RAF 19 AIRFOIL (raf19-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 19 AIRFOIL (raf19-il) Reynolds number: 500,000 Max Cl/Cd: 83.27 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf19-il-500000-n5.txt Download as CSV file: xf-raf19-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 0.2073 0.08766 0.08472 -0.1214 0.8250 0.0089
-9.250 0.2174 0.08498 0.08178 -0.1230 0.7825 0.0088
-9.000 0.2204 0.08210 0.07877 -0.1232 0.7586 0.0085
-8.750 0.2260 0.07986 0.07645 -0.1234 0.7434 0.0086
-8.500 0.2309 0.07767 0.07419 -0.1234 0.7276 0.0090
-8.250 0.2346 0.07539 0.07185 -0.1233 0.7133 0.0092
-8.000 0.2353 0.07266 0.06910 -0.1232 0.7018 0.0093
-7.750 0.2295 0.06944 0.06588 -0.1227 0.6923 0.0099
-7.500 0.2079 0.06391 0.06036 -0.1234 0.6840 0.0103
-7.250 0.2038 0.05901 0.05539 -0.1265 0.6759 0.0108
-7.000 0.2122 0.05636 0.05266 -0.1284 0.6606 0.0111
-6.750 0.2267 0.05470 0.05095 -0.1296 0.6478 0.0117
-6.500 0.2417 0.05280 0.04899 -0.1311 0.6336 0.0121
-6.250 0.2577 0.05086 0.04697 -0.1327 0.6177 0.0127
-6.000 0.2749 0.04881 0.04482 -0.1346 0.6022 0.0135
-5.750 0.2930 0.04701 0.04289 -0.1361 0.5840 0.0139
-5.500 0.3129 0.04491 0.04067 -0.1383 0.5697 0.0147
-5.250 0.3344 0.04359 0.03931 -0.1396 0.5575 0.0166
-5.000 0.3569 0.04194 0.03761 -0.1413 0.5477 0.0188
-4.000 0.4537 0.03629 0.03163 -0.1472 0.5140 0.0366
-3.750 0.4784 0.03552 0.03078 -0.1478 0.5066 0.0389
-3.250 0.5337 0.03104 0.02602 -0.1525 0.4937 0.0433
-3.000 0.5557 0.03150 0.02643 -0.1514 0.4856 0.0444
-2.500 0.6055 0.02997 0.02475 -0.1521 0.4713 0.0480
-2.000 0.6529 0.01435 0.00757 -0.1580 0.4636 0.0521
-1.750 0.6758 0.01344 0.00637 -0.1570 0.4556 0.0529
-1.500 0.6993 0.01306 0.00582 -0.1561 0.4469 0.0538
-1.250 0.7231 0.01285 0.00546 -0.1551 0.4369 0.0545
-1.000 0.7470 0.01270 0.00518 -0.1541 0.4258 0.0552
-0.750 0.7706 0.01262 0.00498 -0.1531 0.4151 0.0559
-0.250 0.8172 0.01256 0.00470 -0.1509 0.3913 0.0578
0.000 0.8403 0.01258 0.00461 -0.1498 0.3801 0.0586
0.250 0.8629 0.01264 0.00456 -0.1486 0.3692 0.0599
0.500 0.8857 0.01269 0.00451 -0.1474 0.3589 0.0612
0.750 0.9081 0.01276 0.00450 -0.1462 0.3502 0.0625
1.000 0.9299 0.01285 0.00450 -0.1449 0.3418 0.0638
1.250 0.9520 0.01292 0.00453 -0.1436 0.3355 0.0668
1.500 0.9740 0.01300 0.00459 -0.1423 0.3296 0.0709
1.750 0.9953 0.01312 0.00467 -0.1409 0.3245 0.0751
2.000 1.0173 0.01324 0.00480 -0.1396 0.3201 0.0811
2.250 1.0393 0.01336 0.00489 -0.1383 0.3157 0.0876
2.500 1.0605 0.01353 0.00505 -0.1369 0.3114 0.0919
3.000 1.1033 0.01388 0.00535 -0.1342 0.3040 0.0995
