FX 84-W-127 (fx84w127-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 84-W-127 (fx84w127-il) Reynolds number: 500,000 Max Cl/Cd: 110.32 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx84w127-il-500000-n5.txt Download as CSV file: xf-fx84w127-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-127
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7608 0.03783 0.03464 -0.0935 0.9389 0.0106
-12.500 -0.7719 0.03486 0.03143 -0.0938 0.9129 0.0108
-12.250 -0.7861 0.03254 0.02888 -0.0915 0.8944 0.0108
-12.000 -0.7906 0.03073 0.02684 -0.0892 0.8821 0.0109
-11.750 -0.7859 0.02900 0.02489 -0.0878 0.8723 0.0111
-11.500 -0.7772 0.02743 0.02309 -0.0866 0.8642 0.0113
-11.250 -0.7654 0.02596 0.02139 -0.0855 0.8563 0.0115
-11.000 -0.7507 0.02464 0.01985 -0.0846 0.8498 0.0118
-10.750 -0.7341 0.02341 0.01841 -0.0838 0.8430 0.0120
-10.250 -0.6971 0.02121 0.01586 -0.0824 0.8305 0.0126
-10.000 -0.6760 0.02040 0.01494 -0.0819 0.8245 0.0129
-9.750 -0.6535 0.01974 0.01415 -0.0815 0.8190 0.0133
-9.500 -0.6301 0.01912 0.01344 -0.0812 0.8130 0.0138
-9.250 -0.6068 0.01847 0.01265 -0.0808 0.8075 0.0143
-9.000 -0.5828 0.01784 0.01189 -0.0805 0.8021 0.0148
-8.750 -0.5585 0.01724 0.01115 -0.0802 0.7964 0.0154
-8.500 -0.5347 0.01656 0.01033 -0.0798 0.7912 0.0159
-8.250 -0.5100 0.01597 0.00968 -0.0796 0.7860 0.0165
-8.000 -0.4845 0.01550 0.00913 -0.0795 0.7806 0.0171
-7.750 -0.4590 0.01506 0.00859 -0.0792 0.7756 0.0178
-7.500 -0.4329 0.01462 0.00806 -0.0791 0.7705 0.0186
-7.250 -0.4066 0.01423 0.00757 -0.0790 0.7654 0.0194
-7.000 -0.3809 0.01376 0.00705 -0.0788 0.7606 0.0205
-6.750 -0.3542 0.01342 0.00666 -0.0788 0.7557 0.0216
-6.500 -0.3274 0.01308 0.00624 -0.0787 0.7503 0.0227
-6.250 -0.3006 0.01276 0.00584 -0.0786 0.7456 0.0238
-6.000 -0.2738 0.01239 0.00543 -0.0785 0.7411 0.0254
-5.750 -0.2466 0.01212 0.00513 -0.0785 0.7359 0.0271
-5.500 -0.2194 0.01188 0.00481 -0.0785 0.7308 0.0289
-5.250 -0.1922 0.01158 0.00447 -0.0785 0.7261 0.0308
-5.000 -0.1648 0.01133 0.00421 -0.0785 0.7208 0.0331
-4.750 -0.1372 0.01114 0.00395 -0.0785 0.7157 0.0357
-4.500 -0.1098 0.01089 0.00369 -0.0785 0.7108 0.0390
-4.250 -0.0820 0.01070 0.00347 -0.0785 0.7054 0.0425
-4.000 -0.0544 0.01052 0.00325 -0.0785 0.7003 0.0465
-3.750 -0.0266 0.01034 0.00306 -0.0786 0.6955 0.0518
-3.500 0.0014 0.01016 0.00288 -0.0787 0.6902 0.0576
-3.250 0.0292 0.01002 0.00272 -0.0787 0.6852 0.0649
-3.000 0.0571 0.00986 0.00257 -0.0788 0.6804 0.0748
-2.750 0.0851 0.00970 0.00244 -0.0789 0.6751 0.0864
-2.500 0.1130 0.00956 0.00232 -0.0790 0.6701 0.1010
-2.250 0.1410 0.00942 0.00221 -0.0791 0.6654 0.1187
-2.000 0.1689 0.00926 0.00212 -0.0792 0.6600 0.1420
-1.750 0.1967 0.00911 0.00203 -0.0793 0.6548 0.1700
-1.500 0.2245 0.00894 0.00196 -0.0795 0.6500 0.2079
-1.250 0.2522 0.00873 0.00190 -0.0796 0.6446 0.2575
-1.000 0.2795 0.00848 0.00183 -0.0797 0.6392 0.3260
-0.750 0.3065 0.00815 0.00179 -0.0798 0.6341 0.4221
-0.500 0.3331 0.00779 0.00177 -0.0799 0.6282 0.5350
-0.250 0.3595 0.00754 0.00179 -0.0797 0.6227 0.6298
0.000 0.3863 0.00740 0.00184 -0.0794 0.6172 0.6940
0.250 0.4134 0.00735 0.00188 -0.0792 0.6114 0.7388
0.500 0.4401 0.00734 0.00193 -0.0789 0.6063 0.7736
1.000 0.4939 0.00734 0.00204 -0.0783 0.5955 0.8264
