FX 84-W-097 (fx84w097-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: FX 84-W-097 (fx84w097-il) Reynolds number: 50,000 Max Cl/Cd: 36.14 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx84w097-il-50000.txt Download as CSV file: xf-fx84w097-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4281 0.11573 0.10900 -0.0125 1.0000 0.2033
-9.250 -0.4106 0.11078 0.10402 -0.0120 1.0000 0.2120
-9.000 -0.4272 0.11013 0.10351 -0.0150 1.0000 0.2188
-8.750 -0.4116 0.10563 0.09902 -0.0143 1.0000 0.2324
-8.500 -0.3980 0.10146 0.09488 -0.0138 1.0000 0.2441
-8.250 -0.3928 0.09810 0.09158 -0.0142 1.0000 0.2549
-8.000 -0.3970 0.09562 0.08920 -0.0152 1.0000 0.2657
-7.750 -0.4074 0.09420 0.08792 -0.0162 1.0000 0.2778
-7.500 -0.3992 0.09071 0.08449 -0.0156 1.0000 0.2922
-7.250 -0.3965 0.08778 0.08165 -0.0150 1.0000 0.3070
-7.000 -0.3996 0.08533 0.07931 -0.0142 1.0000 0.3221
-6.750 -0.3704 0.08062 0.07456 -0.0120 1.0000 0.3460
-6.500 -0.3824 0.07916 0.07327 -0.0101 1.0000 0.3653
-6.250 -0.3770 0.07659 0.07076 -0.0070 1.0000 0.3945
-6.000 -0.3681 0.07382 0.06806 -0.0039 1.0000 0.4224
-5.750 -0.3646 0.07141 0.06574 -0.0002 1.0000 0.4493
-5.500 -0.4005 0.07190 0.06644 0.0063 1.0000 0.4701
-4.500 -0.4124 0.04612 0.03885 -0.0330 1.0000 0.1587
-4.250 -0.3917 0.04179 0.03368 -0.0340 1.0000 0.1456
-4.000 -0.3732 0.03872 0.03037 -0.0336 1.0000 0.1432
-3.750 -0.3520 0.03606 0.02714 -0.0335 1.0000 0.1438
-3.500 -0.3312 0.03390 0.02466 -0.0332 1.0000 0.1492
-3.250 -0.3085 0.03198 0.02239 -0.0328 1.0000 0.1534
-3.000 -0.2842 0.03033 0.02016 -0.0324 1.0000 0.1599
-2.750 -0.2629 0.02905 0.01877 -0.0319 1.0000 0.1731
-2.500 -0.2405 0.02776 0.01734 -0.0313 1.0000 0.1851
-2.250 -0.2184 0.02676 0.01623 -0.0307 1.0000 0.2072
-2.000 -0.1964 0.02583 0.01527 -0.0298 1.0000 0.2345
-1.750 -0.1735 0.02487 0.01456 -0.0294 1.0000 0.2848
-1.500 -0.1498 0.02292 0.01378 -0.0288 1.0000 0.4418
-1.250 -0.1246 0.02116 0.01332 -0.0262 1.0000 1.0000
-1.000 -0.0972 0.02174 0.01336 -0.0275 0.9965 1.0000
-0.750 -0.0540 0.02266 0.01380 -0.0317 0.9862 1.0000
-0.500 -0.0143 0.02354 0.01430 -0.0352 0.9759 1.0000
-0.250 0.0244 0.02443 0.01486 -0.0385 0.9655 1.0000
0.000 0.0643 0.02537 0.01554 -0.0419 0.9551 1.0000
0.250 0.1007 0.02624 0.01619 -0.0447 0.9444 1.0000
0.500 0.1316 0.02704 0.01681 -0.0465 0.9334 1.0000
0.750 0.1642 0.02791 0.01752 -0.0485 0.9226 1.0000
1.000 0.1996 0.02884 0.01833 -0.0509 0.9121 1.0000
1.250 0.2336 0.02975 0.01912 -0.0530 0.9011 1.0000
