MRC-16 (mrc-16-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MRC-16 (mrc-16-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.12 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mrc-16-il-1000000.txt Download as CSV file: xf-mrc-16-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6052 0.09237 0.09059 -0.0484 1.0000 0.0114
-13.500 -0.7693 0.05125 0.04891 -0.0771 1.0000 0.0107
-13.250 -0.7949 0.04343 0.04086 -0.0838 1.0000 0.0107
-13.000 -0.8130 0.03870 0.03594 -0.0861 1.0000 0.0107
-12.750 -0.8294 0.03560 0.03267 -0.0852 1.0000 0.0107
-12.500 -0.8519 0.03397 0.03093 -0.0804 0.9996 0.0108
-12.250 -0.8408 0.03133 0.02806 -0.0820 0.9951 0.0109
-12.000 -0.8241 0.02925 0.02577 -0.0831 0.9905 0.0110
-11.750 -0.8023 0.02766 0.02400 -0.0843 0.9865 0.0110
-11.500 -0.7958 0.02392 0.01987 -0.0843 0.9798 0.0113
-11.250 -0.7785 0.02220 0.01799 -0.0840 0.9729 0.0115
-11.000 -0.7587 0.02119 0.01688 -0.0835 0.9658 0.0118
-10.750 -0.7387 0.02039 0.01600 -0.0826 0.9583 0.0120
-10.500 -0.7188 0.01969 0.01520 -0.0817 0.9507 0.0122
-10.250 -0.6986 0.01898 0.01439 -0.0807 0.9433 0.0125
-10.000 -0.6778 0.01828 0.01359 -0.0798 0.9361 0.0127
-9.750 -0.6565 0.01761 0.01280 -0.0790 0.9289 0.0131
-9.500 -0.6344 0.01696 0.01204 -0.0782 0.9222 0.0134
-9.250 -0.6115 0.01639 0.01137 -0.0775 0.9152 0.0137
-9.000 -0.5874 0.01599 0.01086 -0.0770 0.9090 0.0139
-8.750 -0.5675 0.01486 0.00961 -0.0760 0.9017 0.0145
-8.500 -0.5444 0.01428 0.00896 -0.0753 0.8952 0.0150
-8.250 -0.5197 0.01384 0.00848 -0.0749 0.8888 0.0154
-8.000 -0.4950 0.01344 0.00801 -0.0745 0.8821 0.0159
-7.750 -0.4700 0.01303 0.00754 -0.0741 0.8759 0.0164
-7.500 -0.4446 0.01265 0.00709 -0.0737 0.8691 0.0169
-7.250 -0.4189 0.01236 0.00671 -0.0733 0.8628 0.0174
-7.000 -0.3956 0.01166 0.00595 -0.0727 0.8558 0.0182
-6.750 -0.3702 0.01132 0.00556 -0.0723 0.8491 0.0190
-6.500 -0.3439 0.01104 0.00526 -0.0721 0.8425 0.0199
-6.250 -0.3174 0.01082 0.00498 -0.0719 0.8355 0.0209
-6.000 -0.2916 0.01049 0.00458 -0.0715 0.8289 0.0220
-5.750 -0.2659 0.01014 0.00422 -0.0712 0.8216 0.0236
-5.500 -0.2393 0.00994 0.00396 -0.0710 0.8149 0.0250
-5.250 -0.2122 0.00976 0.00375 -0.0708 0.8074 0.0263
-5.000 -0.1866 0.00944 0.00339 -0.0704 0.8005 0.0292
-4.750 -0.1594 0.00928 0.00321 -0.0703 0.7928 0.0317
-4.500 -0.1332 0.00904 0.00294 -0.0700 0.7856 0.0359
-4.250 -0.1061 0.00887 0.00275 -0.0699 0.7779 0.0401
-4.000 -0.0795 0.00869 0.00257 -0.0697 0.7704 0.0466
