MRC-16 (mrc-16-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MRC-16 (mrc-16-il) Reynolds number: 500,000 Max Cl/Cd: 102.09 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mrc-16-il-500000.txt Download as CSV file: xf-mrc-16-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3817 0.09945 0.09716 -0.0500 1.0000 0.0272
-10.750 -0.3793 0.09647 0.09421 -0.0508 1.0000 0.0276
-10.500 -0.6395 0.04133 0.03807 -0.0820 0.9869 0.0177
-10.250 -0.6354 0.03603 0.03228 -0.0843 0.9821 0.0176
-10.000 -0.6272 0.03182 0.02766 -0.0849 0.9756 0.0177
-9.750 -0.6071 0.02894 0.02451 -0.0861 0.9719 0.0180
-9.500 -0.5860 0.02739 0.02281 -0.0862 0.9662 0.0184
-9.250 -0.5613 0.02649 0.02185 -0.0866 0.9607 0.0190
-9.000 -0.5378 0.02503 0.02020 -0.0868 0.9562 0.0196
-8.750 -0.5212 0.02349 0.01840 -0.0853 0.9477 0.0201
-8.500 -0.5007 0.02186 0.01648 -0.0845 0.9420 0.0206
-8.250 -0.4809 0.02065 0.01504 -0.0832 0.9343 0.0210
-8.000 -0.4585 0.01979 0.01396 -0.0823 0.9280 0.0214
-7.750 -0.4387 0.01798 0.01200 -0.0812 0.9213 0.0221
-7.500 -0.4160 0.01720 0.01117 -0.0804 0.9143 0.0228
-7.250 -0.3920 0.01658 0.01048 -0.0798 0.9085 0.0237
-7.000 -0.3684 0.01603 0.00986 -0.0791 0.9010 0.0247
-6.750 -0.3433 0.01557 0.00928 -0.0785 0.8952 0.0258
-6.500 -0.3208 0.01467 0.00829 -0.0776 0.8878 0.0269
-6.250 -0.2971 0.01404 0.00764 -0.0769 0.8812 0.0282
-6.000 -0.2724 0.01361 0.00717 -0.0763 0.8745 0.0297
-5.750 -0.2474 0.01321 0.00669 -0.0758 0.8674 0.0313
-5.500 -0.2237 0.01260 0.00602 -0.0750 0.8610 0.0334
-5.250 -0.1986 0.01225 0.00567 -0.0745 0.8534 0.0360
-4.750 -0.1486 0.01146 0.00479 -0.0735 0.8393 0.0426
-4.500 -0.1220 0.01124 0.00450 -0.0732 0.8327 0.0469
-4.250 -0.0972 0.01084 0.00413 -0.0726 0.8250 0.0542
-4.000 -0.0715 0.01052 0.00379 -0.0722 0.8180 0.0640
-3.750 -0.0459 0.01023 0.00353 -0.0718 0.8103 0.0795
-3.500 -0.0205 0.00988 0.00327 -0.0713 0.8029 0.1080
-3.250 0.0039 0.00946 0.00306 -0.0709 0.7952 0.1619
-3.000 0.0277 0.00898 0.00285 -0.0703 0.7876 0.2450
-2.750 0.0508 0.00849 0.00270 -0.0696 0.7798 0.3446
-2.500 0.0739 0.00805 0.00257 -0.0689 0.7720 0.4436
-2.250 0.0968 0.00768 0.00248 -0.0680 0.7640 0.5354
-2.000 0.1198 0.00738 0.00242 -0.0669 0.7561 0.6183
-1.750 0.1435 0.00717 0.00241 -0.0659 0.7479 0.6843
-1.500 0.1681 0.00705 0.00239 -0.0651 0.7401 0.7362
-1.250 0.1932 0.00698 0.00240 -0.0643 0.7316 0.7777
-1.000 0.2188 0.00695 0.00240 -0.0636 0.7238 0.8116
-0.750 0.2442 0.00693 0.00243 -0.0628 0.7151 0.8420
-0.500 0.2700 0.00697 0.00246 -0.0620 0.7073 0.8687
-0.250 0.2954 0.00701 0.00251 -0.0613 0.6982 0.8916
0.000 0.3218 0.00709 0.00255 -0.0606 0.6901 0.9095
0.250 0.3484 0.00716 0.00260 -0.0601 0.6810 0.9249
0.500 0.3755 0.00725 0.00265 -0.0597 0.6725 0.9384
0.750 0.4072 0.00737 0.00271 -0.0604 0.6634 0.9476
1.000 0.4379 0.00746 0.00276 -0.0609 0.6543 0.9571
1.250 0.4735 0.00760 0.00281 -0.0625 0.6452 0.9634
1.500 0.5073 0.00769 0.00287 -0.0638 0.6352 0.9706
1.750 0.5481 0.00780 0.00292 -0.0666 0.6255 0.9736
2.000 0.5866 0.00792 0.00296 -0.0690 0.6153 0.9779
2.250 0.6222 0.00801 0.00302 -0.0708 0.6047 0.9833
2.500 0.6624 0.00810 0.00306 -0.0737 0.5941 0.9863
