RAF 19 AIRFOIL (raf19-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 19 AIRFOIL (raf19-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.98 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf19-il-1000000-n5.txt Download as CSV file: xf-raf19-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.1673 0.09316 0.09024 -0.1203 0.7383 0.0054
-10.250 0.1743 0.09046 0.08748 -0.1212 0.7259 0.0055
-10.000 0.1495 0.08145 0.07847 -0.1235 0.7189 0.0056
-9.750 0.1782 0.08339 0.08035 -0.1231 0.7050 0.0058
-9.500 0.1408 0.07329 0.07025 -0.1263 0.7031 0.0063
-9.250 0.1462 0.07122 0.06815 -0.1267 0.6936 0.0065
-9.000 0.1425 0.06825 0.06514 -0.1270 0.6831 0.0065
-8.750 0.1394 0.06601 0.06286 -0.1265 0.6724 0.0067
-8.500 0.1404 0.06370 0.06050 -0.1269 0.6597 0.0071
-8.250 0.1472 0.06160 0.05834 -0.1278 0.6453 0.0071
-8.000 0.1554 0.05955 0.05621 -0.1288 0.6263 0.0072
-7.750 0.1646 0.05756 0.05410 -0.1299 0.6020 0.0075
-7.500 0.1764 0.05567 0.05212 -0.1311 0.5833 0.0076
-7.250 0.1895 0.05388 0.05022 -0.1324 0.5622 0.0078
-7.000 0.2055 0.05204 0.04832 -0.1340 0.5528 0.0079
-6.750 0.2232 0.05067 0.04689 -0.1351 0.5392 0.0083
-6.500 0.2418 0.04902 0.04521 -0.1367 0.5312 0.0087
-6.250 0.2616 0.04721 0.04336 -0.1386 0.5241 0.0092
-6.000 0.2818 0.04519 0.04127 -0.1409 0.5170 0.0100
-5.750 0.3041 0.04364 0.03968 -0.1425 0.5109 0.0102
-5.500 0.3268 0.04166 0.03763 -0.1448 0.5044 0.0108
-5.250 0.3504 0.04015 0.03606 -0.1465 0.4977 0.0116
-5.000 0.3758 0.03772 0.03358 -0.1495 0.4925 0.0127
-4.750 0.4025 0.03454 0.03028 -0.1533 0.4866 0.0140
-4.500 0.4313 0.02272 0.01784 -0.1650 0.4841 0.0158
-4.250 0.4434 0.01560 0.01004 -0.1665 0.4810 0.0192
-4.000 0.4567 0.01191 0.00595 -0.1653 0.4764 0.0345
-3.750 0.4806 0.01133 0.00529 -0.1646 0.4692 0.0379
-3.500 0.5061 0.01119 0.00510 -0.1639 0.4625 0.0403
-3.250 0.5316 0.01108 0.00492 -0.1632 0.4554 0.0415
-3.000 0.5570 0.01102 0.00478 -0.1624 0.4485 0.0420
-2.750 0.5820 0.01083 0.00449 -0.1617 0.4401 0.0434
-2.500 0.6067 0.01071 0.00429 -0.1608 0.4299 0.0448
-2.250 0.6312 0.01066 0.00413 -0.1599 0.4175 0.0455
-2.000 0.6560 0.01066 0.00406 -0.1591 0.4054 0.0466
-1.750 0.6804 0.01070 0.00401 -0.1582 0.3920 0.0479
-1.500 0.7044 0.01070 0.00390 -0.1572 0.3792 0.0486
-1.250 0.7284 0.01070 0.00379 -0.1562 0.3676 0.0491
-0.750 0.7762 0.01075 0.00363 -0.1542 0.3457 0.0499
-0.500 0.8001 0.01079 0.00359 -0.1532 0.3375 0.0504
-0.250 0.8242 0.01083 0.00355 -0.1522 0.3293 0.0508
0.000 0.8480 0.01088 0.00354 -0.1512 0.3230 0.0511
0.250 0.8725 0.01091 0.00352 -0.1503 0.3185 0.0514
0.500 0.8965 0.01094 0.00351 -0.1494 0.3137 0.0519
0.750 0.9201 0.01099 0.00350 -0.1483 0.3087 0.0532
1.000 0.9437 0.01101 0.00349 -0.1473 0.3052 0.0553
1.250 0.9670 0.01104 0.00350 -0.1462 0.3019 0.0571
1.500 0.9896 0.01108 0.00353 -0.1450 0.2981 0.0593
1.750 1.0118 0.01116 0.00358 -0.1437 0.2942 0.0610
2.000 1.0340 0.01124 0.00364 -0.1424 0.2902 0.0637