1.500 0.2574 0.03058 0.01988 -0.0535 0.8900 1.0000
1.750 0.2853 0.03149 0.02073 -0.0546 0.8790 1.0000
2.000 0.3169 0.03246 0.02166 -0.0562 0.8683 1.0000
2.250 0.3509 0.03343 0.02259 -0.0581 0.8573 1.0000
2.500 0.3706 0.03437 0.02351 -0.0578 0.8456 1.0000
2.750 0.3939 0.03536 0.02451 -0.0581 0.8340 1.0000
3.000 0.4205 0.03639 0.02556 -0.0588 0.8225 1.0000
3.250 0.4517 0.03740 0.02661 -0.0600 0.8109 1.0000
3.500 0.4822 0.03840 0.02766 -0.0611 0.7992 1.0000
3.750 0.5007 0.03949 0.02882 -0.0606 0.7865 1.0000
4.000 0.5202 0.04063 0.03002 -0.0603 0.7740 1.0000
4.250 0.5422 0.04178 0.03124 -0.0603 0.7613 1.0000
4.500 0.5660 0.04292 0.03246 -0.0604 0.7483 1.0000
4.750 0.5906 0.04403 0.03367 -0.0605 0.7351 1.0000
5.000 0.6151 0.04512 0.03492 -0.0605 0.7211 1.0000
5.250 0.6391 0.04619 0.03612 -0.0603 0.7064 1.0000
5.500 0.6622 0.04727 0.03734 -0.0600 0.6913 1.0000
5.750 0.6852 0.04836 0.03858 -0.0596 0.6761 1.0000
6.000 0.7091 0.04936 0.03978 -0.0592 0.6600 1.0000
6.250 0.7366 0.05014 0.04077 -0.0588 0.6434 1.0000
6.500 0.7758 0.05016 0.04107 -0.0586 0.6262 1.0000
6.750 0.8022 0.05061 0.04180 -0.0575 0.6073 1.0000
7.000 0.8290 0.05069 0.04214 -0.0559 0.5861 1.0000
7.250 0.9589 0.03817 0.03045 -0.0506 0.5520 1.0000
7.500 1.0095 0.03213 0.02466 -0.0448 0.5073 1.0000
7.750 1.0324 0.02904 0.02167 -0.0392 0.4458 1.0000
8.000 1.0301 0.02850 0.02042 -0.0321 0.3294 1.0000
8.250 1.0178 0.03127 0.02201 -0.0269 0.2339 1.0000
8.500 1.0213 0.03416 0.02421 -0.0239 0.1844 1.0000
8.750 1.0397 0.03676 0.02649 -0.0223 0.1519 1.0000
9.000 1.0728 0.03951 0.02905 -0.0220 0.1300 1.0000
9.250 1.1066 0.04264 0.03210 -0.0221 0.1155 1.0000
9.500 1.1299 0.04595 0.03587 -0.0211 0.1090 1.0000
9.750 1.1570 0.04973 0.03961 -0.0212 0.1013 1.0000
10.000 1.1642 0.05299 0.04351 -0.0191 0.0989 1.0000
10.250 1.1708 0.05694 0.04797 -0.0173 0.0978 1.0000
10.500 1.1718 0.06107 0.05256 -0.0155 0.0976 1.0000
10.750 1.1671 0.06527 0.05716 -0.0137 0.0977 1.0000
11.000 1.1567 0.06946 0.06170 -0.0119 0.0979 1.0000
11.250 1.1409 0.07353 0.06604 -0.0100 0.0984 1.0000
11.500 1.1214 0.07780 0.07052 -0.0088 0.0991 1.0000
11.750 1.1015 0.08253 0.07543 -0.0086 0.0998 1.0000
12.000 1.0831 0.08789 0.08092 -0.0093 0.1006 1.0000
12.250 1.0711 0.09371 0.08683 -0.0104 0.1014 1.0000
12.500 0.9535 0.11041 0.10371 -0.0257 0.1106 1.0000
12.750 0.9391 0.11916 0.11245 -0.0300 0.1132 1.0000
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