MRC-16 (mrc-16-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MRC-16 (mrc-16-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.31 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mrc-16-il-1000000-n5.txt Download as CSV file: xf-mrc-16-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.9601 0.05714 0.05446 -0.0703 1.0000 0.0073
-15.500 -0.9949 0.04632 0.04339 -0.0794 1.0000 0.0073
-15.250 -1.0103 0.04045 0.03733 -0.0838 1.0000 0.0073
-15.000 -1.0184 0.03654 0.03327 -0.0859 1.0000 0.0073
-14.750 -1.0224 0.03366 0.03026 -0.0866 1.0000 0.0074
-14.500 -1.0239 0.03144 0.02792 -0.0862 1.0000 0.0075
-14.250 -1.0240 0.02966 0.02603 -0.0849 1.0000 0.0075
-14.000 -1.0251 0.02824 0.02450 -0.0826 1.0000 0.0076
-13.750 -1.0147 0.02685 0.02300 -0.0820 0.9950 0.0077
-13.500 -0.9979 0.02553 0.02156 -0.0821 0.9870 0.0078
-13.250 -0.9789 0.02435 0.02025 -0.0823 0.9799 0.0079
-13.000 -0.9592 0.02327 0.01905 -0.0823 0.9720 0.0080
-12.750 -0.9406 0.02231 0.01798 -0.0817 0.9633 0.0081
-12.500 -0.9217 0.02146 0.01701 -0.0811 0.9549 0.0082
-12.250 -0.9034 0.02068 0.01612 -0.0801 0.9458 0.0083
-12.000 -0.8841 0.01996 0.01528 -0.0792 0.9377 0.0084
-11.750 -0.8642 0.01930 0.01452 -0.0783 0.9293 0.0085
-11.500 -0.8449 0.01851 0.01361 -0.0774 0.9216 0.0086
-11.250 -0.8251 0.01775 0.01275 -0.0765 0.9137 0.0089
-11.000 -0.8034 0.01714 0.01206 -0.0758 0.9069 0.0091
-10.750 -0.7808 0.01661 0.01145 -0.0752 0.8996 0.0093
-10.500 -0.7577 0.01613 0.01089 -0.0747 0.8930 0.0095
-10.250 -0.7340 0.01567 0.01036 -0.0742 0.8862 0.0097
-10.000 -0.7101 0.01525 0.00986 -0.0738 0.8794 0.0099
-9.750 -0.6856 0.01484 0.00938 -0.0734 0.8731 0.0102
-9.500 -0.6610 0.01444 0.00891 -0.0730 0.8661 0.0105
-9.250 -0.6362 0.01406 0.00845 -0.0727 0.8599 0.0108
-9.000 -0.6112 0.01369 0.00800 -0.0723 0.8529 0.0110
-8.750 -0.5866 0.01327 0.00751 -0.0719 0.8464 0.0112
-8.500 -0.5617 0.01284 0.00702 -0.0715 0.8394 0.0116
-8.250 -0.5364 0.01251 0.00663 -0.0712 0.8325 0.0120
-8.000 -0.5105 0.01220 0.00628 -0.0710 0.8257 0.0124
-7.750 -0.4846 0.01191 0.00594 -0.0707 0.8186 0.0129
-7.500 -0.4585 0.01164 0.00561 -0.0705 0.8119 0.0133
-7.250 -0.4323 0.01139 0.00529 -0.0703 0.8045 0.0137
-7.000 -0.4061 0.01113 0.00498 -0.0701 0.7975 0.0142
-6.750 -0.3801 0.01084 0.00466 -0.0698 0.7897 0.0150
-6.500 -0.3536 0.01063 0.00441 -0.0696 0.7827 0.0158
-6.250 -0.3269 0.01043 0.00417 -0.0695 0.7749 0.0167
-6.000 -0.3003 0.01025 0.00393 -0.0693 0.7677 0.0174
-5.750 -0.2738 0.01002 0.00367 -0.0691 0.7597 0.0186
-5.500 -0.2471 0.00984 0.00346 -0.0689 0.7522 0.0198
