MRC-16 (mrc-16-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MRC-16 (mrc-16-il) Reynolds number: 200,000 Max Cl/Cd: 73.07 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mrc-16-il-200000.txt Download as CSV file: xf-mrc-16-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4010 0.09037 0.08716 -0.0446 1.0000 0.0636
-9.000 -0.4242 0.08834 0.08522 -0.0421 1.0000 0.0642
-8.750 -0.4449 0.08464 0.08159 -0.0434 0.9986 0.0653
-8.500 -0.4870 0.07125 0.06766 -0.0666 0.9810 0.0682
-8.250 -0.4808 0.06364 0.06003 -0.0695 0.9753 0.0695
-8.000 -0.4533 0.06040 0.05687 -0.0715 0.9726 0.0710
-7.750 -0.4335 0.05714 0.05354 -0.0737 0.9676 0.0732
-7.500 -0.4553 0.04000 0.03490 -0.0748 0.9568 0.0449
-7.250 -0.4437 0.03598 0.03045 -0.0737 0.9483 0.0435
-7.000 -0.4175 0.03235 0.02631 -0.0747 0.9441 0.0437
-6.750 -0.3846 0.02888 0.02230 -0.0764 0.9417 0.0435
-6.500 -0.3638 0.02686 0.01992 -0.0753 0.9338 0.0440
-6.250 -0.3302 0.02493 0.01762 -0.0764 0.9300 0.0453
-6.000 -0.2937 0.02330 0.01567 -0.0781 0.9272 0.0479
-5.750 -0.2657 0.02195 0.01432 -0.0784 0.9215 0.0504
-5.500 -0.2361 0.02094 0.01322 -0.0787 0.9155 0.0531
-5.250 -0.2008 0.02011 0.01222 -0.0798 0.9120 0.0568
-5.000 -0.1753 0.01891 0.01111 -0.0795 0.9056 0.0619
-4.750 -0.1477 0.01823 0.01036 -0.0793 0.8992 0.0672
-4.500 -0.1174 0.01724 0.00943 -0.0797 0.8952 0.0758
-4.250 -0.0972 0.01664 0.00883 -0.0782 0.8863 0.0850
-4.000 -0.0698 0.01590 0.00815 -0.0780 0.8809 0.1017
-3.750 -0.0479 0.01525 0.00763 -0.0769 0.8733 0.1301
-3.500 -0.0266 0.01424 0.00709 -0.0758 0.8665 0.2210
-3.250 -0.0090 0.01320 0.00679 -0.0742 0.8596 0.3949
-3.000 0.0089 0.01252 0.00665 -0.0721 0.8517 0.5349
-2.750 0.0319 0.01201 0.00652 -0.0704 0.8465 0.6477
-2.500 0.0521 0.01185 0.00659 -0.0683 0.8375 0.7235
-2.250 0.0792 0.01167 0.00649 -0.0671 0.8324 0.7822
-2.000 0.1016 0.01172 0.00658 -0.0653 0.8234 0.8249
-1.750 0.1299 0.01171 0.00653 -0.0643 0.8177 0.8599
-1.500 0.1560 0.01184 0.00663 -0.0631 0.8094 0.8890
-1.250 0.1902 0.01195 0.00664 -0.0633 0.8031 0.9125
-1.000 0.2289 0.01213 0.00673 -0.0646 0.7958 0.9315
-0.750 0.2738 0.01221 0.00668 -0.0675 0.7887 0.9451
-0.500 0.3198 0.01225 0.00660 -0.0709 0.7815 0.9565
-0.250 0.3686 0.01222 0.00646 -0.0751 0.7733 0.9654
0.000 0.4144 0.01217 0.00631 -0.0788 0.7652 0.9742
0.250 0.4580 0.01209 0.00612 -0.0821 0.7566 0.9835
0.500 0.5046 0.01199 0.00596 -0.0862 0.7472 0.9912
0.750 0.5506 0.01184 0.00568 -0.0902 0.7390 0.9981
1.000 0.5787 0.01180 0.00560 -0.0907 0.7282 1.0000
1.250 0.6016 0.01177 0.00551 -0.0901 0.7189 1.0000
1.500 0.6247 0.01175 0.00541 -0.0894 0.7093 1.0000
1.750 0.6469 0.01177 0.00540 -0.0886 0.6988 1.0000
2.000 0.6702 0.01179 0.00534 -0.0879 0.6896 1.0000
2.250 0.6924 0.01182 0.00534 -0.0870 0.6792 1.0000
2.500 0.7142 0.01189 0.00538 -0.0860 0.6688 1.0000
2.750 0.7372 0.01195 0.00536 -0.0852 0.6594 1.0000
3.000 0.7586 0.01204 0.00543 -0.0841 0.6485 1.0000
3.250 0.7800 0.01214 0.00551 -0.0830 0.6378 1.0000
3.500 0.8026 0.01225 0.00555 -0.0820 0.6280 1.0000
3.750 0.8237 0.01236 0.00564 -0.0808 0.6170 1.0000
