RAF 19 AIRFOIL (raf19-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: RAF 19 AIRFOIL (raf19-il) Reynolds number: 200,000 Max Cl/Cd: 62.38 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf19-il-200000.txt Download as CSV file: xf-raf19-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 0.0642 0.09759 0.09462 -0.0720 0.9449 0.0426
-7.750 0.0823 0.09489 0.09192 -0.0767 0.9334 0.0440
-7.500 0.0963 0.09331 0.09033 -0.0825 0.9201 0.0444
-7.250 0.1152 0.09095 0.08795 -0.0895 0.9054 0.0446
-7.000 0.1425 0.08409 0.08107 -0.0899 0.9000 0.0451
-6.750 0.1723 0.07974 0.07668 -0.0932 0.8883 0.0463
-6.500 0.2058 0.07610 0.07298 -0.0991 0.8750 0.0487
-6.250 0.2436 0.07336 0.07012 -0.1096 0.8567 0.0524
-6.000 0.2839 0.07128 0.06785 -0.1236 0.8360 0.0530
-5.750 0.3010 0.06585 0.06234 -0.1215 0.8205 0.0537
-5.500 0.3219 0.06303 0.05940 -0.1218 0.8030 0.0553
-5.250 0.3403 0.06108 0.05732 -0.1233 0.7845 0.0585
-5.000 0.3780 0.06044 0.05646 -0.1367 0.7655 0.0628
-4.750 0.3807 0.05651 0.05249 -0.1309 0.7515 0.0639
-4.500 0.3947 0.05458 0.05045 -0.1296 0.7368 0.0660
-4.000 0.4369 0.05033 0.04595 -0.1345 0.7077 0.0757
-3.750 0.4810 0.04917 0.04452 -0.1437 0.6931 0.0855
-3.500 0.4859 0.04649 0.04184 -0.1396 0.6807 0.0867
-3.250 0.5006 0.04489 0.04016 -0.1381 0.6685 0.0895
-3.000 0.5636 0.04614 0.04093 -0.1491 0.6543 0.0977
-2.750 0.5718 0.04244 0.03725 -0.1471 0.6427 0.0985
-2.500 0.5856 0.04033 0.03510 -0.1455 0.6311 0.0992
-2.250 0.6032 0.03870 0.03338 -0.1446 0.6203 0.1003
-2.000 0.6235 0.03736 0.03194 -0.1442 0.6089 0.1019
-1.750 0.6462 0.03618 0.03065 -0.1443 0.5972 0.1038
-1.500 0.6724 0.03519 0.02950 -0.1451 0.5860 0.1078
-1.250 0.7223 0.03547 0.02930 -0.1503 0.5743 0.1121
-1.000 0.7369 0.03319 0.02701 -0.1489 0.5635 0.1129
-0.750 0.7550 0.03179 0.02554 -0.1478 0.5531 0.1139
-0.500 0.7759 0.03076 0.02437 -0.1471 0.5430 0.1152
-0.250 0.7969 0.02988 0.02343 -0.1463 0.5315 0.1172
0.000 0.8204 0.02915 0.02256 -0.1459 0.5205 0.1202
0.250 0.8613 0.02967 0.02259 -0.1479 0.5091 0.1271
0.500 0.8751 0.02779 0.02076 -0.1461 0.4980 0.1285
0.750 0.8934 0.02693 0.01985 -0.1447 0.4872 0.1302
1.250 0.9364 0.02582 0.01851 -0.1426 0.4655 0.1373
1.500 0.9654 0.02548 0.01785 -0.1424 0.4551 0.1433
1.750 0.9835 0.02464 0.01692 -0.1408 0.4454 0.1450
2.000 1.0028 0.02411 0.01636 -0.1393 0.4351 0.1473
2.250 1.0244 0.02377 0.01585 -0.1381 0.4263 0.1518
2.500 1.0503 0.02237 0.01410 -0.1371 0.4178 0.1327
2.750 1.0767 0.02090 0.01208 -0.1361 0.4109 0.1287