-5.250 -0.2201 0.00968 0.00326 -0.0688 0.7441 0.0211
-5.000 -0.1934 0.00951 0.00306 -0.0686 0.7366 0.0228
-4.750 -0.1664 0.00936 0.00289 -0.0685 0.7282 0.0251
-4.500 -0.1395 0.00922 0.00272 -0.0683 0.7205 0.0274
-4.250 -0.1125 0.00908 0.00257 -0.0682 0.7121 0.0305
-4.000 -0.0856 0.00896 0.00242 -0.0681 0.7044 0.0340
-3.750 -0.0585 0.00884 0.00229 -0.0680 0.6958 0.0387
-3.500 -0.0316 0.00871 0.00216 -0.0678 0.6880 0.0456
-3.250 -0.0047 0.00860 0.00205 -0.0677 0.6793 0.0536
-3.000 0.0223 0.00847 0.00194 -0.0676 0.6713 0.0648
-2.750 0.0491 0.00836 0.00184 -0.0674 0.6626 0.0786
-2.500 0.0759 0.00822 0.00175 -0.0673 0.6545 0.0981
-2.250 0.1022 0.00808 0.00166 -0.0671 0.6458 0.1264
-2.000 0.1286 0.00789 0.00157 -0.0669 0.6374 0.1649
-1.750 0.1544 0.00771 0.00150 -0.0666 0.6289 0.2111
-1.500 0.1801 0.00747 0.00144 -0.0664 0.6200 0.2704
-1.250 0.2058 0.00728 0.00139 -0.0661 0.6116 0.3293
-1.000 0.2313 0.00707 0.00135 -0.0658 0.6025 0.3938
-0.750 0.2569 0.00689 0.00132 -0.0654 0.5941 0.4556
-0.500 0.2822 0.00672 0.00131 -0.0651 0.5848 0.5185
-0.250 0.3075 0.00653 0.00131 -0.0646 0.5762 0.5864
0.000 0.3323 0.00640 0.00132 -0.0641 0.5672 0.6502
0.250 0.3579 0.00630 0.00135 -0.0637 0.5580 0.7000
0.500 0.3837 0.00626 0.00139 -0.0632 0.5490 0.7382
0.750 0.4099 0.00626 0.00143 -0.0629 0.5393 0.7681
1.250 0.4625 0.00630 0.00153 -0.0623 0.5202 0.8165
1.500 0.4891 0.00634 0.00159 -0.0620 0.5101 0.8371
1.750 0.5155 0.00639 0.00165 -0.0617 0.5002 0.8558
2.000 0.5418 0.00647 0.00173 -0.0614 0.4901 0.8731
2.250 0.5683 0.00654 0.00180 -0.0611 0.4797 0.8891
2.500 0.5946 0.00663 0.00188 -0.0608 0.4699 0.9036
2.750 0.6209 0.00674 0.00198 -0.0605 0.4594 0.9168
3.000 0.6476 0.00684 0.00207 -0.0603 0.4489 0.9289
3.250 0.6744 0.00696 0.00217 -0.0602 0.4385 0.9407
3.500 0.7018 0.00711 0.00228 -0.0602 0.4277 0.9515
3.750 0.7310 0.00726 0.00240 -0.0606 0.4164 0.9603
4.000 0.7594 0.00741 0.00251 -0.0609 0.4051 0.9689
4.250 0.7910 0.00759 0.00265 -0.0619 0.3932 0.9740
4.500 0.8211 0.00778 0.00279 -0.0626 0.3809 0.9797
4.750 0.8515 0.00798 0.00293 -0.0634 0.3681 0.9843
5.000 0.8835 0.00818 0.00309 -0.0646 0.3552 0.9876
5.250 0.9147 0.00839 0.00325 -0.0657 0.3419 0.9910
5.500 0.9452 0.00862 0.00343 -0.0665 0.3281 0.9942
5.750 0.9771 0.00887 0.00362 -0.0678 0.3139 0.9964
6.000 1.0082 0.00914 0.00383 -0.0689 0.2989 0.9989
6.250 1.0324 0.00939 0.00403 -0.0685 0.2848 1.0000
6.500 1.0507 0.00964 0.00422 -0.0668 0.2718 1.0000
6.750 1.0689 0.00991 0.00443 -0.0651 0.2580 1.0000
7.000 1.0874 0.01019 0.00466 -0.0634 0.2439 1.0000
