MRC-20 (mrc-20-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MRC-20 (mrc-20-il) Reynolds number: 500,000 Max Cl/Cd: 86.62 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mrc-20-il-500000-n5.txt Download as CSV file: xf-mrc-20-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MRC-20
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1449 0.08180 0.07934 -0.0993 0.9639 0.0124
-11.000 -0.1419 0.07869 0.07623 -0.1003 0.9617 0.0126
-10.500 -0.2835 0.06753 0.06491 -0.1108 0.9664 0.0096
-10.250 -0.2968 0.06204 0.05934 -0.1155 0.9614 0.0095
-10.000 -0.3133 0.05774 0.05495 -0.1175 0.9544 0.0094
-9.750 -0.3278 0.05422 0.05130 -0.1176 0.9477 0.0094
-9.500 -0.3416 0.05127 0.04823 -0.1158 0.9404 0.0093
-9.250 -0.3506 0.04811 0.04491 -0.1138 0.9342 0.0093
-9.000 -0.3548 0.04470 0.04130 -0.1120 0.9292 0.0092
-8.750 -0.3578 0.04099 0.03736 -0.1097 0.9228 0.0092
-8.500 -0.3592 0.03643 0.03248 -0.1070 0.9179 0.0092
-8.250 -0.3730 0.02757 0.02283 -0.1019 0.9116 0.0094
-8.000 -0.3651 0.02347 0.01812 -0.0992 0.9065 0.0096
-7.750 -0.3470 0.02173 0.01615 -0.0981 0.9030 0.0097
-7.500 -0.3252 0.02065 0.01492 -0.0975 0.9001 0.0099
-7.250 -0.3048 0.01971 0.01386 -0.0965 0.8951 0.0100
-7.000 -0.2824 0.01879 0.01281 -0.0958 0.8908 0.0102
-6.750 -0.2585 0.01789 0.01177 -0.0954 0.8874 0.0104
-6.500 -0.2343 0.01717 0.01094 -0.0949 0.8837 0.0107
-6.250 -0.2115 0.01652 0.01021 -0.0942 0.8785 0.0111
-6.000 -0.1874 0.01579 0.00935 -0.0936 0.8741 0.0115
-5.750 -0.1624 0.01504 0.00848 -0.0932 0.8704 0.0118
-5.500 -0.1402 0.01443 0.00779 -0.0923 0.8648 0.0120
-5.250 -0.1169 0.01387 0.00715 -0.0916 0.8594 0.0122
-5.000 -0.0934 0.01323 0.00647 -0.0909 0.8550 0.0125
-4.750 -0.0712 0.01283 0.00605 -0.0901 0.8487 0.0129
-4.500 -0.0473 0.01244 0.00562 -0.0895 0.8429 0.0133
-4.250 -0.0229 0.01207 0.00521 -0.0889 0.8374 0.0138
-4.000 0.0004 0.01174 0.00483 -0.0882 0.8305 0.0144
-3.750 0.0257 0.01143 0.00445 -0.0877 0.8245 0.0149
-3.500 0.0490 0.01112 0.00413 -0.0870 0.8171 0.0156
-3.250 0.0745 0.01090 0.00387 -0.0867 0.8101 0.0169
-3.000 0.0994 0.01071 0.00363 -0.0862 0.8025 0.0181
-2.750 0.1244 0.01048 0.00336 -0.0857 0.7945 0.0195
-2.500 0.1495 0.01031 0.00315 -0.0852 0.7859 0.0214
-2.250 0.1750 0.01014 0.00294 -0.0848 0.7772 0.0245
-2.000 0.1999 0.01000 0.00279 -0.0843 0.7676 0.0306
-1.750 0.2246 0.00982 0.00263 -0.0838 0.7582 0.0491
-1.500 0.2481 0.00955 0.00250 -0.0831 0.7480 0.1046
-1.250 0.2579 0.00812 0.00218 -0.0804 0.7380 0.4686
-1.000 0.2806 0.00793 0.00216 -0.0795 0.7282 0.5377
-0.750 0.3043 0.00784 0.00216 -0.0787 0.7175 0.5820
-0.500 0.3278 0.00777 0.00218 -0.0779 0.7073 0.6230
-0.250 0.3526 0.00778 0.00217 -0.0773 0.6966 0.6430
0.000 0.3782 0.00781 0.00216 -0.0769 0.6853 0.6502
0.250 0.4037 0.00786 0.00216 -0.0765 0.6742 0.6589
0.500 0.4288 0.00791 0.00217 -0.0760 0.6631 0.6676
0.750 0.4537 0.00797 0.00219 -0.0755 0.6512 0.6773
1.000 0.4787 0.00802 0.00222 -0.0750 0.6397 0.6868
1.250 0.5034 0.00810 0.00225 -0.0745 0.6281 0.6973
1.500 0.5275 0.00817 0.00231 -0.0738 0.6163 0.7086
1.750 0.5518 0.00824 0.00237 -0.0732 0.6040 0.7212
2.000 0.5760 0.00832 0.00244 -0.0726 0.5922 0.7351
2.250 0.5997 0.00841 0.00252 -0.0719 0.5799 0.7499
2.500 0.6229 0.00851 0.00261 -0.0711 0.5676 0.7653
2.750 0.6461 0.00860 0.00272 -0.0703 0.5546 0.7824
3.000 0.6693 0.00869 0.00283 -0.0694 0.5423 0.8016
3.250 0.6918 0.00880 0.00296 -0.0685 0.5296 0.8219
