FX 84-W-097 (fx84w097-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 84-W-097 (fx84w097-il) Reynolds number: 200,000 Max Cl/Cd: 76.9 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx84w097-il-200000.txt Download as CSV file: xf-fx84w097-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3487 0.08832 0.08522 -0.0253 1.0000 0.0515
-9.000 -0.3413 0.08489 0.08181 -0.0257 1.0000 0.0528
-8.750 -0.4383 0.08809 0.08484 -0.0300 1.0000 0.0505
-8.500 -0.4276 0.08527 0.08203 -0.0291 1.0000 0.0515
-8.250 -0.4203 0.08237 0.07916 -0.0295 1.0000 0.0528
-8.000 -0.4179 0.07901 0.07585 -0.0313 1.0000 0.0540
-7.750 -0.4195 0.07544 0.07235 -0.0339 1.0000 0.0552
-7.500 -0.4208 0.07116 0.06811 -0.0385 1.0000 0.0567
-7.250 -0.4259 0.06719 0.06418 -0.0417 1.0000 0.0581
-7.000 -0.4305 0.06137 0.05786 -0.0524 0.9897 0.0617
-6.750 -0.4106 0.05357 0.05010 -0.0570 0.9842 0.0635
-6.500 -0.3822 0.05033 0.04685 -0.0599 0.9776 0.0655
-6.250 -0.3510 0.04614 0.04245 -0.0647 0.9710 0.0699
-6.000 -0.3318 0.03343 0.02853 -0.0694 0.9585 0.0516
-5.750 -0.3074 0.02844 0.02301 -0.0699 0.9484 0.0449
-5.500 -0.2832 0.02427 0.01816 -0.0697 0.9392 0.0432
-5.250 -0.2579 0.02194 0.01537 -0.0691 0.9301 0.0441
-5.000 -0.2337 0.02070 0.01381 -0.0682 0.9198 0.0470
-4.750 -0.2087 0.01983 0.01259 -0.0671 0.9108 0.0492
-4.500 -0.1859 0.01770 0.01027 -0.0661 0.9020 0.0519
-4.250 -0.1619 0.01696 0.00946 -0.0652 0.8925 0.0561
-4.000 -0.1373 0.01648 0.00880 -0.0640 0.8846 0.0613
-3.750 -0.1139 0.01532 0.00766 -0.0631 0.8752 0.0671
-3.500 -0.0889 0.01494 0.00715 -0.0622 0.8670 0.0751
-3.250 -0.0653 0.01419 0.00645 -0.0612 0.8589 0.0869
-3.000 -0.0405 0.01366 0.00592 -0.0605 0.8503 0.1032
-2.750 -0.0165 0.01307 0.00543 -0.0596 0.8431 0.1306
-2.500 0.0080 0.01245 0.00508 -0.0592 0.8342 0.1834
-2.250 0.0308 0.01168 0.00478 -0.0583 0.8277 0.3013
-2.000 0.0499 0.01057 0.00470 -0.0570 0.8186 0.5570
-1.750 0.0653 0.00994 0.00483 -0.0533 0.8120 0.7829
-1.500 0.0869 0.00987 0.00491 -0.0506 0.8035 0.8828
-1.250 0.1208 0.00987 0.00480 -0.0506 0.7975 0.9397
-1.000 0.1750 0.00986 0.00465 -0.0554 0.7897 0.9742
-0.750 0.2391 0.00975 0.00432 -0.0625 0.7841 0.9963
-0.500 0.2692 0.00974 0.00422 -0.0633 0.7748 1.0000
-0.250 0.2912 0.00976 0.00412 -0.0622 0.7673 1.0000
0.000 0.3137 0.00979 0.00407 -0.0613 0.7585 1.0000
0.250 0.3366 0.00985 0.00404 -0.0604 0.7506 1.0000
0.500 0.3598 0.00990 0.00400 -0.0595 0.7427 1.0000
0.750 0.3834 0.00998 0.00402 -0.0587 0.7344 1.0000
1.000 0.4073 0.01004 0.00399 -0.0579 0.7271 1.0000
1.250 0.4315 0.01015 0.00406 -0.0572 0.7184 1.0000
1.500 0.4561 0.01022 0.00403 -0.0564 0.7115 1.0000
1.750 0.4808 0.01033 0.00414 -0.0559 0.7020 1.0000