7.250 1.1064 0.01051 0.00491 -0.0619 0.2292 1.0000
7.500 1.1256 0.01084 0.00519 -0.0606 0.2146 1.0000
7.750 1.1447 0.01121 0.00548 -0.0592 0.1989 1.0000
8.000 1.1634 0.01161 0.00581 -0.0578 0.1826 1.0000
8.250 1.1813 0.01205 0.00617 -0.0563 0.1656 1.0000
8.500 1.1975 0.01253 0.00656 -0.0545 0.1493 1.0000
8.750 1.2131 0.01301 0.00697 -0.0525 0.1339 1.0000
9.000 1.2287 0.01352 0.00741 -0.0507 0.1195 1.0000
9.250 1.2439 0.01408 0.00790 -0.0489 0.1053 1.0000
9.500 1.2588 0.01467 0.00843 -0.0472 0.0921 1.0000
9.750 1.2735 0.01530 0.00900 -0.0454 0.0802 1.0000
10.000 1.2877 0.01596 0.00961 -0.0437 0.0695 1.0000
10.250 1.3016 0.01666 0.01028 -0.0420 0.0600 1.0000
10.500 1.3148 0.01742 0.01100 -0.0403 0.0512 1.0000
10.750 1.3280 0.01820 0.01176 -0.0387 0.0439 1.0000
11.000 1.3418 0.01897 0.01252 -0.0372 0.0383 1.0000
11.250 1.3548 0.01981 0.01335 -0.0358 0.0335 1.0000
11.500 1.3666 0.02074 0.01427 -0.0342 0.0288 1.0000
11.750 1.3789 0.02167 0.01522 -0.0328 0.0252 1.0000
12.000 1.3908 0.02265 0.01621 -0.0315 0.0222 1.0000
12.250 1.4017 0.02373 0.01731 -0.0301 0.0196 1.0000
12.500 1.4133 0.02478 0.01840 -0.0289 0.0178 1.0000
12.750 1.4237 0.02596 0.01960 -0.0277 0.0161 1.0000
13.000 1.4337 0.02718 0.02087 -0.0265 0.0148 1.0000
13.250 1.4436 0.02845 0.02217 -0.0254 0.0136 1.0000
13.500 1.4520 0.02987 0.02364 -0.0243 0.0125 1.0000
13.750 1.4603 0.03133 0.02514 -0.0233 0.0117 1.0000
14.000 1.4683 0.03285 0.02672 -0.0224 0.0109 1.0000
14.250 1.4748 0.03453 0.02845 -0.0215 0.0102 1.0000
14.500 1.4800 0.03639 0.03036 -0.0206 0.0095 1.0000
14.750 1.4863 0.03819 0.03223 -0.0199 0.0091 1.0000
15.000 1.4917 0.04013 0.03424 -0.0192 0.0086 1.0000
15.250 1.4960 0.04224 0.03641 -0.0187 0.0082 1.0000
15.500 1.4992 0.04451 0.03874 -0.0182 0.0078 1.0000
15.750 1.5011 0.04697 0.04126 -0.0178 0.0075 1.0000
16.000 1.5023 0.04957 0.04394 -0.0175 0.0072 1.0000
16.250 1.5043 0.05214 0.04659 -0.0173 0.0070 1.0000
16.500 1.5055 0.05488 0.04941 -0.0173 0.0068 1.0000
16.750 1.5055 0.05778 0.05240 -0.0173 0.0066 1.0000
17.000 1.5044 0.06087 0.05557 -0.0175 0.0064 1.0000
17.250 1.5024 0.06414 0.05893 -0.0177 0.0063 1.0000
17.500 1.4993 0.06761 0.06247 -0.0181 0.0061 1.0000
17.750 1.4952 0.07126 0.06622 -0.0186 0.0059 1.0000
18.000 1.4897 0.07514 0.07018 -0.0192 0.0058 1.0000
18.250 1.4831 0.07924 0.07437 -0.0200 0.0057 1.0000
18.500 1.4751 0.08362 0.07885 -0.0209 0.0055 1.0000
18.750 1.4660 0.08822 0.08354 -0.0220 0.0054 1.0000
19.000 1.4583 0.09263 0.08805 -0.0232 0.0053 1.0000
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