RAF 19 AIRFOIL (raf19-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 19 AIRFOIL (raf19-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.78 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf19-il-1000000.txt Download as CSV file: xf-raf19-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 19 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.0438 0.10265 0.10106 -0.0805 0.9625 0.0142
-9.750 0.0597 0.09900 0.09741 -0.0839 0.9560 0.0143
-9.500 0.0738 0.09512 0.09352 -0.0869 0.9455 0.0146
-9.250 0.1138 0.09122 0.08955 -0.0953 0.9291 0.0149
-9.000 0.1854 0.08520 0.08329 -0.1130 0.8858 0.0158
-8.250 0.2262 0.07293 0.07030 -0.1253 0.7587 0.0148
-8.000 0.2360 0.07170 0.06900 -0.1252 0.7411 0.0151
-7.750 0.1462 0.05279 0.05002 -0.1355 0.7368 0.0142
-7.500 0.1561 0.04932 0.04645 -0.1390 0.7249 0.0147
-7.250 0.1737 0.04770 0.04478 -0.1404 0.7142 0.0152
-7.000 0.1921 0.04626 0.04327 -0.1416 0.7031 0.0156
-6.750 0.2112 0.04430 0.04127 -0.1436 0.6921 0.0163
-6.500 0.2312 0.04197 0.03885 -0.1461 0.6810 0.0172
-6.250 0.2522 0.03995 0.03674 -0.1481 0.6685 0.0180
-6.000 0.2744 0.03898 0.03576 -0.1488 0.6547 0.0200
-5.750 0.2912 0.02206 0.01830 -0.1665 0.6482 0.0354
-5.500 0.3189 0.03585 0.03257 -0.1513 0.6209 0.0318
-5.250 0.3398 0.03723 0.03389 -0.1486 0.5980 0.0325
-5.000 0.3606 0.03803 0.03459 -0.1467 0.5783 0.0333
-4.750 0.3858 0.03478 0.03118 -0.1504 0.5649 0.0381
-4.500 0.4079 0.03547 0.03180 -0.1490 0.5514 0.0386
-4.250 0.4296 0.03612 0.03239 -0.1476 0.5402 0.0393
-4.000 0.4519 0.03627 0.03250 -0.1469 0.5303 0.0404
-3.750 0.4815 0.03359 0.02968 -0.1502 0.5230 0.0443
-2.750 0.5668 0.01293 0.00755 -0.1586 0.5018 0.0526
-2.500 0.5902 0.01244 0.00688 -0.1577 0.4945 0.0532
-2.250 0.6114 0.01120 0.00533 -0.1565 0.4885 0.0547
-2.000 0.6357 0.01089 0.00490 -0.1556 0.4815 0.0554
-1.750 0.6603 0.01067 0.00458 -0.1547 0.4748 0.0561
-1.500 0.6855 0.01047 0.00429 -0.1539 0.4674 0.0566
-1.250 0.7100 0.01034 0.00406 -0.1529 0.4595 0.0572
-1.000 0.7352 0.01021 0.00386 -0.1521 0.4505 0.0579
-0.750 0.7598 0.01014 0.00370 -0.1512 0.4410 0.0587
-0.500 0.7840 0.01011 0.00356 -0.1503 0.4288 0.0597
-0.250 0.8086 0.01008 0.00344 -0.1494 0.4162 0.0605
0.000 0.8326 0.01011 0.00337 -0.1484 0.4028 0.0616
0.250 0.8562 0.01018 0.00334 -0.1473 0.3890 0.0625
0.500 0.8795 0.01022 0.00328 -0.1462 0.3758 0.0633
0.750 0.9024 0.01025 0.00323 -0.1450 0.3639 0.0659
1.000 0.9258 0.01032 0.00324 -0.1439 0.3539 0.0685
1.250 0.9491 0.01041 0.00329 -0.1428 0.3456 0.0711
1.500 0.9721 0.01051 0.00333 -0.1416 0.3376 0.0748
1.750 0.9950 0.01061 0.00344 -0.1405 0.3310 0.0821
2.000 1.0178 0.01073 0.00355 -0.1393 0.3252 0.0894
2.250 1.0391 0.01092 0.00371 -0.1378 0.3189 0.0949
2.500 1.0617 0.01107 0.00384 -0.1366 0.3149 0.0976
