FX 84-W-097 (fx84w097-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 84-W-097 (fx84w097-il) Reynolds number: 200,000 Max Cl/Cd: 73.46 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx84w097-il-200000-n5.txt Download as CSV file: xf-fx84w097-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4499 0.08867 0.08524 -0.0235 1.0000 0.0178
-9.000 -0.4543 0.08320 0.07982 -0.0268 1.0000 0.0175
-8.750 -0.4621 0.07717 0.07386 -0.0307 1.0000 0.0172
-8.500 -0.4890 0.06711 0.06394 -0.0390 1.0000 0.0165
-8.250 -0.5147 0.05274 0.04940 -0.0499 1.0000 0.0161
-8.000 -0.5217 0.04083 0.03690 -0.0575 0.9689 0.0161
-7.750 -0.5126 0.03370 0.02905 -0.0607 0.9473 0.0163
-7.500 -0.4947 0.03063 0.02561 -0.0614 0.9325 0.0168
-7.250 -0.4759 0.02835 0.02298 -0.0612 0.9192 0.0172
-7.000 -0.4560 0.02654 0.02085 -0.0607 0.9075 0.0180
-6.750 -0.4347 0.02511 0.01910 -0.0602 0.8969 0.0193
-6.500 -0.4138 0.02323 0.01677 -0.0593 0.8869 0.0206
-6.250 -0.3915 0.02149 0.01459 -0.0585 0.8772 0.0214
-6.000 -0.3691 0.01984 0.01266 -0.0577 0.8686 0.0223
-5.750 -0.3452 0.01886 0.01155 -0.0572 0.8599 0.0235
-5.500 -0.3205 0.01813 0.01069 -0.0567 0.8515 0.0250
-5.250 -0.2954 0.01748 0.00983 -0.0561 0.8436 0.0274
-5.000 -0.2697 0.01674 0.00890 -0.0556 0.8354 0.0290
-4.750 -0.2456 0.01576 0.00785 -0.0550 0.8281 0.0311
-4.500 -0.2196 0.01522 0.00725 -0.0546 0.8197 0.0338
-4.250 -0.1938 0.01480 0.00668 -0.0541 0.8128 0.0375
-4.000 -0.1681 0.01416 0.00600 -0.0538 0.8044 0.0412
-3.750 -0.1420 0.01376 0.00552 -0.0534 0.7975 0.0460
-3.500 -0.1156 0.01335 0.00507 -0.0531 0.7892 0.0528
-3.250 -0.0892 0.01302 0.00464 -0.0528 0.7823 0.0609
-3.000 -0.0625 0.01267 0.00430 -0.0526 0.7743 0.0730
-2.750 -0.0359 0.01237 0.00400 -0.0523 0.7675 0.0893
-2.500 -0.0091 0.01206 0.00375 -0.0522 0.7598 0.1137
-2.250 0.0175 0.01176 0.00352 -0.0520 0.7530 0.1475
-2.000 0.0441 0.01142 0.00334 -0.0519 0.7453 0.1975
-1.750 0.0701 0.01103 0.00317 -0.0517 0.7385 0.2702
-1.500 0.0955 0.01051 0.00304 -0.0515 0.7307 0.3851
-1.250 0.1182 0.00982 0.00296 -0.0506 0.7240 0.5621
-1.000 0.1391 0.00932 0.00302 -0.0487 0.7163 0.7257
-0.750 0.1614 0.00915 0.00305 -0.0468 0.7096 0.8227
-0.500 0.1875 0.00910 0.00304 -0.0457 0.7017 0.8838
-0.250 0.2189 0.00909 0.00298 -0.0460 0.6947 0.9244
0.000 0.2561 0.00908 0.00291 -0.0476 0.6867 0.9546
0.250 0.2984 0.00908 0.00281 -0.0505 0.6794 0.9782
0.500 0.3470 0.00906 0.00271 -0.0549 0.6713 1.0000
0.750 0.3713 0.00912 0.00269 -0.0542 0.6638 1.0000
1.000 0.3958 0.00918 0.00268 -0.0536 0.6561 1.0000
1.250 0.4205 0.00926 0.00270 -0.0531 0.6484 1.0000
1.500 0.4455 0.00934 0.00272 -0.0525 0.6408 1.0000
1.750 0.4709 0.00943 0.00278 -0.0521 0.6326 1.0000
2.000 0.4963 0.00953 0.00281 -0.0516 0.6249 1.0000
2.250 0.5223 0.00962 0.00289 -0.0512 0.6158 1.0000
2.500 0.5482 0.00973 0.00296 -0.0509 0.6076 1.0000
2.750 0.5744 0.00984 0.00307 -0.0506 0.5986 1.0000
