USA 48 AIRFOIL (usa48-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 48 AIRFOIL (usa48-il) Reynolds number: 200,000 Max Cl/Cd: 63.16 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa48-il-200000-n5.txt Download as CSV file: xf-usa48-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 48 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6195 0.08328 0.07927 -0.0634 1.0000 0.0184
-13.500 -0.6684 0.07127 0.06705 -0.0707 1.0000 0.0181
-13.250 -0.7013 0.06320 0.05880 -0.0753 1.0000 0.0180
-13.000 -0.7268 0.05723 0.05264 -0.0781 1.0000 0.0180
-12.750 -0.7494 0.05252 0.04776 -0.0792 1.0000 0.0180
-12.500 -0.7695 0.04880 0.04387 -0.0790 1.0000 0.0182
-12.250 -0.7886 0.04569 0.04060 -0.0777 1.0000 0.0184
-12.000 -0.8074 0.04311 0.03786 -0.0754 1.0000 0.0185
-11.750 -0.8271 0.04104 0.03564 -0.0719 1.0000 0.0187
-11.500 -0.8480 0.03951 0.03398 -0.0668 1.0000 0.0189
-11.250 -0.8613 0.03769 0.03194 -0.0625 0.9990 0.0192
-11.000 -0.8476 0.03510 0.02899 -0.0633 0.9949 0.0199
-10.750 -0.8254 0.03436 0.02823 -0.0642 0.9911 0.0206
-10.500 -0.8022 0.03335 0.02711 -0.0652 0.9872 0.0213
-10.250 -0.7784 0.03208 0.02566 -0.0662 0.9838 0.0225
-10.000 -0.7602 0.03035 0.02361 -0.0659 0.9788 0.0240
-9.750 -0.7346 0.02921 0.02236 -0.0669 0.9753 0.0249
-9.500 -0.7111 0.02840 0.02147 -0.0671 0.9707 0.0259
-9.250 -0.6868 0.02749 0.02042 -0.0674 0.9660 0.0272
-9.000 -0.6582 0.02644 0.01911 -0.0683 0.9629 0.0296
-8.750 -0.6366 0.02571 0.01837 -0.0679 0.9571 0.0307
-8.500 -0.6092 0.02497 0.01754 -0.0685 0.9524 0.0326
-8.250 -0.5761 0.02412 0.01647 -0.0701 0.9493 0.0350
-8.000 -0.5549 0.02325 0.01559 -0.0693 0.9412 0.0367
-7.750 -0.5234 0.02241 0.01470 -0.0706 0.9368 0.0388
-7.500 -0.4952 0.02174 0.01390 -0.0710 0.9314 0.0412
-7.250 -0.4709 0.02095 0.01304 -0.0706 0.9249 0.0431
-7.000 -0.4417 0.01998 0.01209 -0.0715 0.9212 0.0453
-6.750 -0.4162 0.01929 0.01136 -0.0713 0.9153 0.0476
-6.500 -0.3898 0.01871 0.01068 -0.0712 0.9088 0.0496
-6.250 -0.3595 0.01779 0.00973 -0.0722 0.9048 0.0519
-6.000 -0.3368 0.01712 0.00903 -0.0715 0.8968 0.0539
-5.750 -0.3067 0.01653 0.00837 -0.0722 0.8910 0.0557
-5.500 -0.2694 0.01597 0.00770 -0.0743 0.8873 0.0581
-5.250 -0.2473 0.01554 0.00721 -0.0733 0.8768 0.0604
-5.000 -0.2100 0.01501 0.00663 -0.0754 0.8719 0.0636
-4.750 -0.1844 0.01466 0.00624 -0.0750 0.8617 0.0669
-4.500 -0.1487 0.01409 0.00580 -0.0769 0.8552 0.0914
-4.250 -0.1225 0.01376 0.00547 -0.0766 0.8440 0.1136
-4.000 -0.0958 0.01305 0.00510 -0.0768 0.8342 0.1854
-3.750 -0.0631 0.01278 0.00484 -0.0779 0.8246 0.2158
-3.500 -0.0343 0.01257 0.00464 -0.0781 0.8131 0.2350
-3.250 -0.0039 0.01235 0.00442 -0.0787 0.8018 0.2563
-3.000 0.0272 0.01214 0.00422 -0.0794 0.7912 0.2805
-2.750 0.0545 0.01195 0.00409 -0.0793 0.7796 0.3090
-2.500 0.0823 0.01181 0.00395 -0.0793 0.7684 0.3344
-2.250 0.1109 0.01171 0.00382 -0.0795 0.7570 0.3552
-2.000 0.1382 0.01162 0.00371 -0.0794 0.7448 0.3780
-1.750 0.1632 0.01152 0.00362 -0.0788 0.7320 0.4033
-1.500 0.1878 0.01142 0.00355 -0.0781 0.7191 0.4306
-1.250 0.2121 0.01132 0.00348 -0.0773 0.7069 0.4600
-1.000 0.2339 0.01115 0.00346 -0.0760 0.6946 0.5098
-0.750 0.2515 0.01104 0.00373 -0.0736 0.6812 0.6022
-0.500 0.2744 0.01114 0.00380 -0.0724 0.6680 0.6480
-0.250 0.2985 0.01124 0.00381 -0.0715 0.6557 0.6668
0.000 0.3228 0.01133 0.00383 -0.0706 0.6442 0.6807
0.250 0.3464 0.01139 0.00386 -0.0697 0.6326 0.6927
