MRC-16 (mrc-16-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MRC-16 (mrc-16-il) Reynolds number: 500,000 Max Cl/Cd: 94.37 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mrc-16-il-500000-n5.txt Download as CSV file: xf-mrc-16-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7506 0.05649 0.05356 -0.0724 1.0000 0.0101
-13.250 -0.7835 0.04635 0.04315 -0.0815 1.0000 0.0100
-13.000 -0.8035 0.04099 0.03756 -0.0846 1.0000 0.0100
-12.750 -0.8196 0.03752 0.03391 -0.0845 1.0000 0.0101
-12.500 -0.8373 0.03534 0.03159 -0.0813 0.9998 0.0101
-12.250 -0.8306 0.03251 0.02849 -0.0826 0.9916 0.0103
-12.000 -0.8190 0.03019 0.02590 -0.0832 0.9836 0.0105
-11.750 -0.8048 0.02826 0.02373 -0.0832 0.9754 0.0107
-11.500 -0.7861 0.02658 0.02181 -0.0836 0.9694 0.0109
-11.250 -0.7682 0.02527 0.02030 -0.0832 0.9614 0.0110
-11.000 -0.7498 0.02387 0.01875 -0.0830 0.9546 0.0113
-10.750 -0.7307 0.02296 0.01774 -0.0823 0.9464 0.0116
-10.500 -0.7093 0.02219 0.01689 -0.0819 0.9398 0.0118
-10.250 -0.6890 0.02147 0.01607 -0.0811 0.9318 0.0121
-10.000 -0.6678 0.02072 0.01519 -0.0804 0.9252 0.0124
-9.750 -0.6472 0.01994 0.01429 -0.0796 0.9174 0.0128
-9.500 -0.6259 0.01917 0.01337 -0.0788 0.9107 0.0131
-9.250 -0.6042 0.01844 0.01252 -0.0781 0.9035 0.0134
-9.000 -0.5818 0.01778 0.01171 -0.0773 0.8966 0.0138
-8.750 -0.5590 0.01715 0.01097 -0.0767 0.8900 0.0140
-8.500 -0.5369 0.01644 0.01018 -0.0760 0.8828 0.0145
-8.250 -0.5132 0.01593 0.00960 -0.0755 0.8766 0.0149
-8.000 -0.4891 0.01548 0.00908 -0.0750 0.8694 0.0154
-7.500 -0.4398 0.01464 0.00808 -0.0741 0.8559 0.0168
-7.250 -0.4148 0.01427 0.00760 -0.0737 0.8491 0.0174
-7.000 -0.3906 0.01376 0.00706 -0.0732 0.8423 0.0182
-6.750 -0.3654 0.01340 0.00665 -0.0728 0.8352 0.0190
-6.500 -0.3400 0.01306 0.00625 -0.0724 0.8285 0.0200
-6.250 -0.3144 0.01274 0.00585 -0.0721 0.8212 0.0209
-6.000 -0.2890 0.01240 0.00545 -0.0717 0.8144 0.0221
-5.750 -0.2632 0.01211 0.00513 -0.0714 0.8067 0.0237
-5.500 -0.2371 0.01187 0.00482 -0.0711 0.7998 0.0254
-5.250 -0.2112 0.01159 0.00450 -0.0708 0.7921 0.0272
-5.000 -0.1852 0.01135 0.00422 -0.0705 0.7850 0.0296
-4.750 -0.1587 0.01115 0.00398 -0.0702 0.7771 0.0321
-4.250 -0.1061 0.01072 0.00350 -0.0697 0.7617 0.0405
-3.750 -0.0534 0.01035 0.00310 -0.0692 0.7460 0.0545
-3.500 -0.0271 0.01018 0.00292 -0.0690 0.7383 0.0651
-3.250 -0.0006 0.00999 0.00277 -0.0688 0.7300 0.0796