4.000 0.8445 0.01250 0.00578 -0.0795 0.6060 1.0000
4.250 0.8664 0.01265 0.00588 -0.0784 0.5956 1.0000
4.500 0.8880 0.01279 0.00598 -0.0772 0.5848 1.0000
4.750 0.9081 0.01296 0.00617 -0.0758 0.5731 1.0000
5.000 0.9290 0.01314 0.00633 -0.0745 0.5619 1.0000
5.250 0.9508 0.01333 0.00646 -0.0734 0.5511 1.0000
5.500 0.9709 0.01351 0.00665 -0.0720 0.5392 1.0000
5.750 0.9907 0.01372 0.00688 -0.0705 0.5270 1.0000
6.000 1.0109 0.01394 0.00709 -0.0691 0.5150 1.0000
6.250 1.0315 0.01417 0.00729 -0.0677 0.5031 1.0000
6.500 1.0522 0.01442 0.00751 -0.0664 0.4909 1.0000
6.750 1.0712 0.01466 0.00778 -0.0649 0.4776 1.0000
7.000 1.0906 0.01493 0.00807 -0.0634 0.4643 1.0000
7.250 1.1098 0.01522 0.00836 -0.0619 0.4508 1.0000
7.500 1.1289 0.01552 0.00868 -0.0604 0.4370 1.0000
7.750 1.1475 0.01585 0.00900 -0.0588 0.4230 1.0000
8.000 1.1655 0.01619 0.00934 -0.0572 0.4086 1.0000
8.250 1.1828 0.01656 0.00972 -0.0555 0.3938 1.0000
8.500 1.1993 0.01696 0.01012 -0.0536 0.3787 1.0000
8.750 1.2148 0.01739 0.01055 -0.0517 0.3632 1.0000
9.000 1.2293 0.01785 0.01101 -0.0496 0.3475 1.0000
9.250 1.2421 0.01834 0.01150 -0.0473 0.3316 1.0000
9.500 1.2528 0.01887 0.01204 -0.0446 0.3158 1.0000
9.750 1.2628 0.01948 0.01264 -0.0420 0.2998 1.0000
10.000 1.2723 0.02017 0.01332 -0.0394 0.2836 1.0000
10.250 1.2812 0.02095 0.01408 -0.0369 0.2673 1.0000
10.500 1.2893 0.02182 0.01494 -0.0345 0.2510 1.0000
10.750 1.2965 0.02281 0.01592 -0.0322 0.2349 1.0000
11.000 1.3028 0.02392 0.01700 -0.0299 0.2189 1.0000
11.250 1.3095 0.02509 0.01818 -0.0279 0.2024 1.0000
11.500 1.3151 0.02639 0.01948 -0.0259 0.1859 1.0000
11.750 1.3195 0.02786 0.02094 -0.0240 0.1696 1.0000
12.000 1.3225 0.02950 0.02256 -0.0221 0.1537 1.0000
12.250 1.3239 0.03135 0.02440 -0.0204 0.1383 1.0000
12.500 1.3237 0.03342 0.02643 -0.0187 0.1237 1.0000
12.750 1.3222 0.03570 0.02868 -0.0171 0.1100 1.0000
13.000 1.3195 0.03818 0.03114 -0.0157 0.0975 1.0000
13.250 1.3162 0.04082 0.03377 -0.0145 0.0863 1.0000
13.500 1.3122 0.04364 0.03661 -0.0134 0.0769 1.0000
13.750 1.3062 0.04676 0.03974 -0.0125 0.0694 1.0000
14.000 1.3003 0.05001 0.04299 -0.0119 0.0632 1.0000
14.250 1.2961 0.05318 0.04624 -0.0113 0.0577 1.0000
14.500 1.2902 0.05663 0.04971 -0.0110 0.0535 1.0000
14.750 1.2848 0.06008 0.05323 -0.0107 0.0499 1.0000
15.000 1.2823 0.06334 0.05659 -0.0107 0.0465 1.0000
15.250 1.2758 0.06701 0.06025 -0.0106 0.0439 1.0000
15.500 1.2734 0.07029 0.06364 -0.0106 0.0414 1.0000
15.750 1.2719 0.07360 0.06705 -0.0108 0.0391 1.0000
16.000 1.2695 0.07700 0.07049 -0.0111 0.0372 1.0000
16.250 1.2681 0.07982 0.07325 -0.0105 0.0354 1.0000
16.500 1.2679 0.08310 0.07672 -0.0108 0.0341 1.0000
16.750 1.2675 0.08636 0.08010 -0.0112 0.0327 1.0000
17.000 1.2673 0.08961 0.08343 -0.0117 0.0313 1.0000
17.250 1.2682 0.09258 0.08642 -0.0120 0.0301 1.0000
17.500 1.2714 0.09482 0.08867 -0.0112 0.0288 1.0000
17.750 1.2682 0.09879 0.09283 -0.0123 0.0281 1.0000
18.000 1.2658 0.10259 0.09680 -0.0133 0.0273 1.0000
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Polar data table (+)
Polar graphs
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