-3.750 -0.0527 0.00849 0.00240 -0.0695 0.7627 0.0563
-3.500 -0.0262 0.00832 0.00224 -0.0693 0.7550 0.0705
-3.250 0.0004 0.00811 0.00210 -0.0691 0.7470 0.0920
-3.000 0.0263 0.00790 0.00196 -0.0688 0.7391 0.1248
-2.750 0.0521 0.00760 0.00184 -0.0686 0.7311 0.1732
-2.500 0.0770 0.00730 0.00172 -0.0681 0.7231 0.2387
-2.250 0.1020 0.00695 0.00162 -0.0678 0.7149 0.3176
-2.000 0.1265 0.00665 0.00154 -0.0673 0.7069 0.3990
-1.750 0.1515 0.00636 0.00148 -0.0668 0.6985 0.4759
-1.500 0.1760 0.00611 0.00143 -0.0662 0.6904 0.5535
-1.250 0.2010 0.00591 0.00141 -0.0657 0.6818 0.6192
-1.000 0.2260 0.00576 0.00140 -0.0651 0.6736 0.6766
-0.750 0.2515 0.00566 0.00140 -0.0646 0.6649 0.7221
-0.500 0.2774 0.00561 0.00142 -0.0641 0.6566 0.7601
-0.250 0.3032 0.00558 0.00144 -0.0636 0.6477 0.7941
0.000 0.3293 0.00555 0.00147 -0.0632 0.6391 0.8249
0.500 0.3818 0.00557 0.00155 -0.0623 0.6213 0.8714
0.750 0.4081 0.00563 0.00159 -0.0619 0.6125 0.8892
1.000 0.4347 0.00567 0.00164 -0.0615 0.6030 0.9049
1.250 0.4612 0.00574 0.00169 -0.0612 0.5939 0.9187
1.750 0.5147 0.00590 0.00181 -0.0606 0.5746 0.9423
2.000 0.5413 0.00600 0.00188 -0.0602 0.5652 0.9531
2.250 0.5710 0.00611 0.00195 -0.0606 0.5550 0.9608
2.500 0.5986 0.00622 0.00203 -0.0606 0.5452 0.9697
2.750 0.6325 0.00636 0.00212 -0.0620 0.5349 0.9740
3.000 0.6656 0.00649 0.00221 -0.0633 0.5239 0.9789
3.250 0.6985 0.00662 0.00229 -0.0645 0.5132 0.9834
3.500 0.7361 0.00676 0.00239 -0.0668 0.5021 0.9852
3.750 0.7726 0.00692 0.00249 -0.0689 0.4903 0.9875
4.000 0.8080 0.00706 0.00260 -0.0708 0.4784 0.9903
4.250 0.8417 0.00721 0.00271 -0.0723 0.4663 0.9934
4.500 0.8773 0.00736 0.00281 -0.0742 0.4540 0.9952
4.750 0.9126 0.00752 0.00293 -0.0761 0.4413 0.9971
5.000 0.9473 0.00770 0.00306 -0.0779 0.4278 0.9990
5.250 0.9756 0.00788 0.00319 -0.0784 0.4148 1.0000
5.500 0.9954 0.00802 0.00331 -0.0769 0.4030 1.0000
5.750 1.0145 0.00819 0.00344 -0.0753 0.3909 1.0000
6.000 1.0333 0.00838 0.00359 -0.0737 0.3786 1.0000
6.250 1.0518 0.00858 0.00375 -0.0720 0.3658 1.0000
6.500 1.0703 0.00881 0.00392 -0.0703 0.3523 1.0000
6.750 1.0891 0.00904 0.00411 -0.0686 0.3385 1.0000
7.000 1.1080 0.00928 0.00430 -0.0670 0.3243 1.0000
7.250 1.1269 0.00955 0.00452 -0.0655 0.3094 1.0000
7.500 1.1461 0.00984 0.00476 -0.0640 0.2940 1.0000
7.750 1.1653 0.01017 0.00502 -0.0626 0.2775 1.0000
8.000 1.1848 0.01051 0.00529 -0.0613 0.2607 1.0000
8.250 1.2040 0.01089 0.00560 -0.0599 0.2431 1.0000
