MRC-16 (mrc-16-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MRC-16 (mrc-16-il) Reynolds number: 100,000 Max Cl/Cd: 52.53 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mrc-16-il-100000-n5.txt Download as CSV file: xf-mrc-16-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MRC-16
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4262 0.08345 0.07850 -0.0593 1.0000 0.0319
-10.000 -0.4421 0.07773 0.07285 -0.0614 1.0000 0.0317
-9.750 -0.4651 0.07268 0.06786 -0.0630 1.0000 0.0314
-9.500 -0.4938 0.06958 0.06481 -0.0618 1.0000 0.0312
-9.250 -0.5256 0.06786 0.06313 -0.0579 1.0000 0.0309
-9.000 -0.5395 0.06079 0.05576 -0.0629 0.9887 0.0308
-8.750 -0.5447 0.05435 0.04891 -0.0661 0.9786 0.0309
-8.500 -0.5408 0.04870 0.04273 -0.0682 0.9708 0.0310
-8.250 -0.5355 0.04421 0.03769 -0.0682 0.9615 0.0312
-8.000 -0.5190 0.03979 0.03258 -0.0692 0.9562 0.0317
-7.750 -0.5039 0.03712 0.02953 -0.0686 0.9480 0.0323
-7.500 -0.4760 0.03547 0.02775 -0.0700 0.9435 0.0337
-7.250 -0.4502 0.03381 0.02582 -0.0707 0.9382 0.0355
-7.000 -0.4276 0.03181 0.02342 -0.0704 0.9313 0.0372
-6.750 -0.3975 0.02968 0.02080 -0.0712 0.9272 0.0386
-6.500 -0.3728 0.02818 0.01919 -0.0711 0.9208 0.0400
-6.250 -0.3453 0.02718 0.01810 -0.0715 0.9148 0.0425
-6.000 -0.3126 0.02598 0.01666 -0.0726 0.9109 0.0458
-5.750 -0.2892 0.02488 0.01545 -0.0719 0.9034 0.0481
-5.250 -0.2281 0.02308 0.01348 -0.0732 0.8940 0.0567
-5.000 -0.2085 0.02232 0.01278 -0.0718 0.8850 0.0607
-4.750 -0.1785 0.02160 0.01195 -0.0723 0.8801 0.0680
-4.500 -0.1567 0.02096 0.01134 -0.0713 0.8722 0.0754
-4.250 -0.1300 0.02029 0.01066 -0.0711 0.8661 0.0869
-4.000 -0.1046 0.01968 0.01007 -0.0707 0.8596 0.1034
-3.750 -0.0810 0.01908 0.00957 -0.0700 0.8520 0.1294
-3.500 -0.0529 0.01827 0.00902 -0.0702 0.8473 0.1861
-3.250 -0.0347 0.01761 0.00878 -0.0688 0.8379 0.2774
-3.000 -0.0104 0.01675 0.00845 -0.0682 0.8326 0.4114
-2.750 0.0080 0.01625 0.00842 -0.0662 0.8238 0.5291
-2.500 0.0334 0.01582 0.00835 -0.0650 0.8180 0.6398
-2.250 0.0573 0.01570 0.00843 -0.0633 0.8103 0.7212
-2.000 0.0858 0.01564 0.00843 -0.0624 0.8039 0.7848
-1.750 0.1163 0.01568 0.00846 -0.0618 0.7974 0.8335
-1.500 0.1480 0.01578 0.00848 -0.0617 0.7899 0.8707
-1.250 0.1871 0.01579 0.00835 -0.0631 0.7847 0.8973
-1.000 0.2214 0.01590 0.00836 -0.0641 0.7758 0.9186
-0.750 0.2634 0.01585 0.00814 -0.0665 0.7700 0.9343
-0.500 0.3029 0.01591 0.00810 -0.0688 0.7609 0.9481
-0.250 0.3472 0.01581 0.00785 -0.0720 0.7545 0.9590
0.000 0.3867 0.01583 0.00778 -0.0746 0.7450 0.9706
0.250 0.4307 0.01571 0.00752 -0.0779 0.7378 0.9794
0.500 0.4715 0.01568 0.00742 -0.0809 0.7279 0.9887
0.750 0.5131 0.01560 0.00725 -0.0840 0.7193 0.9971
1.000 0.5416 0.01557 0.00714 -0.0844 0.7100 1.0000
1.250 0.5616 0.01562 0.00714 -0.0832 0.7001 1.0000
1.500 0.5844 0.01560 0.00703 -0.0823 0.6918 1.0000
1.750 0.6035 0.01571 0.00711 -0.0809 0.6811 1.0000
2.000 0.6246 0.01577 0.00712 -0.0797 0.6717 1.0000
2.250 0.6464 0.01583 0.00711 -0.0786 0.6625 1.0000
2.500 0.6661 0.01597 0.00723 -0.0773 0.6521 1.0000