2.750 0.7006 0.00821 0.00310 -0.0761 0.5834 0.9903
3.000 0.7379 0.00829 0.00316 -0.0784 0.5720 0.9943
3.250 0.7770 0.00837 0.00321 -0.0811 0.5607 0.9973
3.500 0.8127 0.00848 0.00327 -0.0830 0.5494 1.0000
3.750 0.8343 0.00858 0.00333 -0.0820 0.5387 1.0000
4.000 0.8557 0.00868 0.00341 -0.0810 0.5279 1.0000
4.250 0.8764 0.00880 0.00350 -0.0797 0.5175 1.0000
4.750 0.9169 0.00907 0.00373 -0.0771 0.4953 1.0000
5.000 0.9369 0.00922 0.00385 -0.0756 0.4842 1.0000
5.250 0.9563 0.00940 0.00399 -0.0741 0.4730 1.0000
5.500 0.9756 0.00958 0.00414 -0.0725 0.4615 1.0000
5.750 0.9953 0.00975 0.00430 -0.0711 0.4495 1.0000
6.000 1.0148 0.00994 0.00447 -0.0695 0.4377 1.0000
6.250 1.0339 0.01016 0.00466 -0.0679 0.4256 1.0000
6.500 1.0525 0.01040 0.00486 -0.0663 0.4130 1.0000
6.750 1.0718 0.01064 0.00507 -0.0648 0.3999 1.0000
7.000 1.0915 0.01088 0.00530 -0.0634 0.3865 1.0000
7.250 1.1111 0.01115 0.00554 -0.0620 0.3726 1.0000
7.500 1.1306 0.01145 0.00581 -0.0606 0.3583 1.0000
7.750 1.1498 0.01177 0.00610 -0.0592 0.3434 1.0000
8.000 1.1687 0.01212 0.00641 -0.0578 0.3279 1.0000
8.250 1.1869 0.01250 0.00675 -0.0563 0.3119 1.0000
8.500 1.2041 0.01291 0.00711 -0.0546 0.2954 1.0000
8.750 1.2194 0.01336 0.00751 -0.0526 0.2788 1.0000
9.000 1.2347 0.01384 0.00793 -0.0507 0.2620 1.0000
9.250 1.2500 0.01435 0.00841 -0.0489 0.2449 1.0000
9.500 1.2648 0.01492 0.00892 -0.0471 0.2278 1.0000
9.750 1.2790 0.01555 0.00949 -0.0452 0.2108 1.0000
10.000 1.2923 0.01624 0.01012 -0.0434 0.1940 1.0000
10.250 1.3047 0.01701 0.01083 -0.0415 0.1775 1.0000
10.500 1.3166 0.01784 0.01160 -0.0396 0.1613 1.0000
10.750 1.3283 0.01871 0.01242 -0.0378 0.1454 1.0000
11.000 1.3390 0.01967 0.01333 -0.0360 0.1300 1.0000
11.250 1.3485 0.02073 0.01434 -0.0342 0.1151 1.0000
11.500 1.3571 0.02189 0.01545 -0.0323 0.1011 1.0000
11.750 1.3647 0.02315 0.01667 -0.0305 0.0881 1.0000
12.000 1.3714 0.02453 0.01801 -0.0288 0.0761 1.0000
12.250 1.3773 0.02600 0.01945 -0.0271 0.0655 1.0000
12.500 1.3824 0.02759 0.02102 -0.0255 0.0562 1.0000
12.750 1.3866 0.02931 0.02274 -0.0239 0.0485 1.0000
13.000 1.3895 0.03120 0.02463 -0.0224 0.0420 1.0000
13.250 1.3919 0.03318 0.02662 -0.0211 0.0369 1.0000
13.500 1.3949 0.03518 0.02868 -0.0199 0.0329 1.0000
13.750 1.3942 0.03759 0.03111 -0.0187 0.0296 1.0000
14.000 1.3969 0.03975 0.03336 -0.0178 0.0271 1.0000
14.250 1.3972 0.04224 0.03590 -0.0171 0.0251 1.0000
14.500 1.3925 0.04535 0.03907 -0.0163 0.0234 1.0000
14.750 1.3946 0.04781 0.04164 -0.0159 0.0221 1.0000
15.000 1.3943 0.05063 0.04454 -0.0156 0.0209 1.0000
15.250 1.3901 0.05397 0.04796 -0.0154 0.0199 1.0000
15.500 1.3785 0.05828 0.05235 -0.0154 0.0190 1.0000
15.750 1.3783 0.06133 0.05552 -0.0155 0.0184 1.0000
16.000 1.3758 0.06474 0.05905 -0.0158 0.0177 1.0000
16.250 1.3720 0.06838 0.06278 -0.0162 0.0171 1.0000
16.500 1.3672 0.07220 0.06670 -0.0168 0.0165 1.0000
16.750 1.3597 0.07646 0.07104 -0.0175 0.0161 1.0000
17.000 1.3487 0.08126 0.07592 -0.0185 0.0156 1.0000
17.250 1.3343 0.08661 0.08136 -0.0196 0.0152 1.0000
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Polar data table (+)
Polar graphs
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