
-2.500 0.0930 0.02067 0.01414 -0.0958 0.9502 0.0477
-2.250 0.1348 0.01859 0.01151 -0.0976 0.9475 0.0444
-2.000 0.1748 0.01715 0.00983 -0.0995 0.9444 0.0442
-1.750 0.2060 0.01607 0.00870 -0.0999 0.9373 0.0464
-1.500 0.2466 0.01528 0.00787 -0.1022 0.9337 0.0531
-1.000 0.3189 0.01367 0.00628 -0.1050 0.9226 0.0730
-0.750 0.3560 0.01166 0.00593 -0.1074 0.9197 0.5356
-0.500 0.4061 0.01042 0.00558 -0.1112 0.9185 1.0000
-0.250 0.4378 0.01033 0.00533 -0.1117 0.9094 1.0000
0.000 0.4796 0.01010 0.00496 -0.1141 0.9049 1.0000
0.250 0.5105 0.01000 0.00476 -0.1144 0.8950 1.0000
0.500 0.5472 0.00982 0.00448 -0.1158 0.8877 1.0000
0.750 0.5801 0.00968 0.00426 -0.1164 0.8778 1.0000
1.000 0.6104 0.00958 0.00410 -0.1165 0.8659 1.0000
1.250 0.6408 0.00949 0.00394 -0.1165 0.8529 1.0000
1.500 0.6705 0.00941 0.00379 -0.1164 0.8385 1.0000
1.750 0.6995 0.00936 0.00369 -0.1161 0.8229 1.0000
2.000 0.7281 0.00936 0.00361 -0.1158 0.8067 1.0000
2.250 0.7546 0.00941 0.00360 -0.1151 0.7886 1.0000
2.500 0.7807 0.00948 0.00361 -0.1144 0.7696 1.0000
2.750 0.8075 0.00958 0.00365 -0.1138 0.7509 1.0000
3.000 0.8328 0.00971 0.00372 -0.1130 0.7304 1.0000
3.250 0.8582 0.00986 0.00380 -0.1122 0.7097 1.0000
3.500 0.8830 0.01003 0.00392 -0.1113 0.6880 1.0000
3.750 0.9077 0.01024 0.00404 -0.1104 0.6658 1.0000
4.000 0.9315 0.01045 0.00424 -0.1094 0.6419 1.0000
4.250 0.9552 0.01070 0.00443 -0.1083 0.6176 1.0000
4.500 0.9784 0.01097 0.00463 -0.1072 0.5921 1.0000
4.750 1.0011 0.01127 0.00485 -0.1060 0.5651 1.0000
5.000 1.0232 0.01160 0.00514 -0.1047 0.5358 1.0000
5.250 1.0447 0.01195 0.00542 -0.1033 0.5038 1.0000
5.500 1.0654 0.01236 0.00574 -0.1018 0.4694 1.0000
5.750 1.0854 0.01282 0.00609 -0.1003 0.4317 1.0000
6.000 1.1046 0.01335 0.00648 -0.0986 0.3905 1.0000
6.250 1.1229 0.01397 0.00696 -0.0969 0.3470 1.0000
6.500 1.1408 0.01466 0.00748 -0.0952 0.3046 1.0000
6.750 1.1585 0.01541 0.00806 -0.0935 0.2665 1.0000
7.000 1.1765 0.01616 0.00867 -0.0919 0.2313 1.0000
7.250 1.1941 0.01695 0.00933 -0.0903 0.1989 1.0000
7.500 1.2121 0.01772 0.01003 -0.0888 0.1668 1.0000
7.750 1.2287 0.01863 0.01079 -0.0872 0.1330 1.0000
8.000 1.2431 0.01977 0.01173 -0.0852 0.0953 1.0000
8.250 1.2537 0.02130 0.01305 -0.0825 0.0658 1.0000
8.500 1.2641 0.02281 0.01455 -0.0797 0.0510 1.0000
8.750 1.2718 0.02452 0.01625 -0.0766 0.0434 1.0000
9.000 1.2847 0.02565 0.01748 -0.0743 0.0377 1.0000
9.250 1.2889 0.02781 0.01966 -0.0709 0.0340 1.0000
9.500 1.3023 0.02918 0.02121 -0.0686 0.0318 1.0000
9.750 1.3150 0.03071 0.02288 -0.0664 0.0294 1.0000
10.000 1.3257 0.03224 0.02444 -0.0642 0.0270 1.0000
10.250 1.3417 0.03570 0.02805 -0.0631 0.0247 1.0000
10.500 1.3551 0.03767 0.03028 -0.0612 0.0238 1.0000
10.750 1.3670 0.04015 0.03306 -0.0591 0.0230 1.0000
11.000 1.3748 0.04295 0.03617 -0.0568 0.0223 1.0000
11.250 1.3777 0.04578 0.03931 -0.0540 0.0218 1.0000
11.500 1.3764 0.04852 0.04234 -0.0511 0.0213 1.0000
11.750 1.3733 0.05093 0.04499 -0.0484 0.0205 1.0000
12.000 1.3690 0.05353 0.04779 -0.0460 0.0199 1.0000
12.250 1.3608 0.05662 0.05110 -0.0438 0.0195 1.0000
12.500 1.3516 0.05984 0.05451 -0.0422 0.0191 1.0000
12.750 1.3391 0.06377 0.05868 -0.0410 0.0189 1.0000
13.000 1.3224 0.06845 0.06364 -0.0404 0.0190 1.0000
13.250 1.3030 0.07381 0.06928 -0.0408 0.0192 1.0000
13.500 1.2812 0.07992 0.07566 -0.0422 0.0194 1.0000
13.750 1.2555 0.08708 0.08310 -0.0451 0.0196 1.0000
14.000 1.2233 0.09629 0.09260 -0.0502 0.0202 1.0000
14.250 1.1874 0.10772 0.10427 -0.0574 0.0211 1.0000
14.500 1.1539 0.12031 0.11705 -0.0659 0.0224 1.0000
14.750 1.1253 0.13305 0.12990 -0.0743 0.0236 1.0000
15.000 1.1013 0.14538 0.14225 -0.0818 0.0246 1.0000
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Polar data table (+)
Polar graphs
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