FX 84-W-127 (fx84w127-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 84-W-127 (fx84w127-il) Reynolds number: 100,000 Max Cl/Cd: 53.82 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx84w127-il-100000.txt Download as CSV file: xf-fx84w127-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3581 0.10407 0.09977 -0.0351 1.0000 0.1142
-8.750 -0.3770 0.10328 0.09907 -0.0326 1.0000 0.1162
-8.500 -0.4020 0.10131 0.09720 -0.0381 0.9957 0.1196
-8.250 -0.3892 0.09573 0.09164 -0.0422 0.9902 0.1224
-8.000 -0.3583 0.09204 0.08788 -0.0430 0.9865 0.1273
-7.750 -0.3675 0.08798 0.08387 -0.0528 0.9754 0.1341
-7.500 -0.3647 0.08215 0.07802 -0.0604 0.9663 0.1375
-7.250 -0.3353 0.07945 0.07530 -0.0592 0.9625 0.1431
-7.000 -0.3528 0.07329 0.06898 -0.0719 0.9482 0.1520
-6.750 -0.3145 0.07086 0.06662 -0.0699 0.9461 0.1605
-6.500 -0.3175 0.06672 0.06238 -0.0741 0.9356 0.1696
-6.250 -0.2998 0.06261 0.05810 -0.0793 0.9297 0.1842
-6.000 -0.3115 0.04927 0.04377 -0.0845 0.9177 0.1093
-5.750 -0.2951 0.04126 0.03474 -0.0858 0.9119 0.0872
-5.500 -0.2806 0.03840 0.03142 -0.0848 0.9040 0.0871
-5.250 -0.2459 0.03543 0.02774 -0.0868 0.9001 0.0899
-5.000 -0.2316 0.03388 0.02571 -0.0847 0.8917 0.0910
-4.750 -0.1987 0.03167 0.02337 -0.0864 0.8871 0.0960
-4.500 -0.1556 0.03011 0.02142 -0.0891 0.8841 0.1034
-4.250 -0.1448 0.02928 0.02037 -0.0863 0.8749 0.1072
-4.000 -0.1060 0.02821 0.01922 -0.0883 0.8708 0.1180
-3.500 -0.0546 0.02667 0.01760 -0.0878 0.8580 0.1395
-3.250 -0.0170 0.02577 0.01677 -0.0894 0.8543 0.1593
-3.000 -0.0015 0.02551 0.01656 -0.0875 0.8460 0.1772
-2.750 0.0287 0.02481 0.01602 -0.0879 0.8408 0.2137
-2.500 0.0629 0.02366 0.01539 -0.0889 0.8375 0.2914
-2.250 0.0663 0.02308 0.01568 -0.0854 0.8278 0.4344
-2.000 0.0810 0.02228 0.01613 -0.0804 0.8236 0.7626
-1.750 0.0874 0.02278 0.01673 -0.0750 0.8155 0.8549
-1.500 0.1339 0.02302 0.01686 -0.0762 0.8114 0.9345
-1.250 0.2745 0.02273 0.01612 -0.0954 0.8134 0.9831
-1.000 0.3592 0.02223 0.01535 -0.1062 0.8110 1.0000
-0.750 0.3840 0.02205 0.01503 -0.1057 0.8065 1.0000
-0.500 0.3775 0.02283 0.01576 -0.1012 0.7951 1.0000
-0.250 0.4041 0.02266 0.01546 -0.1008 0.7910 1.0000
0.000 0.3942 0.02355 0.01632 -0.0956 0.7795 1.0000
0.250 0.4233 0.02338 0.01602 -0.0955 0.7757 1.0000
0.500 0.4136 0.02435 0.01694 -0.0902 0.7642 1.0000
0.750 0.4454 0.02417 0.01665 -0.0904 0.7606 1.0000
1.000 0.4412 0.02520 0.01763 -0.0862 0.7495 1.0000
1.250 0.4745 0.02503 0.01737 -0.0865 0.7457 1.0000
1.500 0.4779 0.02606 0.01835 -0.0836 0.7354 1.0000
1.750 0.5102 0.02597 0.01819 -0.0839 0.7312 1.0000
2.000 0.5466 0.02572 0.01788 -0.0846 0.7284 1.0000
2.250 0.5491 0.02698 0.01912 -0.0818 0.7169 1.0000
2.500 0.5872 0.02663 0.01873 -0.0827 0.7142 1.0000
2.750 0.5900 0.02803 0.02012 -0.0801 0.7027 1.0000
3.000 0.6274 0.02768 0.01975 -0.0808 0.6997 1.0000
3.250 0.6333 0.02899 0.02108 -0.0786 0.6886 1.0000
