RAF 19 AIRFOIL (raf19-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 19 AIRFOIL (raf19-il) Reynolds number: 200,000 Max Cl/Cd: 61.76 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf19-il-200000-n5.txt Download as CSV file: xf-raf19-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 0.0382 0.10939 0.10614 -0.0700 0.9358 0.0257
-9.250 0.0495 0.10655 0.10331 -0.0715 0.9239 0.0258
-9.000 0.0578 0.10140 0.09814 -0.0753 0.9130 0.0192
-8.750 0.0796 0.09821 0.09493 -0.0785 0.9042 0.0185
-8.500 0.1000 0.09454 0.09123 -0.0825 0.8913 0.0180
-8.250 0.1264 0.09040 0.08704 -0.0884 0.8784 0.0177
-8.000 0.1614 0.08572 0.08227 -0.0967 0.8635 0.0179
-7.500 0.2268 0.07635 0.07260 -0.1130 0.8161 0.0187
-7.250 0.2426 0.07321 0.06929 -0.1162 0.7920 0.0187
-7.000 0.2510 0.07088 0.06685 -0.1172 0.7706 0.0187
-6.750 0.2580 0.06822 0.06407 -0.1184 0.7517 0.0189
-6.500 0.2650 0.06548 0.06125 -0.1197 0.7361 0.0191
-6.250 0.2773 0.06391 0.05961 -0.1204 0.7213 0.0199
-6.000 0.2919 0.06287 0.05849 -0.1207 0.7079 0.0215
-5.750 0.3035 0.06048 0.05603 -0.1222 0.6961 0.0220
-5.500 0.3155 0.05745 0.05297 -0.1245 0.6847 0.0233
-5.250 0.3301 0.05431 0.04977 -0.1272 0.6733 0.0245
-5.000 0.3482 0.05308 0.04846 -0.1280 0.6603 0.0258
-4.750 0.3680 0.05002 0.04532 -0.1314 0.6481 0.0298
-4.500 0.3880 0.04888 0.04410 -0.1322 0.6343 0.0324
-4.250 0.4181 0.04466 0.03970 -0.1389 0.6224 0.0418
-4.000 0.4357 0.04477 0.03973 -0.1373 0.6080 0.0440
-3.750 0.4655 0.04277 0.03751 -0.1411 0.5952 0.0507
-3.250 0.5152 0.04167 0.03613 -0.1431 0.5708 0.0635
-1.750 0.6686 0.03121 0.02458 -0.1502 0.5159 0.0640
-1.500 0.6937 0.02963 0.02286 -0.1507 0.5075 0.0644
-1.250 0.7159 0.02876 0.02185 -0.1503 0.4990 0.0652
-1.000 0.7393 0.02792 0.02091 -0.1500 0.4902 0.0657
-0.750 0.7644 0.02640 0.01916 -0.1501 0.4823 0.0656
-0.500 0.7887 0.02524 0.01786 -0.1498 0.4739 0.0660
-0.250 0.8121 0.02422 0.01664 -0.1492 0.4659 0.0665
0.000 0.8356 0.02324 0.01550 -0.1486 0.4565 0.0673
0.250 0.8585 0.02230 0.01435 -0.1478 0.4473 0.0685
0.500 0.8815 0.02096 0.01274 -0.1469 0.4376 0.0703
0.750 0.9068 0.01791 0.00894 -0.1466 0.4291 0.0773
1.000 0.9278 0.01803 0.00900 -0.1451 0.4189 0.0788
1.250 0.9501 0.01798 0.00886 -0.1440 0.4087 0.0809
1.500 0.9723 0.01770 0.00836 -0.1428 0.3993 0.0853
1.750 0.9943 0.01758 0.00807 -0.1416 0.3900 0.0892
2.000 1.0147 0.01782 0.00829 -0.1401 0.3812 0.0920
2.250 1.0346 0.01797 0.00832 -0.1385 0.3729 0.0980
2.500 1.0550 0.01809 0.00835 -0.1370 0.3654 0.1035
2.750 1.0733 0.01838 0.00861 -0.1351 0.3583 0.1071