-3.000 0.0253 0.00980 0.00261 -0.0685 0.7222 0.1008
-2.750 0.0512 0.00956 0.00247 -0.0682 0.7137 0.1328
-2.500 0.0766 0.00931 0.00234 -0.0679 0.7059 0.1771
-2.250 0.1018 0.00902 0.00221 -0.0675 0.6973 0.2358
-2.000 0.1264 0.00870 0.00211 -0.0671 0.6893 0.3075
-1.750 0.1509 0.00840 0.00202 -0.0666 0.6806 0.3822
-1.500 0.1753 0.00813 0.00196 -0.0661 0.6725 0.4569
-1.250 0.1994 0.00787 0.00191 -0.0654 0.6637 0.5290
-1.000 0.2236 0.00766 0.00189 -0.0647 0.6555 0.5981
-0.750 0.2476 0.00749 0.00189 -0.0639 0.6468 0.6628
-0.500 0.2719 0.00735 0.00191 -0.0631 0.6382 0.7201
-0.250 0.2967 0.00730 0.00194 -0.0624 0.6296 0.7639
0.000 0.3225 0.00727 0.00198 -0.0618 0.6205 0.7972
0.250 0.3483 0.00728 0.00202 -0.0613 0.6118 0.8241
0.500 0.3745 0.00731 0.00206 -0.0608 0.6026 0.8466
0.750 0.4009 0.00736 0.00211 -0.0604 0.5937 0.8665
1.000 0.4273 0.00743 0.00216 -0.0600 0.5844 0.8839
1.250 0.4543 0.00750 0.00222 -0.0598 0.5749 0.8993
1.500 0.4814 0.00759 0.00229 -0.0596 0.5657 0.9132
1.750 0.5090 0.00769 0.00235 -0.0595 0.5556 0.9257
2.000 0.5374 0.00780 0.00243 -0.0596 0.5459 0.9370
2.250 0.5674 0.00793 0.00251 -0.0601 0.5357 0.9460
2.500 0.5965 0.00806 0.00259 -0.0604 0.5250 0.9555
2.750 0.6294 0.00819 0.00269 -0.0616 0.5144 0.9622
3.000 0.6592 0.00834 0.00279 -0.0622 0.5038 0.9702
3.250 0.6932 0.00850 0.00290 -0.0637 0.4924 0.9748
3.500 0.7250 0.00864 0.00301 -0.0647 0.4814 0.9804
3.750 0.7581 0.00881 0.00313 -0.0661 0.4699 0.9844
4.000 0.7921 0.00899 0.00326 -0.0677 0.4582 0.9878
4.250 0.8246 0.00917 0.00340 -0.0690 0.4460 0.9918
4.500 0.8574 0.00935 0.00355 -0.0703 0.4336 0.9951
4.750 0.8907 0.00954 0.00371 -0.0718 0.4210 0.9981
5.000 0.9184 0.00974 0.00387 -0.0721 0.4085 1.0000
5.250 0.9371 0.00994 0.00402 -0.0705 0.3972 1.0000
5.500 0.9560 0.01013 0.00418 -0.0689 0.3852 1.0000
5.750 0.9752 0.01034 0.00436 -0.0673 0.3733 1.0000
6.000 0.9942 0.01056 0.00455 -0.0657 0.3613 1.0000
6.250 1.0129 0.01081 0.00476 -0.0641 0.3487 1.0000
6.500 1.0318 0.01107 0.00499 -0.0626 0.3359 1.0000
6.750 1.0508 0.01136 0.00523 -0.0611 0.3223 1.0000
7.000 1.0702 0.01166 0.00549 -0.0597 0.3084 1.0000
7.250 1.0896 0.01198 0.00577 -0.0583 0.2942 1.0000
7.500 1.1086 0.01233 0.00608 -0.0569 0.2794 1.0000
7.750 1.1272 0.01271 0.00641 -0.0555 0.2643 1.0000
8.000 1.1450 0.01313 0.00677 -0.0540 0.2488 1.0000
