FX 84-W-097 (fx84w097-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 84-W-097 (fx84w097-il) Reynolds number: 500,000 Max Cl/Cd: 104.34 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx84w097-il-500000.txt Download as CSV file: xf-fx84w097-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4479 0.10225 0.10004 -0.0182 1.0000 0.0216
-9.750 -0.4459 0.09780 0.09560 -0.0206 1.0000 0.0217
-9.500 -0.4560 0.09109 0.08894 -0.0230 1.0000 0.0223
-9.250 -0.4518 0.08787 0.08574 -0.0243 1.0000 0.0226
-9.000 -0.4446 0.08551 0.08339 -0.0250 1.0000 0.0231
-8.750 -0.4413 0.08216 0.08007 -0.0267 1.0000 0.0235
-8.500 -0.4404 0.07842 0.07636 -0.0290 1.0000 0.0238
-8.250 -0.4413 0.07452 0.07251 -0.0317 1.0000 0.0243
-8.000 -0.4477 0.06999 0.06804 -0.0359 1.0000 0.0245
-7.750 -0.4373 0.06293 0.06094 -0.0464 0.9727 0.0251
-7.500 -0.4262 0.05563 0.05346 -0.0545 0.9421 0.0260
-7.250 -0.4582 0.03790 0.03493 -0.0589 0.9124 0.0230
-7.000 -0.4592 0.02970 0.02610 -0.0579 0.8987 0.0191
-6.750 -0.4540 0.02190 0.01725 -0.0561 0.8873 0.0183
-6.500 -0.4327 0.01980 0.01478 -0.0554 0.8780 0.0188
-6.250 -0.4099 0.01825 0.01292 -0.0546 0.8698 0.0195
-6.000 -0.3854 0.01698 0.01139 -0.0540 0.8611 0.0204
-5.750 -0.3602 0.01603 0.01022 -0.0534 0.8534 0.0212
-5.500 -0.3358 0.01459 0.00853 -0.0529 0.8453 0.0224
-5.250 -0.3103 0.01382 0.00769 -0.0526 0.8374 0.0243
-5.000 -0.2841 0.01335 0.00713 -0.0522 0.8297 0.0260
-4.750 -0.2574 0.01279 0.00647 -0.0519 0.8219 0.0277
-4.500 -0.2305 0.01246 0.00602 -0.0516 0.8146 0.0289
-4.250 -0.2052 0.01145 0.00494 -0.0512 0.8069 0.0326
-4.000 -0.1783 0.01114 0.00457 -0.0510 0.7999 0.0358
-3.750 -0.1507 0.01088 0.00424 -0.0508 0.7923 0.0382
-3.500 -0.1245 0.01028 0.00359 -0.0505 0.7854 0.0445
-3.250 -0.0968 0.01005 0.00331 -0.0504 0.7779 0.0501
-3.000 -0.0697 0.00970 0.00294 -0.0502 0.7709 0.0603
-2.750 -0.0421 0.00942 0.00267 -0.0502 0.7636 0.0747
-2.500 -0.0149 0.00912 0.00244 -0.0501 0.7565 0.0994
-2.250 0.0126 0.00884 0.00226 -0.0501 0.7491 0.1353
-2.000 0.0397 0.00854 0.00212 -0.0500 0.7419 0.1900
-1.750 0.0667 0.00816 0.00200 -0.0501 0.7345 0.2677
-1.500 0.0928 0.00764 0.00188 -0.0500 0.7273 0.3991
-1.250 0.1172 0.00692 0.00182 -0.0496 0.7199 0.5962
-1.000 0.1401 0.00644 0.00184 -0.0484 0.7129 0.7571
-0.750 0.1636 0.00626 0.00189 -0.0470 0.7056 0.8408
-0.500 0.1873 0.00621 0.00189 -0.0456 0.6987 0.8890
-0.250 0.2118 0.00620 0.00189 -0.0445 0.6915 0.9246
0.000 0.2402 0.00621 0.00187 -0.0442 0.6844 0.9516
0.250 0.2757 0.00623 0.00184 -0.0455 0.6770 0.9722
0.500 0.3158 0.00626 0.00179 -0.0480 0.6696 0.9847
0.750 0.3598 0.00628 0.00176 -0.0515 0.6615 0.9934
1.000 0.4009 0.00631 0.00171 -0.0544 0.6538 1.0000
1.250 0.4251 0.00634 0.00171 -0.0537 0.6452 1.0000
1.500 0.4495 0.00641 0.00171 -0.0531 0.6378 1.0000
1.750 0.4745 0.00646 0.00174 -0.0525 0.6293 1.0000
2.000 0.4996 0.00654 0.00178 -0.0520 0.6217 1.0000
2.250 0.5252 0.00661 0.00182 -0.0516 0.6134 1.0000
2.500 0.5512 0.00669 0.00188 -0.0512 0.6051 1.0000