8.500 1.2227 0.01130 0.00593 -0.0585 0.2255 1.0000
8.750 1.2405 0.01174 0.00629 -0.0570 0.2082 1.0000
9.000 1.2565 0.01220 0.00668 -0.0551 0.1915 1.0000
9.250 1.2721 0.01269 0.00710 -0.0533 0.1753 1.0000
9.500 1.2877 0.01321 0.00755 -0.0515 0.1592 1.0000
9.750 1.3028 0.01377 0.00804 -0.0497 0.1437 1.0000
10.000 1.3172 0.01439 0.00859 -0.0478 0.1285 1.0000
10.250 1.3307 0.01507 0.00920 -0.0460 0.1136 1.0000
10.500 1.3434 0.01582 0.00988 -0.0441 0.0995 1.0000
10.750 1.3557 0.01660 0.01060 -0.0422 0.0869 1.0000
11.000 1.3678 0.01743 0.01138 -0.0404 0.0755 1.0000
11.250 1.3793 0.01831 0.01222 -0.0386 0.0652 1.0000
11.500 1.3901 0.01927 0.01315 -0.0368 0.0558 1.0000
11.750 1.4003 0.02029 0.01414 -0.0351 0.0475 1.0000
12.000 1.4101 0.02137 0.01520 -0.0334 0.0406 1.0000
12.250 1.4190 0.02254 0.01636 -0.0317 0.0347 1.0000
12.500 1.4277 0.02377 0.01758 -0.0301 0.0300 1.0000
12.750 1.4372 0.02499 0.01882 -0.0288 0.0264 1.0000
13.000 1.4445 0.02639 0.02024 -0.0273 0.0231 1.0000
13.250 1.4527 0.02777 0.02165 -0.0260 0.0208 1.0000
13.500 1.4587 0.02937 0.02328 -0.0247 0.0187 1.0000
13.750 1.4665 0.03086 0.02483 -0.0236 0.0172 1.0000
14.000 1.4704 0.03271 0.02671 -0.0224 0.0157 1.0000
14.250 1.4761 0.03447 0.02854 -0.0214 0.0147 1.0000
14.500 1.4821 0.03626 0.03039 -0.0205 0.0138 1.0000
14.750 1.4853 0.03835 0.03253 -0.0197 0.0130 1.0000
15.000 1.4836 0.04101 0.03526 -0.0188 0.0121 1.0000
15.250 1.4884 0.04309 0.03743 -0.0183 0.0117 1.0000
15.500 1.4916 0.04540 0.03982 -0.0178 0.0112 1.0000
15.750 1.4934 0.04790 0.04239 -0.0175 0.0108 1.0000
16.000 1.4935 0.05066 0.04522 -0.0172 0.0104 1.0000
16.250 1.4910 0.05378 0.04842 -0.0171 0.0100 1.0000
16.500 1.4844 0.05748 0.05221 -0.0171 0.0096 1.0000
16.750 1.4775 0.06131 0.05614 -0.0172 0.0094 1.0000
17.000 1.4762 0.06453 0.05945 -0.0175 0.0092 1.0000
17.250 1.4731 0.06804 0.06306 -0.0179 0.0090 1.0000
17.500 1.4687 0.07177 0.06690 -0.0185 0.0088 1.0000
17.750 1.4630 0.07571 0.07093 -0.0191 0.0087 1.0000
18.000 1.4564 0.07985 0.07517 -0.0199 0.0085 1.0000
18.250 1.4491 0.08417 0.07958 -0.0209 0.0083 1.0000
18.500 1.4410 0.08866 0.08417 -0.0219 0.0082 1.0000
18.750 1.4316 0.09339 0.08899 -0.0232 0.0080 1.0000
19.000 1.4210 0.09836 0.09406 -0.0246 0.0079 1.0000
19.250 1.4093 0.10362 0.09942 -0.0263 0.0078 1.0000
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Polar data table (+)
Polar graphs
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