RAF 27 AIRFOIL (raf27-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 27 AIRFOIL (raf27-il) Reynolds number: 50,000 Max Cl/Cd: 28.27 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf27-il-50000.txt Download as CSV file: xf-raf27-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 27 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5863 0.08337 0.07670 -0.0184 1.0000 0.1653
-9.250 -0.5968 0.07513 0.06850 -0.0214 1.0000 0.1533
-9.000 -0.6169 0.06802 0.06140 -0.0242 1.0000 0.1460
-8.750 -0.7443 0.06948 0.06240 -0.0227 1.0000 0.1338
-8.500 -0.7586 0.06393 0.05665 -0.0223 1.0000 0.1289
-8.250 -0.7838 0.05822 0.05027 -0.0207 1.0000 0.1227
-8.000 -0.7790 0.05377 0.04557 -0.0192 1.0000 0.1212
-7.750 -0.7759 0.04974 0.04111 -0.0172 1.0000 0.1211
-7.500 -0.7716 0.04610 0.03689 -0.0148 1.0000 0.1225
-7.250 -0.7609 0.04255 0.03291 -0.0128 1.0000 0.1249
-7.000 -0.7433 0.03940 0.02957 -0.0113 1.0000 0.1280
-6.750 -0.7261 0.03664 0.02643 -0.0096 1.0000 0.1329
-6.500 -0.7081 0.03409 0.02354 -0.0078 1.0000 0.1406
-6.250 -0.6861 0.03176 0.02092 -0.0064 1.0000 0.1493
-6.000 -0.6637 0.02970 0.01878 -0.0051 1.0000 0.1630
-5.750 -0.6397 0.02770 0.01671 -0.0039 1.0000 0.1806
-5.500 -0.6166 0.02581 0.01498 -0.0025 1.0000 0.2092
-5.250 -0.5975 0.02384 0.01347 -0.0005 1.0000 0.2620
-5.000 -0.5881 0.02165 0.01227 0.0034 1.0000 0.3750
-4.750 -0.5831 0.02063 0.01201 0.0089 1.0000 0.5001
-4.500 -0.5733 0.02046 0.01228 0.0145 1.0000 0.5900
-4.250 -0.5593 0.02060 0.01255 0.0198 1.0000 0.6596
-4.000 -0.5399 0.02081 0.01280 0.0243 1.0000 0.7173
-3.750 -0.5128 0.02146 0.01340 0.0284 1.0000 0.7735
-3.500 -0.4620 0.02264 0.01428 0.0289 1.0000 0.8287
-3.250 -0.3847 0.02343 0.01457 0.0225 1.0000 0.8718
-3.000 -0.2891 0.02370 0.01426 0.0111 1.0000 0.9093
-2.750 -0.2074 0.02328 0.01345 0.0007 1.0000 0.9434
-2.500 -0.1226 0.02231 0.01212 -0.0113 1.0000 0.9750
-2.250 -0.0501 0.02103 0.01059 -0.0221 1.0000 1.0000
-2.000 -0.0406 0.02039 0.00992 -0.0209 1.0000 1.0000
-1.750 -0.0316 0.01983 0.00935 -0.0194 1.0000 1.0000
-1.500 -0.0233 0.01935 0.00887 -0.0176 1.0000 1.0000
-1.250 -0.0158 0.01894 0.00846 -0.0155 1.0000 1.0000
-1.000 -0.0095 0.01860 0.00814 -0.0131 1.0000 1.0000
-0.750 -0.0044 0.01833 0.00789 -0.0104 1.0000 1.0000
-0.500 -0.0011 0.01812 0.00771 -0.0073 1.0000 1.0000
-0.250 0.0002 0.01800 0.00761 -0.0038 1.0000 1.0000
0.000 0.0000 0.01795 0.00757 0.0000 1.0000 1.0000
0.250 -0.0002 0.01800 0.00761 0.0038 1.0000 1.0000
0.500 0.0011 0.01812 0.00771 0.0073 1.0000 1.0000
0.750 0.0044 0.01832 0.00789 0.0104 1.0000 1.0000
1.000 0.0095 0.01860 0.00814 0.0131 1.0000 1.0000
1.250 0.0158 0.01894 0.00846 0.0155 1.0000 1.0000
1.500 0.0233 0.01935 0.00886 0.0176 1.0000 1.0000
1.750 0.0316 0.01983 0.00935 0.0194 1.0000 1.0000
2.000 0.0406 0.02038 0.00992 0.0209 1.0000 1.0000
2.250 0.0501 0.02102 0.01059 0.0221 1.0000 1.0000
2.500 0.1224 0.02230 0.01211 0.0114 0.9751 1.0000
2.750 0.2075 0.02327 0.01344 -0.0007 0.9434 1.0000
3.000 0.2892 0.02370 0.01426 -0.0111 0.9092 1.0000
3.250 0.3845 0.02344 0.01457 -0.0225 0.8718 1.0000
3.500 0.4623 0.02263 0.01427 -0.0289 0.8286 1.0000
3.750 0.5129 0.02146 0.01340 -0.0284 0.7734 1.0000
4.000 0.5399 0.02081 0.01280 -0.0243 0.7173 1.0000
4.250 0.5594 0.02060 0.01255 -0.0198 0.6596 1.0000
4.500 0.5734 0.02047 0.01229 -0.0146 0.5900 1.0000
4.750 0.5832 0.02063 0.01201 -0.0089 0.5002 1.0000
5.000 0.5880 0.02165 0.01227 -0.0034 0.3747 1.0000
5.250 0.5976 0.02384 0.01347 0.0005 0.2621 1.0000
5.500 0.6167 0.02582 0.01499 0.0025 0.2090 1.0000
5.750 0.6398 0.02770 0.01671 0.0039 0.1806 1.0000
6.000 0.6636 0.02969 0.01878 0.0051 0.1628 1.0000
6.250 0.6861 0.03176 0.02093 0.0064 0.1492 1.0000
6.500 0.7082 0.03410 0.02356 0.0078 0.1407 1.0000
6.750 0.7261 0.03665 0.02645 0.0096 0.1328 1.0000
7.000 0.7433 0.03941 0.02957 0.0113 0.1279 1.0000
7.250 0.7611 0.04256 0.03289 0.0128 0.1248 1.0000
7.500 0.7714 0.04608 0.03687 0.0149 0.1224 1.0000
7.750 0.7757 0.04973 0.04110 0.0173 0.1210 1.0000
8.000 0.7788 0.05378 0.04558 0.0192 0.1212 1.0000
8.250 0.7836 0.05822 0.05027 0.0207 0.1227 1.0000
8.500 0.7585 0.06393 0.05666 0.0223 0.1289 1.0000
8.750 0.7443 0.06947 0.06239 0.0227 0.1337 1.0000
9.000 0.7242 0.07530 0.06836 0.0220 0.1403 1.0000
9.250 0.6869 0.08213 0.07515 0.0196 0.1481 1.0000
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Polar data table (+)
Polar graphs
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