3.000 1.0929 0.01854 0.00869 -0.1335 0.3520 0.1122
3.250 1.1137 0.01862 0.00864 -0.1321 0.3462 0.1172
3.500 1.1320 0.01891 0.00891 -0.1304 0.3411 0.1201
3.750 1.1516 0.01918 0.00918 -0.1289 0.3366 0.1238
4.000 1.1720 0.01944 0.00938 -0.1275 0.3321 0.1304
4.250 1.1913 0.01972 0.00966 -0.1260 0.3278 0.1342
4.500 1.2099 0.02006 0.00996 -0.1244 0.3241 0.1372
4.750 1.2312 0.02026 0.01015 -0.1233 0.3203 0.1398
5.000 1.2520 0.02049 0.01037 -0.1221 0.3162 0.1433
5.250 1.2718 0.02077 0.01059 -0.1208 0.3122 0.1463
5.500 1.2914 0.02106 0.01086 -0.1195 0.3089 0.1482
5.750 1.3119 0.02138 0.01120 -0.1185 0.3059 0.1504
6.000 1.3355 0.02167 0.01154 -0.1180 0.3028 0.1528
6.250 1.3591 0.02201 0.01191 -0.1176 0.2995 0.1558
6.500 1.3822 0.02238 0.01229 -0.1172 0.2965 0.1594
6.750 1.4046 0.02280 0.01270 -0.1167 0.2938 0.1626
7.000 1.4266 0.02327 0.01317 -0.1161 0.2913 0.1660
7.250 1.4482 0.02366 0.01365 -0.1154 0.2889 0.1713
7.500 1.4688 0.02406 0.01411 -0.1146 0.2861 0.1769
7.750 1.4892 0.02448 0.01462 -0.1138 0.2834 0.1817
8.000 1.5065 0.02495 0.01512 -0.1125 0.2799 0.1878
8.250 1.5215 0.02554 0.01569 -0.1109 0.2757 0.1933
8.500 1.5360 0.02602 0.01629 -0.1092 0.2700 0.1994
8.750 1.5491 0.02661 0.01693 -0.1075 0.2643 0.2062
9.000 1.5605 0.02735 0.01765 -0.1056 0.2597 0.2135
9.250 1.5745 0.02797 0.01839 -0.1041 0.2539 0.2232
9.500 1.5843 0.02880 0.01925 -0.1022 0.2468 0.2332
9.750 1.5938 0.02971 0.02023 -0.1004 0.2391 0.2436
10.000 1.6010 0.03082 0.02136 -0.0985 0.2299 0.2551
10.250 1.6093 0.03197 0.02256 -0.0969 0.2193 0.2739
10.750 1.6447 0.03768 0.02857 -0.1035 0.1537 1.0000
11.000 1.6192 0.04226 0.03291 -0.1005 0.1178 1.0000
11.250 1.5893 0.04770 0.03820 -0.0981 0.0842 1.0000
11.500 1.5664 0.05280 0.04327 -0.0966 0.0593 1.0000
11.750 1.5423 0.05842 0.04891 -0.0956 0.0318 1.0000
12.000 1.5267 0.06330 0.05388 -0.0951 0.0208 1.0000
12.250 1.5192 0.06733 0.05803 -0.0949 0.0187 1.0000
12.500 1.5133 0.07127 0.06212 -0.0948 0.0176 1.0000
12.750 1.5069 0.07535 0.06634 -0.0948 0.0168 1.0000
13.000 1.4997 0.07963 0.07078 -0.0950 0.0163 1.0000
13.250 1.4913 0.08416 0.07547 -0.0953 0.0158 1.0000
13.500 1.4818 0.08895 0.08042 -0.0958 0.0154 1.0000
13.750 1.4702 0.09413 0.08576 -0.0964 0.0149 1.0000
14.000 1.4574 0.09959 0.09139 -0.0972 0.0145 1.0000
14.250 1.4443 0.10521 0.09717 -0.0982 0.0142 1.0000
14.500 1.4311 0.11093 0.10306 -0.0994 0.0140 1.0000
14.750 1.4170 0.11688 0.10916 -0.1007 0.0137 1.0000
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Polar data table (+)
Polar graphs
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