FX 84-W-097 (fx84w097-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 84-W-097 (fx84w097-il) Reynolds number: 100,000 Max Cl/Cd: 55.64 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx84w097-il-100000-n5.txt Download as CSV file: xf-fx84w097-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4475 0.09085 0.08602 -0.0278 1.0000 0.0289
-9.000 -0.4477 0.08622 0.08145 -0.0306 1.0000 0.0289
-8.750 -0.4347 0.08586 0.08111 -0.0287 1.0000 0.0312
-8.500 -0.4377 0.08104 0.07637 -0.0320 1.0000 0.0309
-8.000 -0.4625 0.06460 0.05997 -0.0471 1.0000 0.0290
-7.250 -0.4794 0.05064 0.04566 -0.0496 0.9993 0.0291
-7.000 -0.4599 0.04418 0.03872 -0.0547 0.9841 0.0292
-6.750 -0.4370 0.03911 0.03316 -0.0582 0.9721 0.0296
-6.500 -0.4119 0.03536 0.02898 -0.0605 0.9612 0.0303
-6.250 -0.3849 0.03244 0.02565 -0.0622 0.9512 0.0315
-6.000 -0.3555 0.03026 0.02308 -0.0637 0.9426 0.0341
-5.750 -0.3295 0.02768 0.01990 -0.0641 0.9321 0.0365
-5.500 -0.3022 0.02542 0.01705 -0.0642 0.9227 0.0379
-5.250 -0.2746 0.02352 0.01493 -0.0645 0.9147 0.0400
-5.000 -0.2489 0.02267 0.01395 -0.0644 0.9045 0.0438
-4.750 -0.2220 0.02153 0.01252 -0.0641 0.8958 0.0476
-4.500 -0.1959 0.02029 0.01110 -0.0636 0.8873 0.0507
-4.250 -0.1710 0.01959 0.01037 -0.0631 0.8779 0.0562
-4.000 -0.1450 0.01883 0.00945 -0.0625 0.8703 0.0626
-3.750 -0.1207 0.01813 0.00875 -0.0619 0.8609 0.0695
-3.500 -0.0955 0.01755 0.00813 -0.0613 0.8527 0.0804
-3.250 -0.0704 0.01699 0.00752 -0.0607 0.8445 0.0934
-3.000 -0.0454 0.01652 0.00707 -0.0602 0.8358 0.1146
-2.750 -0.0202 0.01601 0.00664 -0.0595 0.8284 0.1440
-2.500 0.0044 0.01552 0.00632 -0.0591 0.8195 0.1926
-2.250 0.0287 0.01493 0.00603 -0.0584 0.8126 0.2759
-2.000 0.0512 0.01417 0.00587 -0.0577 0.8037 0.4264
-1.750 0.0698 0.01333 0.00588 -0.0552 0.7968 0.6550
-1.500 0.0924 0.01306 0.00597 -0.0526 0.7888 0.8155
-1.250 0.1265 0.01299 0.00586 -0.0526 0.7825 0.9017
-1.000 0.1718 0.01294 0.00568 -0.0555 0.7748 0.9535
-0.750 0.2264 0.01282 0.00533 -0.0606 0.7688 0.9886
-0.500 0.2613 0.01282 0.00519 -0.0623 0.7599 1.0000
-0.250 0.2837 0.01287 0.00510 -0.0613 0.7521 1.0000
0.000 0.3064 0.01294 0.00505 -0.0604 0.7435 1.0000
0.250 0.3295 0.01302 0.00503 -0.0595 0.7352 1.0000
0.500 0.3528 0.01309 0.00499 -0.0586 0.7274 1.0000
0.750 0.3764 0.01321 0.00504 -0.0579 0.7187 1.0000
1.000 0.4006 0.01328 0.00501 -0.0571 0.7116 1.0000
1.250 0.4247 0.01342 0.00511 -0.0565 0.7024 1.0000
1.500 0.4495 0.01352 0.00513 -0.0558 0.6953 1.0000
1.750 0.4742 0.01367 0.00526 -0.0552 0.6864 1.0000
2.000 0.4994 0.01380 0.00535 -0.0547 0.6785 1.0000
2.250 0.5247 0.01392 0.00545 -0.0541 0.6702 1.0000
2.500 0.5500 0.01408 0.00560 -0.0537 0.6614 1.0000
2.750 0.5757 0.01419 0.00569 -0.0531 0.6537 1.0000