8.500 1.1772 0.01402 0.00756 -0.0504 0.2177 1.0000
8.750 1.1928 0.01454 0.00802 -0.0486 0.2015 1.0000
9.000 1.2079 0.01510 0.00852 -0.0468 0.1851 1.0000
9.250 1.2224 0.01572 0.00908 -0.0450 0.1686 1.0000
9.500 1.2363 0.01639 0.00969 -0.0432 0.1526 1.0000
9.750 1.2496 0.01713 0.01036 -0.0414 0.1371 1.0000
10.000 1.2622 0.01792 0.01109 -0.0396 0.1225 1.0000
10.500 1.2858 0.01967 0.01274 -0.0361 0.0958 1.0000
10.750 1.2968 0.02064 0.01368 -0.0344 0.0838 1.0000
11.000 1.3074 0.02166 0.01467 -0.0327 0.0731 1.0000
11.250 1.3177 0.02273 0.01573 -0.0311 0.0637 1.0000
11.500 1.3276 0.02387 0.01685 -0.0296 0.0556 1.0000
11.750 1.3368 0.02508 0.01806 -0.0281 0.0486 1.0000
12.000 1.3450 0.02641 0.01940 -0.0267 0.0424 1.0000
12.250 1.3534 0.02776 0.02077 -0.0253 0.0371 1.0000
12.500 1.3614 0.02918 0.02221 -0.0241 0.0329 1.0000
12.750 1.3679 0.03076 0.02382 -0.0228 0.0292 1.0000
13.000 1.3758 0.03228 0.02538 -0.0218 0.0264 1.0000
13.250 1.3809 0.03406 0.02720 -0.0207 0.0238 1.0000
13.500 1.3874 0.03577 0.02899 -0.0198 0.0217 1.0000
13.750 1.3919 0.03771 0.03098 -0.0189 0.0198 1.0000
14.000 1.3961 0.03973 0.03306 -0.0181 0.0183 1.0000
14.250 1.4003 0.04182 0.03522 -0.0174 0.0170 1.0000
14.500 1.4028 0.04414 0.03760 -0.0169 0.0158 1.0000
14.750 1.4048 0.04658 0.04012 -0.0164 0.0150 1.0000
15.000 1.4074 0.04902 0.04265 -0.0161 0.0142 1.0000
15.250 1.4086 0.05167 0.04539 -0.0158 0.0135 1.0000
15.500 1.4085 0.05455 0.04835 -0.0157 0.0128 1.0000
15.750 1.4067 0.05768 0.05157 -0.0157 0.0123 1.0000
16.000 1.4050 0.06088 0.05487 -0.0159 0.0119 1.0000
16.250 1.4036 0.06411 0.05821 -0.0161 0.0115 1.0000
16.500 1.4012 0.06754 0.06174 -0.0165 0.0111 1.0000
16.750 1.3979 0.07115 0.06545 -0.0170 0.0107 1.0000
17.000 1.3932 0.07497 0.06937 -0.0177 0.0103 1.0000
17.250 1.3875 0.07904 0.07353 -0.0185 0.0100 1.0000
17.500 1.3803 0.08338 0.07797 -0.0194 0.0098 1.0000
17.750 1.3714 0.08804 0.08273 -0.0206 0.0095 1.0000
18.000 1.3639 0.09254 0.08733 -0.0218 0.0093 1.0000
18.250 1.3571 0.09702 0.09193 -0.0231 0.0091 1.0000
18.500 1.3496 0.10167 0.09669 -0.0245 0.0089 1.0000
18.750 1.3416 0.10645 0.10159 -0.0261 0.0087 1.0000
19.000 1.3333 0.11131 0.10656 -0.0278 0.0085 1.0000
19.250 1.3247 0.11629 0.11164 -0.0296 0.0084 1.0000
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Polar data table (+)
Polar graphs
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