3.500 0.6699 0.02863 0.02071 -0.0792 0.6851 1.0000
3.750 0.7090 0.02814 0.02022 -0.0800 0.6823 1.0000
4.000 0.7138 0.02954 0.02165 -0.0777 0.6706 1.0000
4.250 0.7559 0.02882 0.02096 -0.0787 0.6683 1.0000
5.000 0.8033 0.03128 0.02356 -0.0749 0.6416 1.0000
5.250 0.8471 0.03033 0.02265 -0.0759 0.6389 1.0000
5.500 0.8509 0.03190 0.02429 -0.0736 0.6271 1.0000
5.750 0.8967 0.03072 0.02320 -0.0746 0.6242 1.0000
6.000 0.9042 0.03199 0.02454 -0.0725 0.6128 1.0000
6.250 0.9522 0.03057 0.02321 -0.0737 0.6094 1.0000
6.500 0.9631 0.03156 0.02429 -0.0718 0.5985 1.0000
6.750 1.0106 0.03015 0.02299 -0.0730 0.5944 1.0000
7.000 1.0255 0.03083 0.02378 -0.0713 0.5839 1.0000
7.250 1.0746 0.02925 0.02232 -0.0726 0.5788 1.0000
7.500 1.0946 0.02940 0.02259 -0.0712 0.5675 1.0000
7.750 1.1378 0.02750 0.02075 -0.0713 0.5553 1.0000
8.000 1.1751 0.02573 0.01903 -0.0707 0.5387 1.0000
8.250 1.2052 0.02471 0.01805 -0.0697 0.5217 1.0000
8.500 1.2315 0.02405 0.01743 -0.0684 0.5039 1.0000
8.750 1.2538 0.02363 0.01705 -0.0668 0.4847 1.0000
9.000 1.2645 0.02376 0.01731 -0.0639 0.4631 1.0000
9.250 1.2778 0.02374 0.01730 -0.0612 0.4391 1.0000
9.500 1.2826 0.02411 0.01770 -0.0576 0.4121 1.0000
9.750 1.2796 0.02477 0.01833 -0.0531 0.3826 1.0000
10.000 1.2722 0.02588 0.01935 -0.0486 0.3465 1.0000
10.250 1.2598 0.02762 0.02086 -0.0442 0.2998 1.0000
10.500 1.2411 0.03020 0.02303 -0.0401 0.2472 1.0000
10.750 1.2198 0.03350 0.02590 -0.0365 0.1980 1.0000
11.000 1.2009 0.03705 0.02905 -0.0338 0.1626 1.0000
11.250 1.1891 0.04031 0.03205 -0.0316 0.1373 1.0000
11.500 1.1828 0.04322 0.03473 -0.0298 0.1210 1.0000
11.750 1.1837 0.04562 0.03699 -0.0283 0.1078 1.0000
12.000 1.1901 0.04764 0.03898 -0.0269 0.0972 1.0000
12.250 1.2030 0.04930 0.04060 -0.0255 0.0884 1.0000
12.500 1.2228 0.05072 0.04185 -0.0244 0.0804 1.0000
12.750 1.2400 0.05235 0.04361 -0.0234 0.0748 1.0000
13.000 1.2739 0.05378 0.04494 -0.0227 0.0686 1.0000
13.250 1.2869 0.05588 0.04729 -0.0219 0.0651 1.0000
13.500 1.3077 0.05793 0.04945 -0.0213 0.0618 1.0000
13.750 1.3450 0.06098 0.05252 -0.0214 0.0582 1.0000
14.000 1.3401 0.06390 0.05580 -0.0201 0.0570 1.0000
14.250 1.3366 0.06720 0.05943 -0.0191 0.0557 1.0000
14.500 1.3319 0.07080 0.06335 -0.0184 0.0547 1.0000
14.750 1.3246 0.07483 0.06769 -0.0179 0.0541 1.0000
15.000 1.3131 0.07927 0.07244 -0.0177 0.0538 1.0000
15.250 1.2975 0.08418 0.07765 -0.0179 0.0537 1.0000
15.500 1.2778 0.08964 0.08341 -0.0188 0.0538 1.0000
15.750 1.2550 0.09570 0.08976 -0.0203 0.0541 1.0000
16.000 1.2294 0.10248 0.09681 -0.0227 0.0544 1.0000
16.250 1.2019 0.11007 0.10465 -0.0260 0.0550 1.0000
16.500 1.1722 0.11862 0.11341 -0.0305 0.0557 1.0000
16.750 1.1411 0.12826 0.12324 -0.0361 0.0565 1.0000
17.000 1.1110 0.13884 0.13396 -0.0426 0.0574 1.0000
17.250 1.0884 0.14899 0.14419 -0.0486 0.0583 1.0000
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