1.250 0.5204 0.00738 0.00209 -0.0779 0.5903 0.8473
1.500 0.5455 0.00738 0.00216 -0.0772 0.5846 0.8750
1.750 0.5696 0.00742 0.00223 -0.0762 0.5792 0.9005
2.000 0.5949 0.00746 0.00228 -0.0755 0.5739 0.9160
2.750 0.6753 0.00762 0.00244 -0.0748 0.5547 0.9511
3.000 0.7050 0.00770 0.00249 -0.0752 0.5480 0.9617
3.250 0.7366 0.00777 0.00257 -0.0761 0.5417 0.9719
3.500 0.7701 0.00787 0.00265 -0.0775 0.5348 0.9813
3.750 0.8042 0.00797 0.00274 -0.0790 0.5283 0.9914
4.000 0.8352 0.00807 0.00284 -0.0799 0.5210 1.0000
4.250 0.8609 0.00821 0.00296 -0.0796 0.5130 1.0000
4.500 0.8868 0.00836 0.00308 -0.0794 0.5032 1.0000
4.750 0.9131 0.00850 0.00321 -0.0793 0.4944 1.0000
5.250 0.9654 0.00881 0.00352 -0.0790 0.4772 1.0000
5.500 0.9911 0.00899 0.00369 -0.0788 0.4677 1.0000
5.750 1.0160 0.00921 0.00388 -0.0784 0.4534 1.0000
6.000 1.0383 0.00957 0.00412 -0.0777 0.4265 1.0000
6.250 1.0594 0.01000 0.00441 -0.0767 0.3950 1.0000
6.500 1.0808 0.01041 0.00471 -0.0759 0.3679 1.0000
6.750 1.1011 0.01089 0.00507 -0.0749 0.3401 1.0000
7.000 1.1198 0.01144 0.00549 -0.0737 0.3089 1.0000
7.250 1.1363 0.01209 0.00597 -0.0721 0.2745 1.0000
7.500 1.1503 0.01286 0.00654 -0.0702 0.2363 1.0000
7.750 1.1618 0.01369 0.00717 -0.0680 0.1993 1.0000
8.000 1.1706 0.01449 0.00782 -0.0652 0.1674 1.0000
8.250 1.1760 0.01540 0.00856 -0.0620 0.1361 1.0000
8.500 1.1822 0.01635 0.00936 -0.0591 0.1091 1.0000
8.750 1.1899 0.01730 0.01021 -0.0567 0.0879 1.0000
9.000 1.1987 0.01824 0.01108 -0.0545 0.0721 1.0000
9.250 1.2082 0.01920 0.01199 -0.0525 0.0598 1.0000
9.500 1.2191 0.02012 0.01289 -0.0509 0.0513 1.0000
9.750 1.2305 0.02105 0.01382 -0.0493 0.0450 1.0000
10.000 1.2406 0.02208 0.01484 -0.0477 0.0392 1.0000
10.250 1.2522 0.02307 0.01585 -0.0463 0.0352 1.0000
10.500 1.2623 0.02418 0.01698 -0.0449 0.0318 1.0000
10.750 1.2740 0.02522 0.01806 -0.0437 0.0295 1.0000
11.000 1.2836 0.02644 0.01930 -0.0424 0.0268 1.0000
11.250 1.2934 0.02768 0.02058 -0.0412 0.0249 1.0000
11.500 1.3037 0.02892 0.02187 -0.0402 0.0233 1.0000
11.750 1.3128 0.03029 0.02329 -0.0391 0.0220 1.0000
12.000 1.3203 0.03181 0.02486 -0.0380 0.0208 1.0000
12.250 1.3288 0.03329 0.02640 -0.0371 0.0198 1.0000
12.500 1.3371 0.03483 0.02802 -0.0362 0.0189 1.0000
12.750 1.3445 0.03647 0.02972 -0.0354 0.0180 1.0000
13.000 1.3510 0.03825 0.03154 -0.0346 0.0170 1.0000
13.250 1.3554 0.04029 0.03363 -0.0339 0.0163 1.0000
13.500 1.3619 0.04218 0.03560 -0.0333 0.0157 1.0000
13.750 1.3684 0.04412 0.03763 -0.0328 0.0151 1.0000
14.000 1.3738 0.04623 0.03982 -0.0324 0.0146 1.0000
14.250 1.3790 0.04841 0.04208 -0.0321 0.0140 1.0000
14.500 1.3829 0.05079 0.04452 -0.0319 0.0135 1.0000
14.750 1.3860 0.05332 0.04712 -0.0317 0.0131 1.0000
15.000 1.3866 0.05623 0.05009 -0.0317 0.0126 1.0000
15.250 1.3899 0.05888 0.05284 -0.0318 0.0123 1.0000
15.500 1.3930 0.06161 0.05568 -0.0320 0.0120 1.0000
15.750 1.3970 0.06427 0.05843 -0.0322 0.0115 1.0000
16.000 1.3990 0.06725 0.06150 -0.0326 0.0112 1.0000
16.250 1.3992 0.07056 0.06491 -0.0331 0.0110 1.0000
16.500 1.4014 0.07361 0.06804 -0.0337 0.0106 1.0000
16.750 1.4013 0.07707 0.07158 -0.0345 0.0104 1.0000
17.000 1.3999 0.08078 0.07538 -0.0354 0.0101 1.0000
17.250 1.3975 0.08474 0.07943 -0.0365 0.0099 1.0000
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