FX 73-CL3-152 (fx73cl3152-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 73-CL3-152 (fx73cl3152-il) Reynolds number: 500,000 Max Cl/Cd: 100.64 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx73cl3152-il-500000-n5.txt Download as CSV file: xf-fx73cl3152-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 73-CL3-152
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.1391 0.09020 0.08673 -0.1235 0.8049 0.0220
-10.250 0.1462 0.08794 0.08443 -0.1240 0.7899 0.0221
-10.000 0.1506 0.08552 0.08189 -0.1242 0.7599 0.0221
-9.500 -0.1102 0.04108 0.03735 -0.1476 0.7838 0.0250
-9.250 -0.1326 0.02584 0.02152 -0.1711 0.7685 0.0252
-9.000 -0.1056 0.02195 0.01717 -0.1787 0.7399 0.0254
-8.750 -0.0835 0.02061 0.01551 -0.1800 0.6990 0.0257
-8.500 -0.0609 0.01983 0.01445 -0.1804 0.6637 0.0259
-8.250 -0.0371 0.01915 0.01354 -0.1808 0.6352 0.0262
-8.000 -0.0126 0.01858 0.01276 -0.1810 0.6108 0.0265
-7.750 0.0124 0.01801 0.01200 -0.1811 0.5900 0.0268
-7.500 0.0380 0.01749 0.01129 -0.1813 0.5721 0.0272
-7.250 0.0640 0.01696 0.01059 -0.1814 0.5575 0.0276
-7.000 0.0901 0.01648 0.00993 -0.1814 0.5450 0.0281
-6.750 0.1164 0.01605 0.00933 -0.1814 0.5331 0.0286
-6.500 0.1431 0.01565 0.00877 -0.1813 0.5230 0.0290
-6.250 0.1694 0.01526 0.00828 -0.1812 0.5133 0.0295
-6.000 0.1962 0.01498 0.00793 -0.1811 0.5051 0.0301
-5.750 0.2229 0.01476 0.00761 -0.1809 0.4967 0.0307
-5.500 0.2496 0.01453 0.00728 -0.1806 0.4894 0.0314
-5.250 0.2766 0.01428 0.00693 -0.1804 0.4824 0.0321
-5.000 0.3032 0.01406 0.00660 -0.1801 0.4757 0.0327
-4.750 0.3300 0.01382 0.00628 -0.1798 0.4706 0.0334
-4.500 0.3571 0.01360 0.00602 -0.1796 0.4657 0.0341
-4.250 0.3840 0.01345 0.00581 -0.1793 0.4609 0.0349
-4.000 0.4107 0.01333 0.00561 -0.1789 0.4564 0.0359
-3.750 0.4376 0.01321 0.00541 -0.1786 0.4527 0.0370
-3.500 0.4647 0.01304 0.00522 -0.1783 0.4492 0.0382
-3.250 0.4917 0.01294 0.00508 -0.1780 0.4455 0.0395
-3.000 0.5185 0.01285 0.00493 -0.1776 0.4417 0.0409
-2.750 0.5449 0.01280 0.00480 -0.1771 0.4379 0.0423
-2.500 0.5714 0.01271 0.00468 -0.1767 0.4347 0.0439
-2.250 0.5985 0.01264 0.00459 -0.1764 0.4322 0.0461
-2.000 0.6254 0.01257 0.00450 -0.1760 0.4296 0.0483
-1.750 0.6522 0.01251 0.00442 -0.1756 0.4270 0.0511
-1.500 0.6787 0.01248 0.00436 -0.1752 0.4244 0.0541
-1.250 0.7050 0.01246 0.00431 -0.1747 0.4218 0.0579
-1.000 0.7309 0.01246 0.00429 -0.1742 0.4191 0.0631
-0.750 0.7569 0.01246 0.00428 -0.1736 0.4165 0.0701
-0.500 0.7837 0.01242 0.00427 -0.1733 0.4146 0.0800
-0.250 0.8101 0.01240 0.00428 -0.1728 0.4126 0.0937
0.000 0.8364 0.01239 0.00431 -0.1724 0.4106 0.1107
0.250 0.8625 0.01240 0.00435 -0.1719 0.4084 0.1277
0.500 0.8883 0.01244 0.00441 -0.1714 0.4061 0.1437
0.750 0.9138 0.01250 0.00447 -0.1708 0.4038 0.1595
1.000 0.9390 0.01257 0.00455 -0.1702 0.4014 0.1754
1.250 0.9639 0.01267 0.00466 -0.1695 0.3991 0.1917
1.500 0.9898 0.01271 0.00474 -0.1690 0.3974 0.2082
1.750 1.0156 0.01276 0.00484 -0.1685 0.3954 0.2266
2.000 1.0410 0.01281 0.00494 -0.1679 0.3934 0.2479
2.250 1.0662 0.01288 0.00505 -0.1673 0.3912 0.2649
2.500 1.0910 0.01297 0.00516 -0.1666 0.3890 0.2814
2.750 1.1154 0.01308 0.00528 -0.1659 0.3869 0.3002
3.000 1.1393 0.01319 0.00541 -0.1651 0.3848 0.3201