3.000 0.6010 0.01437 0.00590 -0.0527 0.6438 1.0000
3.250 0.6267 0.01452 0.00606 -0.0522 0.6350 1.0000
3.500 0.6525 0.01466 0.00621 -0.0517 0.6260 1.0000
3.750 0.6780 0.01486 0.00649 -0.0513 0.6160 1.0000
4.000 0.7039 0.01502 0.00668 -0.0509 0.6068 1.0000
4.250 0.7297 0.01518 0.00687 -0.0504 0.5966 1.0000
4.500 0.7550 0.01536 0.00713 -0.0499 0.5847 1.0000
4.750 0.7804 0.01555 0.00742 -0.0494 0.5727 1.0000
5.000 0.8058 0.01573 0.00768 -0.0489 0.5609 1.0000
5.250 0.8312 0.01592 0.00795 -0.0483 0.5484 1.0000
5.500 0.8562 0.01612 0.00825 -0.0477 0.5346 1.0000
5.750 0.8804 0.01629 0.00850 -0.0469 0.5151 1.0000
6.000 0.9034 0.01643 0.00866 -0.0459 0.4874 1.0000
6.250 0.9253 0.01665 0.00883 -0.0447 0.4533 1.0000
6.500 0.9464 0.01701 0.00915 -0.0436 0.4150 1.0000
6.750 0.9661 0.01752 0.00957 -0.0423 0.3695 1.0000
7.000 0.9831 0.01830 0.01011 -0.0408 0.3099 1.0000
7.250 0.9960 0.01951 0.01092 -0.0391 0.2347 1.0000
7.500 1.0047 0.02119 0.01208 -0.0372 0.1546 1.0000
7.750 1.0135 0.02292 0.01341 -0.0353 0.1001 1.0000
8.000 1.0237 0.02445 0.01479 -0.0334 0.0751 1.0000
8.250 1.0344 0.02585 0.01615 -0.0316 0.0617 1.0000
8.500 1.0445 0.02722 0.01755 -0.0297 0.0527 1.0000
8.750 1.0533 0.02858 0.01902 -0.0276 0.0476 1.0000
9.000 1.0601 0.02992 0.02043 -0.0254 0.0432 1.0000
9.250 1.0644 0.03155 0.02208 -0.0232 0.0397 1.0000
9.500 1.0727 0.03302 0.02370 -0.0214 0.0366 1.0000
9.750 1.0808 0.03464 0.02542 -0.0198 0.0345 1.0000
10.000 1.0889 0.03635 0.02721 -0.0183 0.0327 1.0000
10.250 1.0973 0.03840 0.02924 -0.0170 0.0307 1.0000
10.500 1.1102 0.03999 0.03106 -0.0158 0.0288 1.0000
10.750 1.1223 0.04178 0.03301 -0.0148 0.0270 1.0000
11.000 1.1348 0.04376 0.03514 -0.0137 0.0258 1.0000
11.250 1.1465 0.04587 0.03740 -0.0128 0.0249 1.0000
11.500 1.1570 0.04818 0.03983 -0.0119 0.0240 1.0000
11.750 1.1673 0.05089 0.04267 -0.0111 0.0233 1.0000
12.000 1.1727 0.05404 0.04609 -0.0102 0.0227 1.0000
12.250 1.1718 0.05709 0.04946 -0.0095 0.0222 1.0000
12.500 1.1675 0.06047 0.05318 -0.0090 0.0217 1.0000
12.750 1.1598 0.06418 0.05719 -0.0089 0.0211 1.0000
13.000 1.1506 0.06827 0.06156 -0.0093 0.0206 1.0000
13.250 1.1390 0.07282 0.06638 -0.0102 0.0203 1.0000
13.500 1.1253 0.07784 0.07166 -0.0117 0.0201 1.0000
13.750 1.1089 0.08359 0.07766 -0.0139 0.0201 1.0000
14.000 1.0907 0.08996 0.08426 -0.0169 0.0201 1.0000
14.250 1.0700 0.09721 0.09174 -0.0208 0.0202 1.0000
14.500 1.0480 0.10546 0.10019 -0.0257 0.0204 1.0000
14.750 1.0240 0.11496 0.10988 -0.0318 0.0207 1.0000
15.000 0.9991 0.12590 0.12096 -0.0389 0.0212 1.0000
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Polar data table (+)
Polar graphs
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