3.000 1.0966 0.02103 0.01226 -0.1346 0.4027 0.1328
3.250 1.1212 0.02080 0.01165 -0.1337 0.3964 0.1432
3.500 1.1406 0.02099 0.01200 -0.1323 0.3891 0.1490
3.750 1.1646 0.02091 0.01161 -0.1313 0.3833 0.1584
4.000 1.1859 0.02105 0.01179 -0.1303 0.3773 0.1637
4.250 1.2081 0.02118 0.01177 -0.1290 0.3714 0.1732
4.500 1.2313 0.02137 0.01192 -0.1284 0.3663 0.1797
4.750 1.2534 0.02155 0.01203 -0.1273 0.3612 0.1860
5.000 1.2758 0.02161 0.01204 -0.1263 0.3563 0.1886
5.250 1.3001 0.02180 0.01217 -0.1258 0.3519 0.1920
5.500 1.3256 0.02212 0.01243 -0.1255 0.3479 0.1969
5.750 1.3472 0.02231 0.01264 -0.1244 0.3439 0.1993
6.000 1.3704 0.02257 0.01285 -0.1236 0.3398 0.2016
6.250 1.3966 0.02281 0.01309 -0.1236 0.3364 0.2047
6.500 1.4250 0.02326 0.01348 -0.1240 0.3327 0.2089
6.750 1.4438 0.02354 0.01386 -0.1225 0.3292 0.2134
7.000 1.4682 0.02386 0.01424 -0.1222 0.3254 0.2198
7.250 1.4967 0.02426 0.01466 -0.1228 0.3220 0.2272
7.500 1.5342 0.02487 0.01516 -0.1252 0.3176 0.2356
7.750 1.5457 0.02507 0.01554 -0.1224 0.3132 0.2423
8.000 1.5615 0.02526 0.01580 -0.1205 0.3080 0.2510
8.250 1.5848 0.02562 0.01607 -0.1201 0.3029 0.2636
8.500 1.5944 0.02596 0.01655 -0.1171 0.2983 0.2760
8.750 1.6040 0.02624 0.01693 -0.1142 0.2933 0.2922
9.000 1.6182 0.02655 0.01722 -0.1122 0.2882 0.3173
9.250 1.6811 0.02695 0.01845 -0.1216 0.2790 1.0000
9.500 1.6886 0.02739 0.01889 -0.1185 0.2740 1.0000
9.750 1.6927 0.02798 0.01948 -0.1152 0.2675 1.0000
10.000 1.6969 0.02862 0.02021 -0.1120 0.2613 1.0000
10.250 1.7030 0.02940 0.02093 -0.1093 0.2555 1.0000
10.500 1.7082 0.03023 0.02192 -0.1066 0.2489 1.0000
10.750 1.7111 0.03130 0.02298 -0.1040 0.2415 1.0000
11.000 1.7174 0.03236 0.02415 -0.1019 0.2338 1.0000
11.250 1.7227 0.03361 0.02543 -0.0999 0.2278 1.0000
11.500 1.7267 0.03505 0.02692 -0.0980 0.2179 1.0000
11.750 1.7279 0.03682 0.02871 -0.0961 0.2082 1.0000
12.000 1.7277 0.03886 0.03074 -0.0944 0.1973 1.0000
12.250 1.7245 0.04133 0.03318 -0.0927 0.1816 1.0000
12.500 1.7183 0.04421 0.03603 -0.0911 0.1648 1.0000
12.750 1.7092 0.04753 0.03932 -0.0898 0.1491 1.0000
13.000 1.6832 0.05289 0.04456 -0.0884 0.1252 1.0000
13.250 1.6572 0.05862 0.05024 -0.0875 0.1067 1.0000
13.500 1.6310 0.06473 0.05635 -0.0872 0.0893 1.0000
13.750 1.6043 0.07127 0.06292 -0.0874 0.0733 1.0000
14.000 1.5832 0.07732 0.06905 -0.0878 0.0628 1.0000
14.250 1.5577 0.08421 0.07603 -0.0886 0.0518 1.0000
14.500 1.5323 0.09133 0.08326 -0.0898 0.0403 1.0000
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