2.250 1.0567 0.01128 0.00371 -0.1413 0.2874 0.0718
2.500 1.0792 0.01136 0.00382 -0.1401 0.2842 0.0816
2.750 1.1014 0.01148 0.00392 -0.1389 0.2810 0.0869
3.000 1.1231 0.01162 0.00405 -0.1376 0.2778 0.0904
3.250 1.1449 0.01176 0.00419 -0.1363 0.2748 0.0941
3.500 1.1674 0.01187 0.00431 -0.1351 0.2728 0.0972
3.750 1.1898 0.01199 0.00443 -0.1340 0.2706 0.0991
4.000 1.2119 0.01212 0.00456 -0.1328 0.2682 0.1006
4.250 1.2334 0.01228 0.00470 -0.1316 0.2654 0.1018
4.500 1.2544 0.01242 0.00486 -0.1302 0.2627 0.1054
4.750 1.2752 0.01260 0.00503 -0.1289 0.2598 0.1077
5.000 1.2968 0.01274 0.00519 -0.1277 0.2580 0.1094
5.250 1.3185 0.01288 0.00535 -0.1265 0.2564 0.1113
5.500 1.3397 0.01304 0.00553 -0.1253 0.2538 0.1135
5.750 1.3604 0.01321 0.00571 -0.1240 0.2515 0.1152
6.000 1.3805 0.01342 0.00591 -0.1226 0.2487 0.1165
6.250 1.3994 0.01368 0.00615 -0.1210 0.2426 0.1180
6.500 1.4201 0.01384 0.00635 -0.1198 0.2402 0.1211
6.750 1.4394 0.01408 0.00658 -0.1184 0.2352 0.1234
7.000 1.4579 0.01435 0.00685 -0.1168 0.2310 0.1257
7.250 1.4766 0.01462 0.00713 -0.1153 0.2268 0.1284
7.500 1.4954 0.01489 0.00740 -0.1139 0.2218 0.1305
7.750 1.5118 0.01526 0.00775 -0.1121 0.2153 0.1340
8.000 1.5290 0.01560 0.00810 -0.1104 0.2089 0.1399
8.250 1.5421 0.01615 0.00858 -0.1082 0.1973 0.1446
8.500 1.5515 0.01687 0.00920 -0.1055 0.1799 0.1483
8.750 1.5439 0.01849 0.01053 -0.1004 0.1414 0.1515
9.000 1.5187 0.02117 0.01289 -0.0933 0.0885 0.1525
9.250 1.4939 0.02416 0.01566 -0.0871 0.0344 0.1533
9.500 1.4975 0.02554 0.01706 -0.0846 0.0149 0.1585
9.750 1.5083 0.02651 0.01807 -0.0830 0.0129 0.1622
10.000 1.5195 0.02748 0.01911 -0.0815 0.0120 0.1682
10.250 1.5294 0.02859 0.02027 -0.0801 0.0107 0.1733
10.500 1.5382 0.02983 0.02157 -0.0786 0.0099 0.1780
10.750 1.5476 0.03108 0.02288 -0.0774 0.0092 0.1830
11.000 1.5560 0.03244 0.02431 -0.0761 0.0086 0.1877
11.250 1.5636 0.03392 0.02584 -0.0750 0.0078 0.1908
11.500 1.5694 0.03564 0.02763 -0.0738 0.0074 0.1949
11.750 1.5759 0.03734 0.02940 -0.0728 0.0070 0.1993
12.000 1.5811 0.03918 0.03132 -0.0719 0.0065 0.2039
12.250 1.5851 0.04121 0.03341 -0.0710 0.0062 0.2064
12.500 1.5886 0.04335 0.03562 -0.0702 0.0059 0.2126
12.750 1.5902 0.04575 0.03810 -0.0695 0.0056 0.2178
13.000 1.5893 0.04849 0.04093 -0.0688 0.0053 0.2248
13.500 1.5885 0.05415 0.04680 -0.0680 0.0050 0.2616
14.000 1.6965 0.06526 0.05908 -0.0956 0.0038 1.0000
14.250 1.6892 0.06930 0.06321 -0.0954 0.0038 1.0000
14.500 1.6785 0.07387 0.06790 -0.0955 0.0038 1.0000
14.750 1.6692 0.07826 0.07238 -0.0955 0.0037 1.0000
15.000 1.6576 0.08305 0.07728 -0.0957 0.0036 1.0000
15.250 1.6453 0.08800 0.08234 -0.0961 0.0035 1.0000
15.500 1.6311 0.09330 0.08776 -0.0966 0.0035 1.0000
15.750 1.6178 0.09854 0.09310 -0.0971 0.0034 1.0000
16.000 1.6033 0.10405 0.09873 -0.0979 0.0034 1.0000
16.250 1.5880 0.10979 0.10458 -0.0989 0.0033 1.0000
16.500 1.5735 0.11545 0.11035 -0.0999 0.0033 1.0000
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