2.750 1.0838 0.01114 0.00391 -0.1353 0.3109 0.1024
3.000 1.1052 0.01131 0.00408 -0.1339 0.3065 0.1057
3.250 1.1259 0.01150 0.00424 -0.1324 0.3018 0.1084
3.500 1.1489 0.01160 0.00435 -0.1313 0.2993 0.1104
3.750 1.1711 0.01174 0.00448 -0.1301 0.2962 0.1115
4.000 1.1924 0.01181 0.00453 -0.1287 0.2929 0.1144
4.250 1.2130 0.01197 0.00469 -0.1272 0.2892 0.1174
4.500 1.2334 0.01216 0.00488 -0.1257 0.2857 0.1195
4.750 1.2561 0.01227 0.00501 -0.1246 0.2836 0.1222
5.000 1.2780 0.01241 0.00516 -0.1234 0.2809 0.1245
5.250 1.2989 0.01259 0.00534 -0.1221 0.2776 0.1263
5.500 1.3190 0.01275 0.00549 -0.1206 0.2747 0.1290
5.750 1.3375 0.01298 0.00570 -0.1189 0.2708 0.1313
6.000 1.3600 0.01306 0.00583 -0.1178 0.2682 0.1335
6.250 1.3817 0.01319 0.00597 -0.1167 0.2648 0.1356
6.500 1.4019 0.01338 0.00616 -0.1153 0.2613 0.1380
6.750 1.4198 0.01367 0.00642 -0.1136 0.2563 0.1404
7.000 1.4406 0.01383 0.00661 -0.1123 0.2537 0.1423
7.250 1.4617 0.01397 0.00678 -0.1112 0.2506 0.1477
7.500 1.4808 0.01422 0.00702 -0.1098 0.2449 0.1523
7.750 1.4986 0.01452 0.00731 -0.1081 0.2394 0.1564
8.000 1.5188 0.01471 0.00753 -0.1069 0.2346 0.1630
8.250 1.5353 0.01508 0.00786 -0.1051 0.2272 0.1695
8.500 1.5529 0.01541 0.00818 -0.1035 0.2179 0.1760
8.750 1.5652 0.01597 0.00865 -0.1012 0.2027 0.1825
9.000 1.5676 0.01705 0.00949 -0.0974 0.1730 0.1868
9.250 1.5576 0.01878 0.01094 -0.0920 0.1329 0.1899
9.500 1.5306 0.02159 0.01342 -0.0848 0.0806 0.1908
9.750 1.5028 0.02482 0.01643 -0.0785 0.0216 0.1913
10.000 1.5099 0.02601 0.01768 -0.0764 0.0157 0.1963
10.250 1.5193 0.02709 0.01882 -0.0748 0.0140 0.2011
10.500 1.5295 0.02819 0.02000 -0.0734 0.0137 0.2075
10.750 1.5383 0.02942 0.02130 -0.0719 0.0129 0.2130
11.000 1.5454 0.03086 0.02283 -0.0705 0.0123 0.2193
11.250 1.5521 0.03240 0.02445 -0.0693 0.0119 0.2256
11.500 1.5537 0.03445 0.02661 -0.0678 0.0113 0.2313
11.750 1.5564 0.03652 0.02878 -0.0666 0.0108 0.2387
12.000 1.5607 0.03851 0.03087 -0.0657 0.0106 0.2509
12.250 1.5663 0.04052 0.03300 -0.0652 0.0100 0.2984
12.500 1.6766 0.04788 0.04151 -0.0931 0.0084 1.0000
12.750 1.6698 0.05142 0.04516 -0.0923 0.0083 1.0000
13.000 1.6660 0.05470 0.04852 -0.0917 0.0082 1.0000
13.250 1.6623 0.05808 0.05199 -0.0912 0.0080 1.0000
13.500 1.6531 0.06230 0.05632 -0.0910 0.0079 1.0000
13.750 1.6458 0.06634 0.06046 -0.0909 0.0077 1.0000
14.000 1.6350 0.07095 0.06518 -0.0910 0.0076 1.0000
14.250 1.6190 0.07642 0.07078 -0.0913 0.0076 1.0000
14.500 1.6048 0.08169 0.07616 -0.0917 0.0075 1.0000
14.750 1.5889 0.08728 0.08187 -0.0922 0.0074 1.0000
15.000 1.5735 0.09292 0.08762 -0.0929 0.0073 1.0000
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Polar data table (+)
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