3.250 1.1628 0.01333 0.00557 -0.1642 0.3826 0.3416
3.500 1.1862 0.01346 0.00574 -0.1633 0.3808 0.3651
3.750 1.2100 0.01353 0.00588 -0.1624 0.3794 0.3907
4.000 1.2333 0.01362 0.00604 -0.1615 0.3777 0.4165
4.250 1.2562 0.01371 0.00620 -0.1605 0.3760 0.4452
4.500 1.2788 0.01382 0.00639 -0.1595 0.3739 0.4766
4.750 1.3010 0.01394 0.00659 -0.1584 0.3718 0.5119
5.000 1.3226 0.01408 0.00679 -0.1572 0.3696 0.5480
5.250 1.3438 0.01424 0.00702 -0.1560 0.3675 0.5857
5.500 1.3648 0.01442 0.00726 -0.1548 0.3656 0.6224
5.750 1.3861 0.01461 0.00752 -0.1536 0.3638 0.6646
6.000 1.4091 0.01471 0.00775 -0.1528 0.3622 0.7138
6.500 1.5055 0.01496 0.00834 -0.1619 0.3577 1.0000
6.750 1.5287 0.01520 0.00859 -0.1612 0.3555 1.0000
7.000 1.5515 0.01546 0.00885 -0.1604 0.3534 1.0000
7.250 1.5736 0.01575 0.00912 -0.1596 0.3511 1.0000
7.500 1.5950 0.01608 0.00943 -0.1588 0.3488 1.0000
7.750 1.6170 0.01639 0.00975 -0.1580 0.3466 1.0000
8.000 1.6401 0.01665 0.01005 -0.1574 0.3446 1.0000
8.250 1.6626 0.01695 0.01038 -0.1567 0.3424 1.0000
8.500 1.6843 0.01727 0.01074 -0.1560 0.3400 1.0000
8.750 1.7055 0.01762 0.01110 -0.1552 0.3376 1.0000
9.000 1.7258 0.01802 0.01150 -0.1543 0.3353 1.0000
9.250 1.7453 0.01845 0.01195 -0.1533 0.3329 1.0000
9.500 1.7650 0.01889 0.01241 -0.1524 0.3307 1.0000
9.750 1.7860 0.01927 0.01284 -0.1516 0.3282 1.0000
10.000 1.8060 0.01969 0.01331 -0.1508 0.3254 1.0000
10.250 1.8251 0.02017 0.01382 -0.1498 0.3228 1.0000
10.500 1.8431 0.02070 0.01438 -0.1488 0.3202 1.0000
10.750 1.8601 0.02128 0.01498 -0.1477 0.3177 1.0000
11.000 1.8766 0.02191 0.01564 -0.1465 0.3154 1.0000
11.250 1.8952 0.02243 0.01623 -0.1456 0.3131 1.0000
11.500 1.9128 0.02301 0.01686 -0.1446 0.3103 1.0000
11.750 1.9287 0.02368 0.01759 -0.1434 0.3073 1.0000
12.000 1.9427 0.02447 0.01840 -0.1421 0.3040 1.0000
12.250 1.9543 0.02542 0.01935 -0.1406 0.3002 1.0000
12.500 1.9691 0.02619 0.02020 -0.1394 0.2954 1.0000
12.750 1.9797 0.02724 0.02127 -0.1379 0.2897 1.0000
13.000 1.9874 0.02850 0.02254 -0.1362 0.2848 1.0000
13.250 2.0002 0.02946 0.02357 -0.1350 0.2806 1.0000
13.500 2.0094 0.03069 0.02485 -0.1336 0.2763 1.0000
13.750 2.0165 0.03208 0.02628 -0.1320 0.2727 1.0000
14.000 2.0239 0.03351 0.02775 -0.1306 0.2696 1.0000
14.250 2.0333 0.03483 0.02916 -0.1294 0.2661 1.0000
14.500 2.0408 0.03635 0.03074 -0.1281 0.2627 1.0000
14.750 2.0437 0.03829 0.03273 -0.1267 0.2588 1.0000
15.000 2.0455 0.04041 0.03490 -0.1253 0.2554 1.0000
15.250 2.0520 0.04217 0.03676 -0.1243 0.2521 1.0000
15.500 2.0535 0.04448 0.03914 -0.1232 0.2475 1.0000
15.750 2.0483 0.04754 0.04224 -0.1220 0.2427 1.0000
16.000 2.0465 0.05033 0.04511 -0.1210 0.2376 1.0000
16.250 2.0413 0.05358 0.04843 -0.1202 0.2322 1.0000
16.500 2.0280 0.05781 0.05270 -0.1193 0.2269 1.0000
16.750 2.0231 0.06115 0.05614 -0.1187 0.2214 1.0000
17.000 2.0095 0.06556 0.06062 -0.1181 0.2158 1.0000
17.250 1.9953 0.07010 0.06523 -0.1176 0.2106 1.0000
17.500 1.9787 0.07503 0.07023 -0.1173 0.2035 1.0000
17.750 1.9568 0.08065 0.07592 -0.1171 0.1975 1.0000
18.000 1.9362 0.08621 0.08154 -0.1171 0.1900 1.0000
18.250 1.9108 0.09247 0.08784 -0.1172 0.1826 1.0000
18.500 1.8826 0.09915 0.09455 -0.1176 0.1738 1.0000
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