3.500 0.7138 0.00892 0.00310 -0.0674 0.5171 0.8432
4.000 0.7568 0.00918 0.00341 -0.0650 0.4909 0.8905
4.250 0.7789 0.00935 0.00359 -0.0639 0.4777 0.9155
4.500 0.8042 0.00957 0.00380 -0.0636 0.4643 0.9390
4.750 0.8338 0.00982 0.00402 -0.0643 0.4504 0.9580
5.000 0.8648 0.01010 0.00425 -0.0655 0.4359 0.9741
5.250 0.8954 0.01039 0.00450 -0.0666 0.4214 0.9876
5.500 0.9260 0.01069 0.00474 -0.0677 0.4071 0.9985
5.750 0.9434 0.01091 0.00492 -0.0660 0.3945 1.0000
6.000 0.9597 0.01114 0.00511 -0.0639 0.3829 1.0000
6.250 0.9767 0.01141 0.00534 -0.0621 0.3706 1.0000
6.500 0.9941 0.01172 0.00560 -0.0604 0.3580 1.0000
6.750 1.0124 0.01202 0.00587 -0.0590 0.3450 1.0000
7.000 1.0313 0.01234 0.00615 -0.0576 0.3320 1.0000
7.250 1.0497 0.01269 0.00646 -0.0563 0.3189 1.0000
7.500 1.0680 0.01306 0.00680 -0.0549 0.3057 1.0000
7.750 1.0861 0.01347 0.00716 -0.0536 0.2917 1.0000
8.000 1.1036 0.01390 0.00755 -0.0522 0.2772 1.0000
8.250 1.1207 0.01438 0.00797 -0.0507 0.2622 1.0000
8.500 1.1375 0.01488 0.00843 -0.0493 0.2465 1.0000
8.750 1.1534 0.01544 0.00893 -0.0478 0.2299 1.0000
9.000 1.1687 0.01605 0.00947 -0.0462 0.2128 1.0000
9.250 1.1835 0.01669 0.01005 -0.0446 0.1960 1.0000
9.500 1.1979 0.01737 0.01067 -0.0430 0.1803 1.0000
9.750 1.2120 0.01809 0.01132 -0.0414 0.1653 1.0000
10.000 1.2253 0.01885 0.01203 -0.0397 0.1506 1.0000
10.250 1.2384 0.01965 0.01278 -0.0381 0.1366 1.0000
10.500 1.2506 0.02051 0.01360 -0.0364 0.1232 1.0000
10.750 1.2627 0.02139 0.01444 -0.0348 0.1107 1.0000
11.000 1.2743 0.02233 0.01535 -0.0332 0.0993 1.0000
11.250 1.2855 0.02331 0.01630 -0.0316 0.0888 1.0000
11.500 1.2961 0.02434 0.01732 -0.0300 0.0794 1.0000
11.750 1.3061 0.02544 0.01841 -0.0284 0.0710 1.0000
12.000 1.3156 0.02660 0.01956 -0.0268 0.0636 1.0000
12.250 1.3246 0.02781 0.02077 -0.0253 0.0569 1.0000
12.500 1.3338 0.02904 0.02203 -0.0239 0.0512 1.0000
12.750 1.3418 0.03040 0.02340 -0.0224 0.0461 1.0000
13.000 1.3496 0.03183 0.02485 -0.0211 0.0415 1.0000
13.250 1.3575 0.03327 0.02633 -0.0199 0.0381 1.0000
13.500 1.3640 0.03487 0.02797 -0.0186 0.0349 1.0000
13.750 1.3714 0.03646 0.02961 -0.0176 0.0325 1.0000
14.000 1.3774 0.03821 0.03142 -0.0166 0.0302 1.0000
14.250 1.3828 0.04006 0.03333 -0.0156 0.0282 1.0000
14.500 1.3884 0.04194 0.03527 -0.0147 0.0265 1.0000
14.750 1.3920 0.04406 0.03746 -0.0139 0.0250 1.0000
15.000 1.3954 0.04627 0.03973 -0.0133 0.0237 1.0000
15.250 1.3995 0.04847 0.04203 -0.0127 0.0227 1.0000
15.500 1.4018 0.05089 0.04453 -0.0122 0.0217 1.0000
15.750 1.4025 0.05355 0.04726 -0.0118 0.0208 1.0000
16.000 1.4019 0.05643 0.05022 -0.0116 0.0201 1.0000
16.250 1.4032 0.05916 0.05305 -0.0115 0.0194 1.0000
16.500 1.4032 0.06210 0.05609 -0.0114 0.0188 1.0000
16.750 1.4019 0.06524 0.05933 -0.0115 0.0182 1.0000
17.000 1.3991 0.06861 0.06279 -0.0118 0.0176 1.0000
17.250 1.3949 0.07226 0.06653 -0.0121 0.0171 1.0000
17.500 1.3887 0.07623 0.07059 -0.0127 0.0167 1.0000
17.750 1.3853 0.07989 0.07437 -0.0133 0.0163 1.0000
18.000 1.3806 0.08377 0.07836 -0.0140 0.0160 1.0000
18.250 1.3750 0.08783 0.08253 -0.0149 0.0156 1.0000
18.500 1.3688 0.09204 0.08685 -0.0159 0.0153 1.0000
18.750 1.3620 0.09640 0.09132 -0.0171 0.0150 1.0000
19.000 1.3545 0.10091 0.09592 -0.0184 0.0147 1.0000
19.250 1.3463 0.10555 0.10066 -0.0198 0.0145 1.0000
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Polar data table (+)
Polar graphs
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