2.750 0.6881 0.01605 0.00725 -0.0762 0.6429 1.0000
3.000 0.7089 0.01618 0.00735 -0.0749 0.6327 1.0000
3.250 0.7293 0.01633 0.00749 -0.0736 0.6224 1.0000
3.500 0.7518 0.01645 0.00755 -0.0726 0.6130 1.0000
3.750 0.7720 0.01662 0.00772 -0.0712 0.6022 1.0000
4.000 0.7926 0.01680 0.00789 -0.0699 0.5916 1.0000
4.250 0.8147 0.01696 0.00801 -0.0688 0.5816 1.0000
4.500 0.8352 0.01716 0.00821 -0.0675 0.5706 1.0000
4.750 0.8555 0.01738 0.00844 -0.0661 0.5594 1.0000
5.000 0.8771 0.01758 0.00864 -0.0650 0.5488 1.0000
5.250 0.8988 0.01779 0.00883 -0.0638 0.5380 1.0000
5.500 0.9186 0.01806 0.00913 -0.0624 0.5261 1.0000
5.750 0.9394 0.01832 0.00940 -0.0612 0.5146 1.0000
6.000 0.9607 0.01858 0.00967 -0.0601 0.5033 1.0000
6.250 0.9816 0.01885 0.00994 -0.0589 0.4916 1.0000
6.500 1.0012 0.01917 0.01030 -0.0575 0.4790 1.0000
6.750 1.0209 0.01949 0.01068 -0.0562 0.4666 1.0000
7.000 1.0407 0.01983 0.01103 -0.0548 0.4541 1.0000
7.250 1.0601 0.02018 0.01140 -0.0535 0.4414 1.0000
7.500 1.0791 0.02056 0.01178 -0.0521 0.4287 1.0000
7.750 1.0970 0.02096 0.01224 -0.0505 0.4152 1.0000
8.000 1.1141 0.02140 0.01273 -0.0489 0.4014 1.0000
8.250 1.1306 0.02187 0.01323 -0.0471 0.3875 1.0000
8.500 1.1462 0.02236 0.01376 -0.0453 0.3735 1.0000
8.750 1.1609 0.02289 0.01434 -0.0434 0.3594 1.0000
9.000 1.1738 0.02345 0.01494 -0.0412 0.3452 1.0000
9.250 1.1852 0.02407 0.01558 -0.0388 0.3310 1.0000
9.500 1.1958 0.02475 0.01629 -0.0365 0.3166 1.0000
9.750 1.2058 0.02550 0.01708 -0.0342 0.3020 1.0000
10.000 1.2149 0.02635 0.01795 -0.0319 0.2873 1.0000
10.250 1.2231 0.02728 0.01891 -0.0296 0.2725 1.0000
10.500 1.2304 0.02831 0.01997 -0.0274 0.2576 1.0000
10.750 1.2367 0.02946 0.02114 -0.0253 0.2427 1.0000
11.000 1.2421 0.03073 0.02244 -0.0232 0.2279 1.0000
11.250 1.2465 0.03214 0.02388 -0.0213 0.2132 1.0000
11.500 1.2500 0.03369 0.02545 -0.0194 0.1988 1.0000
11.750 1.2526 0.03539 0.02717 -0.0177 0.1846 1.0000
12.000 1.2542 0.03724 0.02905 -0.0161 0.1708 1.0000
12.250 1.2548 0.03928 0.03111 -0.0147 0.1577 1.0000
12.500 1.2543 0.04150 0.03336 -0.0134 0.1451 1.0000
12.750 1.2526 0.04393 0.03580 -0.0123 0.1334 1.0000
13.000 1.2502 0.04654 0.03845 -0.0114 0.1222 1.0000
13.250 1.2479 0.04923 0.04121 -0.0106 0.1115 1.0000
13.500 1.2445 0.05215 0.04418 -0.0100 0.1020 1.0000
13.750 1.2391 0.05540 0.04746 -0.0096 0.0939 1.0000
14.000 1.2342 0.05874 0.05086 -0.0095 0.0862 1.0000
14.250 1.2290 0.06223 0.05443 -0.0094 0.0794 1.0000
14.500 1.2217 0.06610 0.05834 -0.0097 0.0737 1.0000
14.750 1.2162 0.06985 0.06219 -0.0100 0.0684 1.0000
15.000 1.2087 0.07397 0.06639 -0.0106 0.0639 1.0000
15.250 1.2010 0.07821 0.07069 -0.0113 0.0601 1.0000
15.500 1.1952 0.08233 0.07493 -0.0121 0.0560 1.0000
15.750 1.1866 0.08690 0.07956 -0.0132 0.0531 1.0000
16.000 1.1799 0.09123 0.08399 -0.0142 0.0504 1.0000
16.250 1.1748 0.09548 0.08837 -0.0153 0.0474 1.0000
16.500 1.1681 0.10001 0.09299 -0.0167 0.0451 1.0000
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Polar data table (+)
Polar graphs
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