3.000 0.6007 0.00996 0.00318 -0.0503 0.5898 1.0000
3.250 0.6270 0.01009 0.00328 -0.0500 0.5814 1.0000
3.500 0.6535 0.01022 0.00344 -0.0497 0.5712 1.0000
3.750 0.6798 0.01035 0.00358 -0.0495 0.5602 1.0000
4.000 0.7061 0.01050 0.00372 -0.0492 0.5492 1.0000
4.250 0.7324 0.01066 0.00388 -0.0489 0.5385 1.0000
4.500 0.7588 0.01082 0.00410 -0.0486 0.5268 1.0000
4.750 0.7850 0.01099 0.00430 -0.0484 0.5142 1.0000
5.000 0.8109 0.01117 0.00450 -0.0480 0.4993 1.0000
5.250 0.8357 0.01139 0.00468 -0.0475 0.4731 1.0000
5.500 0.8595 0.01170 0.00489 -0.0469 0.4389 1.0000
5.750 0.8833 0.01205 0.00516 -0.0463 0.4049 1.0000
6.000 0.9062 0.01250 0.00548 -0.0456 0.3673 1.0000
6.250 0.9279 0.01308 0.00589 -0.0449 0.3212 1.0000
6.500 0.9469 0.01392 0.00646 -0.0439 0.2596 1.0000
6.750 0.9638 0.01502 0.00719 -0.0428 0.1910 1.0000
7.000 0.9792 0.01626 0.00806 -0.0415 0.1243 1.0000
7.250 0.9953 0.01741 0.00895 -0.0403 0.0807 1.0000
7.500 1.0128 0.01837 0.00980 -0.0392 0.0580 1.0000
7.750 1.0309 0.01924 0.01065 -0.0381 0.0457 1.0000
8.000 1.0483 0.02012 0.01156 -0.0369 0.0378 1.0000
8.250 1.0648 0.02103 0.01250 -0.0356 0.0325 1.0000
8.500 1.0800 0.02199 0.01354 -0.0342 0.0289 1.0000
8.750 1.0951 0.02289 0.01453 -0.0328 0.0260 1.0000
9.000 1.1061 0.02401 0.01568 -0.0309 0.0235 1.0000
9.250 1.1147 0.02510 0.01687 -0.0287 0.0220 1.0000
9.500 1.1234 0.02625 0.01815 -0.0266 0.0207 1.0000
9.750 1.1316 0.02750 0.01951 -0.0247 0.0197 1.0000
10.000 1.1397 0.02884 0.02093 -0.0230 0.0188 1.0000
10.250 1.1473 0.03031 0.02248 -0.0215 0.0180 1.0000
10.500 1.1529 0.03203 0.02425 -0.0200 0.0173 1.0000
10.750 1.1589 0.03390 0.02619 -0.0185 0.0166 1.0000
11.000 1.1690 0.03539 0.02784 -0.0175 0.0158 1.0000
11.250 1.1781 0.03700 0.02959 -0.0165 0.0149 1.0000
11.500 1.1860 0.03885 0.03159 -0.0155 0.0144 1.0000
11.750 1.1935 0.04078 0.03365 -0.0146 0.0139 1.0000
12.000 1.2003 0.04280 0.03580 -0.0138 0.0135 1.0000
12.250 1.2063 0.04495 0.03806 -0.0131 0.0132 1.0000
12.500 1.2113 0.04726 0.04051 -0.0125 0.0129 1.0000
12.750 1.2144 0.04982 0.04318 -0.0121 0.0125 1.0000
13.000 1.2161 0.05279 0.04629 -0.0116 0.0123 1.0000
13.250 1.2154 0.05611 0.04982 -0.0114 0.0120 1.0000
13.500 1.2129 0.05953 0.05349 -0.0115 0.0118 1.0000
13.750 1.2081 0.06329 0.05750 -0.0120 0.0116 1.0000
14.000 1.2013 0.06746 0.06191 -0.0129 0.0114 1.0000
14.250 1.1918 0.07214 0.06684 -0.0142 0.0112 1.0000
14.500 1.1808 0.07724 0.07217 -0.0160 0.0110 1.0000
14.750 1.1670 0.08315 0.07832 -0.0184 0.0110 1.0000
15.000 1.1538 0.08921 0.08460 -0.0214 0.0108 1.0000
15.250 1.1374 0.09630 0.09190 -0.0252 0.0108 1.0000
15.500 1.1192 0.10427 0.10010 -0.0297 0.0107 1.0000
15.750 1.0992 0.11314 0.10917 -0.0350 0.0108 1.0000
16.000 1.0769 0.12327 0.11949 -0.0413 0.0109 1.0000
16.250 1.0512 0.13521 0.13161 -0.0489 0.0112 1.0000
16.500 1.0244 0.14857 0.14511 -0.0572 0.0116 1.0000
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