FX 84-W-097 (fx84w097-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 84-W-097 (fx84w097-il) Reynolds number: 100,000 Max Cl/Cd: 56.48 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx84w097-il-100000.txt Download as CSV file: xf-fx84w097-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-097
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4339 0.11468 0.10978 -0.0147 1.0000 0.0868
-9.750 -0.4477 0.11282 0.10803 -0.0207 1.0000 0.0884
-9.500 -0.4618 0.11038 0.10571 -0.0267 1.0000 0.0888
-9.250 -0.4215 0.10332 0.09855 -0.0193 1.0000 0.0925
-9.000 -0.4136 0.10014 0.09540 -0.0200 1.0000 0.0967
-8.750 -0.3252 0.08790 0.08355 -0.0254 1.0000 0.1095
-8.500 -0.3271 0.08431 0.08001 -0.0274 1.0000 0.1139
-8.250 -0.3519 0.08126 0.07709 -0.0334 1.0000 0.1166
-8.000 -0.3434 0.07612 0.07199 -0.0330 1.0000 0.1188
-7.750 -0.3255 0.07262 0.06849 -0.0311 1.0000 0.1235
-7.500 -0.3331 0.06926 0.06522 -0.0330 1.0000 0.1282
-7.250 -0.4131 0.07605 0.07179 -0.0345 1.0000 0.1216
-7.000 -0.4129 0.07316 0.06896 -0.0354 1.0000 0.1263
-6.750 -0.4438 0.07160 0.06740 -0.0373 1.0000 0.1306
-6.500 -0.4677 0.06959 0.06533 -0.0362 1.0000 0.1321
-6.250 -0.4630 0.06678 0.06269 -0.0316 1.0000 0.1341
-6.000 -0.4652 0.06495 0.06090 -0.0285 1.0000 0.1370
-5.750 -0.4774 0.06238 0.05804 -0.0313 0.9998 0.1467
-5.500 -0.4484 0.05840 0.05420 -0.0318 0.9948 0.1522
-5.250 -0.4175 0.05399 0.04962 -0.0373 0.9869 0.1667
-5.000 -0.3747 0.03916 0.03312 -0.0482 0.9788 0.0912
-4.750 -0.3378 0.03430 0.02768 -0.0511 0.9727 0.0832
-4.500 -0.3029 0.02962 0.02204 -0.0529 0.9659 0.0780
-4.250 -0.2641 0.02745 0.01953 -0.0554 0.9596 0.0821
-4.000 -0.2268 0.02558 0.01708 -0.0570 0.9526 0.0871
-3.750 -0.1876 0.02353 0.01477 -0.0592 0.9463 0.0927
-3.500 -0.1480 0.02234 0.01337 -0.0614 0.9400 0.1044
-3.250 -0.1100 0.02116 0.01210 -0.0632 0.9329 0.1182
-3.000 -0.0675 0.01999 0.01109 -0.0661 0.9278 0.1422
-2.750 -0.0379 0.01918 0.01042 -0.0665 0.9188 0.1758
-2.500 -0.0051 0.01804 0.00978 -0.0676 0.9119 0.2511
-2.250 0.0127 0.01604 0.00961 -0.0656 0.9036 0.6055
-2.000 0.0816 0.01563 0.00977 -0.0688 0.9033 0.9560
-1.750 0.1914 0.01516 0.00882 -0.0842 0.9046 1.0000
-1.500 0.2145 0.01525 0.00873 -0.0837 0.8934 1.0000
-1.250 0.2391 0.01532 0.00864 -0.0833 0.8836 1.0000
-1.000 0.2600 0.01546 0.00862 -0.0821 0.8729 1.0000
-0.750 0.2780 0.01568 0.00873 -0.0806 0.8615 1.0000
-0.500 0.2979 0.01588 0.00881 -0.0792 0.8513 1.0000
-0.250 0.3208 0.01598 0.00879 -0.0780 0.8429 1.0000
0.000 0.3390 0.01627 0.00898 -0.0764 0.8317 1.0000
0.250 0.3592 0.01652 0.00914 -0.0750 0.8220 1.0000
0.500 0.3824 0.01662 0.00914 -0.0737 0.8140 1.0000
0.750 0.4019 0.01694 0.00942 -0.0724 0.8034 1.0000
1.000 0.4239 0.01717 0.00958 -0.0711 0.7946 1.0000
1.250 0.4470 0.01733 0.00968 -0.0700 0.7860 1.0000
