RAF 19 AIRFOIL (raf19-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 19 AIRFOIL (raf19-il) Reynolds number: 500,000 Max Cl/Cd: 82.22 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf19-il-500000.txt Download as CSV file: xf-raf19-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 0.0441 0.10121 0.09912 -0.0745 0.9628 0.0223
-9.000 0.0660 0.09811 0.09602 -0.0781 0.9582 0.0229
-8.750 0.0785 0.09557 0.09348 -0.0793 0.9467 0.0238
-8.500 0.0948 0.09242 0.09033 -0.0822 0.9346 0.0253
-8.250 0.1153 0.08832 0.08620 -0.0912 0.9194 0.0263
-8.000 0.1560 0.08297 0.08078 -0.0979 0.9043 0.0269
-7.750 0.2147 0.07829 0.07596 -0.1104 0.8837 0.0281
-7.500 0.2567 0.07400 0.07140 -0.1231 0.8391 0.0314
-7.250 0.2636 0.07188 0.06906 -0.1251 0.8015 0.0315
-7.000 0.2701 0.06988 0.06693 -0.1255 0.7773 0.0315
-6.750 0.2774 0.06748 0.06443 -0.1259 0.7593 0.0315
-6.500 0.2807 0.06332 0.06019 -0.1247 0.7455 0.0259
-6.250 0.2903 0.06157 0.05837 -0.1248 0.7306 0.0254
-6.000 0.2986 0.05887 0.05560 -0.1261 0.7178 0.0252
-5.750 0.3083 0.05580 0.05247 -0.1281 0.7056 0.0251
-5.500 0.3189 0.05074 0.04736 -0.1327 0.6946 0.0268
-5.250 0.3382 0.05113 0.04769 -0.1315 0.6806 0.0279
-5.000 0.3565 0.04471 0.04115 -0.1388 0.6702 0.0319
-4.750 0.3760 0.04488 0.04126 -0.1377 0.6545 0.0327
-4.500 0.3967 0.04393 0.04022 -0.1382 0.6384 0.0358
-4.250 0.4247 0.04172 0.03787 -0.1423 0.6225 0.0453
-4.000 0.4391 0.04250 0.03860 -0.1390 0.6060 0.0464
-3.500 0.5050 0.04121 0.03696 -0.1458 0.5769 0.0627
-3.250 0.5176 0.03823 0.03391 -0.1451 0.5664 0.0638
-3.000 0.5330 0.03744 0.03306 -0.1433 0.5557 0.0648
-2.750 0.5524 0.03671 0.03225 -0.1426 0.5456 0.0667
-2.500 0.5998 0.03592 0.03122 -0.1486 0.5366 0.0732
-2.250 0.6270 0.03444 0.02958 -0.1498 0.5281 0.0734
-2.000 0.6439 0.03143 0.02651 -0.1498 0.5209 0.0745
-1.750 0.6642 0.03038 0.02539 -0.1491 0.5126 0.0749
-1.500 0.6854 0.02946 0.02442 -0.1485 0.5046 0.0756
-1.250 0.7077 0.02859 0.02346 -0.1480 0.4962 0.0764
-1.000 0.7313 0.02770 0.02251 -0.1478 0.4885 0.0776
-0.750 0.7553 0.02687 0.02158 -0.1476 0.4800 0.0797
-0.500 0.7940 0.02613 0.02058 -0.1495 0.4716 0.0848
-0.250 0.8044 0.01360 0.00671 -0.1486 0.4700 0.0714
0.000 0.8271 0.01323 0.00611 -0.1474 0.4607 0.0728
0.250 0.8510 0.01272 0.00541 -0.1465 0.4503 0.0744
0.500 0.8740 0.01256 0.00515 -0.1453 0.4389 0.0761
0.750 0.8964 0.01261 0.00512 -0.1440 0.4264 0.0780
1.000 0.9187 0.01266 0.00508 -0.1427 0.4134 0.0803
1.250 0.9414 0.01268 0.00500 -0.1415 0.4007 0.0830
1.500 0.9636 0.01269 0.00490 -0.1402 0.3887 0.0863
1.750 0.9847 0.01289 0.00505 -0.1387 0.3780 0.0900
2.000 1.0056 0.01309 0.00519 -0.1372 0.3685 0.0948
2.250 1.0266 0.01322 0.00526 -0.1357 0.3606 0.1003