2.750 0.5773 0.00679 0.00193 -0.0509 0.5960 1.0000
3.000 0.6039 0.00686 0.00200 -0.0507 0.5857 1.0000
3.250 0.6307 0.00696 0.00208 -0.0504 0.5767 1.0000
3.500 0.6574 0.00708 0.00217 -0.0503 0.5675 1.0000
3.750 0.6845 0.00717 0.00228 -0.0501 0.5570 1.0000
4.000 0.7116 0.00728 0.00239 -0.0500 0.5468 1.0000
4.250 0.7384 0.00741 0.00250 -0.0498 0.5356 1.0000
4.500 0.7651 0.00754 0.00261 -0.0496 0.5170 1.0000
4.750 0.7912 0.00772 0.00272 -0.0494 0.4950 1.0000
5.000 0.8178 0.00788 0.00287 -0.0492 0.4751 1.0000
5.250 0.8441 0.00809 0.00303 -0.0490 0.4547 1.0000
5.500 0.8700 0.00834 0.00324 -0.0488 0.4297 1.0000
5.750 0.8953 0.00866 0.00347 -0.0485 0.3988 1.0000
6.000 0.9196 0.00909 0.00375 -0.0481 0.3590 1.0000
6.250 0.9424 0.00970 0.00413 -0.0476 0.3052 1.0000
6.500 0.9628 0.01059 0.00467 -0.0468 0.2349 1.0000
6.750 0.9811 0.01172 0.00537 -0.0459 0.1561 1.0000
7.000 0.9983 0.01293 0.00618 -0.0448 0.0870 1.0000
7.250 1.0175 0.01388 0.00691 -0.0439 0.0532 1.0000
7.500 1.0382 0.01464 0.00761 -0.0430 0.0390 1.0000
7.750 1.0575 0.01551 0.00848 -0.0419 0.0307 1.0000
8.000 1.0792 0.01607 0.00911 -0.0412 0.0272 1.0000
8.250 1.0959 0.01708 0.01014 -0.0398 0.0236 1.0000
8.500 1.1140 0.01788 0.01103 -0.0385 0.0217 1.0000
8.750 1.1329 0.01854 0.01175 -0.0375 0.0200 1.0000
9.000 1.1497 0.01933 0.01259 -0.0361 0.0186 1.0000
9.250 1.1585 0.02068 0.01399 -0.0338 0.0173 1.0000
9.500 1.1629 0.02209 0.01552 -0.0308 0.0166 1.0000
9.750 1.1737 0.02301 0.01652 -0.0287 0.0162 1.0000
10.000 1.1836 0.02407 0.01766 -0.0267 0.0157 1.0000
10.250 1.1933 0.02525 0.01893 -0.0248 0.0152 1.0000
10.500 1.2034 0.02646 0.02023 -0.0231 0.0146 1.0000
10.750 1.2145 0.02755 0.02137 -0.0218 0.0139 1.0000
11.000 1.2240 0.02886 0.02275 -0.0205 0.0134 1.0000
11.250 1.2311 0.03049 0.02443 -0.0191 0.0127 1.0000
11.500 1.2373 0.03278 0.02683 -0.0174 0.0124 1.0000
11.750 1.2447 0.03532 0.02955 -0.0160 0.0120 1.0000
12.000 1.2526 0.03694 0.03132 -0.0149 0.0118 1.0000
12.250 1.2594 0.03898 0.03352 -0.0138 0.0116 1.0000
12.500 1.2646 0.04107 0.03578 -0.0128 0.0114 1.0000
12.750 1.2671 0.04370 0.03859 -0.0118 0.0112 1.0000
13.000 1.2674 0.04654 0.04163 -0.0111 0.0110 1.0000
13.250 1.2654 0.04958 0.04487 -0.0105 0.0108 1.0000
13.500 1.2599 0.05320 0.04870 -0.0103 0.0107 1.0000
13.750 1.2529 0.05699 0.05269 -0.0104 0.0106 1.0000
14.000 1.2436 0.06124 0.05716 -0.0110 0.0105 1.0000
14.250 1.2282 0.06659 0.06276 -0.0122 0.0105 1.0000
14.500 1.2203 0.07080 0.06710 -0.0136 0.0103 1.0000
14.750 1.2026 0.07695 0.07348 -0.0159 0.0104 1.0000
15.000 1.1815 0.08422 0.08097 -0.0192 0.0104 1.0000
15.250 1.1630 0.09145 0.08838 -0.0230 0.0104 1.0000
15.500 1.1335 0.10161 0.09877 -0.0287 0.0106 1.0000
15.750 1.1127 0.11060 0.10793 -0.0342 0.0106 1.0000
16.000 1.0891 0.12100 0.11850 -0.0408 0.0107 1.0000
16.250 1.0537 0.13559 0.13328 -0.0502 0.0113 1.0000
16.500 1.0178 0.15196 0.14977 -0.0603 0.0117 1.0000
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Polar data table (+)
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