1.500 0.4683 0.01766 0.00998 -0.0689 0.7760 1.0000
1.750 0.4939 0.01768 0.00995 -0.0678 0.7694 1.0000
2.000 0.5154 0.01805 0.01032 -0.0669 0.7584 1.0000
2.250 0.5385 0.01832 0.01058 -0.0659 0.7490 1.0000
2.500 0.5643 0.01835 0.01059 -0.0649 0.7414 1.0000
2.750 0.5869 0.01869 0.01097 -0.0641 0.7306 1.0000
3.000 0.6115 0.01887 0.01116 -0.0632 0.7217 1.0000
3.250 0.6371 0.01895 0.01125 -0.0623 0.7130 1.0000
3.500 0.6605 0.01927 0.01162 -0.0615 0.7023 1.0000
3.750 0.6861 0.01939 0.01180 -0.0606 0.6934 1.0000
4.000 0.7119 0.01945 0.01189 -0.0598 0.6839 1.0000
4.250 0.7359 0.01967 0.01218 -0.0589 0.6722 1.0000
4.500 0.7609 0.01978 0.01236 -0.0580 0.6611 1.0000
4.750 0.7881 0.01970 0.01234 -0.0570 0.6517 1.0000
5.000 0.8137 0.01975 0.01247 -0.0561 0.6402 1.0000
5.250 0.8385 0.01987 0.01269 -0.0552 0.6273 1.0000
5.500 0.8637 0.01989 0.01284 -0.0542 0.6140 1.0000
5.750 0.8901 0.01955 0.01255 -0.0529 0.5982 1.0000
6.000 0.9152 0.01905 0.01207 -0.0512 0.5772 1.0000
6.250 0.9404 0.01849 0.01151 -0.0494 0.5538 1.0000
6.500 0.9634 0.01823 0.01136 -0.0478 0.5278 1.0000
6.750 0.9860 0.01806 0.01125 -0.0462 0.4990 1.0000
7.000 1.0069 0.01798 0.01122 -0.0445 0.4633 1.0000
7.250 1.0246 0.01814 0.01133 -0.0424 0.4110 1.0000
7.500 1.0326 0.01910 0.01181 -0.0393 0.3012 1.0000
7.750 1.0222 0.02227 0.01367 -0.0350 0.1550 1.0000
8.000 1.0222 0.02473 0.01564 -0.0318 0.1138 1.0000
8.250 1.0293 0.02656 0.01740 -0.0293 0.0942 1.0000
8.500 1.0394 0.02841 0.01917 -0.0270 0.0831 1.0000
8.750 1.0547 0.03038 0.02098 -0.0255 0.0739 1.0000
9.000 1.0751 0.03209 0.02272 -0.0245 0.0667 1.0000
9.250 1.1067 0.03489 0.02549 -0.0247 0.0616 1.0000
9.500 1.1287 0.03682 0.02764 -0.0238 0.0569 1.0000
9.750 1.1528 0.03930 0.03020 -0.0236 0.0534 1.0000
10.000 1.1821 0.04422 0.03528 -0.0241 0.0516 1.0000
10.250 1.1957 0.04730 0.03877 -0.0225 0.0511 1.0000
10.500 1.2055 0.05071 0.04261 -0.0208 0.0509 1.0000
10.750 1.2089 0.05387 0.04620 -0.0187 0.0505 1.0000
11.000 1.2070 0.05695 0.04969 -0.0163 0.0500 1.0000
11.250 1.1999 0.06009 0.05321 -0.0138 0.0495 1.0000
11.500 1.1891 0.06348 0.05688 -0.0112 0.0496 1.0000
11.750 1.1749 0.06702 0.06068 -0.0091 0.0497 1.0000
12.000 1.1589 0.07101 0.06490 -0.0078 0.0500 1.0000
12.250 1.1445 0.07566 0.06975 -0.0074 0.0506 1.0000
12.500 1.1441 0.08203 0.07624 -0.0077 0.0517 1.0000
12.750 1.1216 0.08508 0.07954 -0.0079 0.0522 1.0000
13.000 1.0844 0.09021 0.08497 -0.0104 0.0531 1.0000
13.250 0.9946 0.10631 0.10150 -0.0225 0.0590 1.0000
13.500 0.9697 0.11616 0.11141 -0.0285 0.0610 1.0000
13.750 0.9647 0.12298 0.11823 -0.0309 0.0626 1.0000
14.000 0.7541 0.13892 0.13455 -0.0389 0.0748 1.0000
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Polar data table (+)
Polar graphs
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