2.000 0.5061 0.01042 0.00417 -0.0553 0.6944 1.0000
2.250 0.5315 0.01051 0.00424 -0.0548 0.6854 1.0000
2.500 0.5572 0.01063 0.00434 -0.0543 0.6768 1.0000
2.750 0.5833 0.01072 0.00439 -0.0538 0.6688 1.0000
3.000 0.6093 0.01085 0.00454 -0.0535 0.6593 1.0000
3.250 0.6356 0.01096 0.00462 -0.0531 0.6511 1.0000
3.500 0.6618 0.01106 0.00474 -0.0527 0.6412 1.0000
3.750 0.6880 0.01117 0.00487 -0.0523 0.6305 1.0000
4.000 0.7144 0.01129 0.00498 -0.0519 0.6207 1.0000
4.250 0.7409 0.01140 0.00509 -0.0516 0.6109 1.0000
4.500 0.7671 0.01153 0.00530 -0.0512 0.5994 1.0000
4.750 0.7933 0.01166 0.00547 -0.0508 0.5879 1.0000
5.000 0.8194 0.01176 0.00559 -0.0504 0.5747 1.0000
5.250 0.8446 0.01176 0.00559 -0.0497 0.5556 1.0000
5.500 0.8695 0.01181 0.00565 -0.0489 0.5341 1.0000
5.750 0.8945 0.01192 0.00578 -0.0483 0.5128 1.0000
6.000 0.9192 0.01208 0.00596 -0.0477 0.4901 1.0000
6.250 0.9434 0.01229 0.00616 -0.0470 0.4639 1.0000
6.500 0.9666 0.01257 0.00643 -0.0462 0.4298 1.0000
6.750 0.9881 0.01302 0.00676 -0.0453 0.3838 1.0000
7.000 1.0061 0.01380 0.00725 -0.0439 0.3139 1.0000
7.250 1.0151 0.01550 0.00825 -0.0419 0.1956 1.0000
7.500 1.0186 0.01789 0.00985 -0.0393 0.0914 1.0000
7.750 1.0297 0.01946 0.01125 -0.0373 0.0663 1.0000
8.000 1.0425 0.02075 0.01257 -0.0354 0.0552 1.0000
8.250 1.0522 0.02224 0.01408 -0.0332 0.0491 1.0000
8.500 1.0653 0.02338 0.01525 -0.0315 0.0436 1.0000
8.750 1.0720 0.02516 0.01702 -0.0290 0.0400 1.0000
9.000 1.0857 0.02631 0.01828 -0.0271 0.0376 1.0000
9.250 1.0996 0.02767 0.01970 -0.0254 0.0352 1.0000
9.500 1.1151 0.02919 0.02126 -0.0241 0.0333 1.0000
9.750 1.1474 0.03277 0.02484 -0.0251 0.0309 1.0000
10.000 1.1608 0.03371 0.02600 -0.0233 0.0298 1.0000
10.250 1.1782 0.03543 0.02794 -0.0221 0.0285 1.0000
10.500 1.1970 0.03778 0.03053 -0.0213 0.0277 1.0000
10.750 1.2119 0.04041 0.03344 -0.0201 0.0272 1.0000
11.000 1.2214 0.04332 0.03666 -0.0184 0.0269 1.0000
11.250 1.2242 0.04648 0.04014 -0.0161 0.0268 1.0000
11.500 1.2210 0.04978 0.04379 -0.0137 0.0270 1.0000
11.750 1.2150 0.05271 0.04698 -0.0116 0.0267 1.0000
12.000 1.2062 0.05587 0.05039 -0.0098 0.0264 1.0000
12.250 1.1930 0.05969 0.05448 -0.0085 0.0266 1.0000
12.500 1.1833 0.06286 0.05783 -0.0079 0.0260 1.0000
12.750 1.1590 0.06840 0.06369 -0.0079 0.0267 1.0000
13.000 1.1369 0.07390 0.06944 -0.0089 0.0271 1.0000
13.250 1.1156 0.07954 0.07529 -0.0108 0.0272 1.0000
13.500 1.0901 0.08652 0.08248 -0.0138 0.0279 1.0000
13.750 1.0658 0.09382 0.08994 -0.0177 0.0282 1.0000
14.000 1.0410 0.10200 0.09827 -0.0225 0.0289 1.0000
14.250 1.0167 0.11104 0.10742 -0.0279 0.0297 1.0000
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Polar data table (+)
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