3.250 1.1251 0.01404 0.00549 -0.1330 0.3004 0.1020
3.500 1.1461 0.01421 0.00567 -0.1316 0.2965 0.1057
3.750 1.1662 0.01445 0.00588 -0.1301 0.2927 0.1086
4.000 1.1871 0.01464 0.00607 -0.1288 0.2899 0.1114
4.250 1.2087 0.01478 0.00623 -0.1276 0.2873 0.1136
4.500 1.2299 0.01496 0.00640 -0.1263 0.2845 0.1154
4.750 1.2504 0.01515 0.00659 -0.1250 0.2816 0.1169
5.000 1.2702 0.01535 0.00681 -0.1235 0.2787 0.1197
5.250 1.2893 0.01563 0.00709 -0.1220 0.2760 0.1235
5.500 1.3097 0.01583 0.00732 -0.1207 0.2738 0.1261
5.750 1.3304 0.01602 0.00753 -0.1194 0.2718 0.1280
6.000 1.3506 0.01622 0.00776 -0.1181 0.2695 0.1295
6.250 1.3701 0.01646 0.00802 -0.1167 0.2668 0.1309
6.500 1.3891 0.01672 0.00830 -0.1153 0.2642 0.1334
6.750 1.4070 0.01703 0.00863 -0.1137 0.2613 0.1360
7.000 1.4246 0.01736 0.00898 -0.1121 0.2586 0.1386
7.250 1.4446 0.01759 0.00926 -0.1109 0.2539 0.1420
7.500 1.4621 0.01793 0.00961 -0.1094 0.2488 0.1451
7.750 1.4775 0.01837 0.01003 -0.1076 0.2440 0.1487
8.000 1.4959 0.01869 0.01041 -0.1062 0.2399 0.1543
8.250 1.5129 0.01908 0.01083 -0.1047 0.2346 0.1594
8.500 1.5264 0.01964 0.01137 -0.1028 0.2282 0.1651
8.750 1.5429 0.02007 0.01184 -0.1013 0.2216 0.1716
9.000 1.5541 0.02080 0.01251 -0.0992 0.2108 0.1769
9.250 1.5635 0.02166 0.01331 -0.0970 0.1963 0.1819
9.500 1.5653 0.02300 0.01450 -0.0939 0.1718 0.1866
9.750 1.5475 0.02570 0.01688 -0.0890 0.1278 0.1882
10.000 1.5206 0.02934 0.02028 -0.0840 0.0836 0.1884
10.250 1.4939 0.03344 0.02423 -0.0799 0.0388 0.1887
10.500 1.4900 0.03595 0.02677 -0.0780 0.0176 0.1919
10.750 1.4961 0.03768 0.02860 -0.0769 0.0150 0.1967
11.000 1.5008 0.03959 0.03061 -0.0758 0.0135 0.2017
11.250 1.5057 0.04152 0.03264 -0.0748 0.0125 0.2059
11.500 1.5101 0.04358 0.03480 -0.0740 0.0117 0.2111
11.750 1.5133 0.04581 0.03714 -0.0732 0.0110 0.2164
12.000 1.5145 0.04834 0.03978 -0.0726 0.0102 0.2239
12.250 1.5125 0.05129 0.04286 -0.0719 0.0097 0.2278
12.500 1.5135 0.05401 0.04570 -0.0716 0.0094 0.2390
12.750 1.5130 0.05699 0.04880 -0.0713 0.0090 0.2504
13.000 1.5107 0.06031 0.05227 -0.0712 0.0085 0.2771
13.500 1.5904 0.07349 0.06663 -0.0957 0.0070 1.0000
13.750 1.5805 0.07809 0.07135 -0.0958 0.0068 1.0000
14.000 1.5703 0.08279 0.07617 -0.0961 0.0066 1.0000
14.250 1.5584 0.08783 0.08135 -0.0965 0.0065 1.0000
14.500 1.5452 0.09313 0.08678 -0.0970 0.0064 1.0000
14.750 1.5315 0.09858 0.09236 -0.0977 0.0063 1.0000
15.000 1.5171 0.10427 0.09817 -0.0986 0.0062 1.0000
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Polar data table (+)
Polar graphs
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