2.500 1.0463 0.01350 0.00554 -0.1339 0.3531 0.1049
2.750 1.0666 0.01374 0.00572 -0.1323 0.3467 0.1101
3.000 1.0878 0.01383 0.00577 -0.1309 0.3406 0.1147
3.250 1.1067 0.01411 0.00602 -0.1291 0.3347 0.1181
3.500 1.1280 0.01429 0.00620 -0.1277 0.3301 0.1219
3.750 1.1490 0.01447 0.00635 -0.1263 0.3257 0.1252
4.000 1.1692 0.01464 0.00645 -0.1248 0.3213 0.1283
4.250 1.1885 0.01491 0.00672 -0.1232 0.3172 0.1321
4.500 1.2104 0.01505 0.00691 -0.1220 0.3139 0.1350
4.750 1.2312 0.01525 0.00710 -0.1206 0.3103 0.1386
5.000 1.2506 0.01554 0.00735 -0.1190 0.3068 0.1419
5.250 1.2700 0.01573 0.00749 -0.1175 0.3030 0.1443
5.500 1.2908 0.01591 0.00772 -0.1162 0.3003 0.1470
5.750 1.3120 0.01607 0.00792 -0.1150 0.2975 0.1496
6.000 1.3323 0.01625 0.00812 -0.1137 0.2943 0.1520
6.250 1.3517 0.01648 0.00834 -0.1122 0.2913 0.1542
6.500 1.3701 0.01679 0.00862 -0.1106 0.2883 0.1564
6.750 1.3892 0.01705 0.00889 -0.1092 0.2849 0.1590
7.000 1.4093 0.01714 0.00907 -0.1079 0.2806 0.1625
7.250 1.4281 0.01738 0.00934 -0.1064 0.2772 0.1659
7.500 1.4446 0.01773 0.00966 -0.1046 0.2731 0.1700
7.750 1.4624 0.01803 0.00999 -0.1031 0.2690 0.1745
8.000 1.4818 0.01823 0.01027 -0.1018 0.2653 0.1806
8.250 1.4992 0.01854 0.01059 -0.1002 0.2611 0.1870
8.500 1.5136 0.01899 0.01103 -0.0983 0.2560 0.1931
8.750 1.5329 0.01920 0.01131 -0.0971 0.2502 0.2009
9.000 1.5489 0.01958 0.01171 -0.0955 0.2437 0.2095
9.250 1.5645 0.02002 0.01217 -0.0939 0.2377 0.2176
9.500 1.5798 0.02049 0.01265 -0.0924 0.2289 0.2270
9.750 1.5924 0.02114 0.01326 -0.0906 0.2150 0.2363
10.000 1.5985 0.02220 0.01418 -0.0880 0.1947 0.2449
10.250 1.6005 0.02359 0.01543 -0.0852 0.1708 0.2545
10.500 1.5878 0.02602 0.01761 -0.0811 0.1340 0.2611
10.750 1.5606 0.02976 0.02110 -0.0763 0.0931 0.2623
11.000 1.5303 0.03425 0.02543 -0.0724 0.0515 0.2630
11.250 1.5156 0.03783 0.02900 -0.0702 0.0227 0.2695
11.500 1.5167 0.04021 0.03150 -0.0693 0.0190 0.3028
11.750 1.6298 0.04519 0.03755 -0.0938 0.0150 1.0000
12.000 1.6270 0.04814 0.04062 -0.0927 0.0146 1.0000
12.250 1.6193 0.05177 0.04442 -0.0919 0.0141 1.0000
12.500 1.6144 0.05518 0.04795 -0.0912 0.0139 1.0000
12.750 1.6088 0.05881 0.05170 -0.0908 0.0139 1.0000
13.000 1.6022 0.06270 0.05572 -0.0905 0.0136 1.0000
13.250 1.5935 0.06695 0.06009 -0.0904 0.0133 1.0000
13.500 1.5824 0.07165 0.06492 -0.0905 0.0131 1.0000
13.750 1.5697 0.07669 0.07009 -0.0908 0.0128 1.0000
14.000 1.5564 0.08187 0.07540 -0.0912 0.0127 1.0000
14.250 1.5411 0.08745 0.08112 -0.0918 0.0127 1.0000
14.500 1.5246 0.09336 0.08716 -0.0926 0.0125 1.0000
14.750 1.5072 0.09948 0.09342 -0.0936 0.0124 1.0000
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Polar data table (+)
Polar graphs
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