0.500 0.3702 0.01146 0.00388 -0.0687 0.6213 0.7037
0.750 0.3939 0.01155 0.00389 -0.0678 0.6098 0.7138
1.000 0.4171 0.01161 0.00391 -0.0667 0.5968 0.7214
1.250 0.4399 0.01169 0.00394 -0.0656 0.5842 0.7323
1.500 0.4628 0.01174 0.00399 -0.0645 0.5729 0.7428
1.750 0.4854 0.01180 0.00404 -0.0633 0.5631 0.7564
2.000 0.5075 0.01185 0.00410 -0.0620 0.5517 0.7701
2.250 0.5300 0.01191 0.00416 -0.0609 0.5413 0.7822
2.500 0.5525 0.01198 0.00423 -0.0597 0.5302 0.7924
2.750 0.5758 0.01205 0.00430 -0.0588 0.5197 0.8007
3.000 0.5990 0.01214 0.00440 -0.0579 0.5085 0.8083
3.250 0.6224 0.01225 0.00449 -0.0570 0.4979 0.8159
3.500 0.6461 0.01234 0.00461 -0.0562 0.4860 0.8256
3.750 0.6713 0.01244 0.00476 -0.0557 0.4746 0.8367
4.000 0.6976 0.01258 0.00492 -0.0555 0.4614 0.8503
4.250 0.7275 0.01274 0.00514 -0.0561 0.4467 0.8713
4.500 0.7666 0.01296 0.00542 -0.0586 0.4307 0.9004
4.750 0.8095 0.01324 0.00570 -0.0622 0.4132 0.9366
5.000 0.8468 0.01353 0.00597 -0.0646 0.3963 0.9780
5.250 0.8754 0.01386 0.00625 -0.0652 0.3815 1.0000
5.500 0.8906 0.01411 0.00645 -0.0629 0.3692 1.0000
5.750 0.9042 0.01440 0.00668 -0.0602 0.3549 1.0000
6.000 0.9170 0.01471 0.00692 -0.0575 0.3404 1.0000
6.250 0.9315 0.01501 0.00719 -0.0550 0.3277 1.0000
6.500 0.9472 0.01531 0.00748 -0.0529 0.3173 1.0000
6.750 0.9615 0.01567 0.00781 -0.0505 0.3046 1.0000
7.000 0.9757 0.01606 0.00816 -0.0482 0.2916 1.0000
7.250 0.9912 0.01643 0.00852 -0.0461 0.2797 1.0000
7.500 1.0068 0.01682 0.00891 -0.0441 0.2677 1.0000
7.750 1.0207 0.01728 0.00936 -0.0419 0.2529 1.0000
8.000 1.0329 0.01782 0.00984 -0.0395 0.2344 1.0000
8.250 1.0429 0.01848 0.01041 -0.0368 0.2123 1.0000
8.500 1.0517 0.01923 0.01105 -0.0340 0.1876 1.0000
8.750 1.0602 0.02004 0.01175 -0.0314 0.1681 1.0000
9.000 1.0703 0.02081 0.01247 -0.0290 0.1568 1.0000
9.250 1.0805 0.02160 0.01324 -0.0268 0.1485 1.0000
9.500 1.0902 0.02244 0.01407 -0.0246 0.1419 1.0000
9.750 1.1001 0.02330 0.01494 -0.0225 0.1357 1.0000
10.000 1.1077 0.02431 0.01595 -0.0203 0.1304 1.0000
10.250 1.1192 0.02515 0.01686 -0.0186 0.1255 1.0000
10.500 1.1288 0.02612 0.01789 -0.0168 0.1206 1.0000
10.750 1.1356 0.02730 0.01910 -0.0149 0.1159 1.0000
11.000 1.1466 0.02827 0.02015 -0.0134 0.1111 1.0000
11.250 1.1573 0.02929 0.02125 -0.0121 0.1043 1.0000
11.500 1.1680 0.03035 0.02239 -0.0108 0.0950 1.0000
11.750 1.1714 0.03199 0.02385 -0.0092 0.0568 1.0000
12.000 1.1660 0.03439 0.02616 -0.0072 0.0462 1.0000
12.250 1.1647 0.03659 0.02840 -0.0056 0.0407 1.0000
12.500 1.1665 0.03863 0.03052 -0.0044 0.0370 1.0000
12.750 1.1678 0.04079 0.03276 -0.0034 0.0340 1.0000
13.000 1.1667 0.04326 0.03531 -0.0024 0.0318 1.0000
13.250 1.1693 0.04546 0.03762 -0.0017 0.0296 1.0000
13.500 1.1704 0.04788 0.04015 -0.0012 0.0280 1.0000
13.750 1.1694 0.05059 0.04295 -0.0008 0.0265 1.0000
14.000 1.1651 0.05376 0.04622 -0.0006 0.0253 1.0000
14.250 1.1646 0.05663 0.04921 -0.0006 0.0242 1.0000
14.500 1.1627 0.05975 0.05246 -0.0007 0.0234 1.0000
14.750 1.1601 0.06303 0.05586 -0.0010 0.0225 1.0000
15.000 1.1564 0.06654 0.05948 -0.0014 0.0219 1.0000
15.250 1.1521 0.07021 0.06326 -0.0021 0.0212 1.0000
15.500 1.1455 0.07428 0.06742 -0.0029 0.0205 1.0000
15.750 1.1368 0.07872 0.07196 -0.0040 0.0201 1.0000
16.000 1.1329 0.08261 0.07596 -0.0049 0.0195 1.0000
16.250 1.1278 0.08671 0.08018 -0.0060 0.0191 1.0000
16.500 1.1240 0.09069 0.08427 -0.0072 0.0183 1.0000
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