RAF-48 AIRFOIL (raf48-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF-48 AIRFOIL (raf48-il) Reynolds number: 50,000 Max Cl/Cd: 7.42 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf48-il-50000.txt Download as CSV file: xf-raf48-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: RAF-48 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3344 0.11561 0.10831 -0.0274 1.0000 0.3119
-10.000 -0.3001 0.10988 0.10254 -0.0267 1.0000 0.3211
-9.750 -0.3254 0.10925 0.10207 -0.0266 1.0000 0.3305
-9.500 -0.2949 0.10445 0.09722 -0.0259 1.0000 0.3403
-9.250 -0.3028 0.10224 0.09512 -0.0253 1.0000 0.3505
-9.000 -0.3159 0.10121 0.09421 -0.0239 1.0000 0.3644
-8.750 -0.2891 0.09670 0.08970 -0.0232 1.0000 0.3743
-8.500 -0.3060 0.09516 0.08832 -0.0216 1.0000 0.3847
-8.250 -0.2946 0.09225 0.08545 -0.0202 1.0000 0.3942
-8.000 -0.5945 0.07611 0.06985 -0.0296 1.0000 0.1926
-7.750 -0.5990 0.07324 0.06698 -0.0271 1.0000 0.1901
-7.500 -0.6121 0.07010 0.06382 -0.0245 1.0000 0.1873
-7.250 -0.6745 0.06262 0.05569 -0.0219 1.0000 0.1755
-7.000 -0.6783 0.05927 0.05218 -0.0197 1.0000 0.1749
-6.750 -0.6821 0.05586 0.04850 -0.0174 1.0000 0.1745
-6.500 -0.6863 0.05247 0.04468 -0.0149 1.0000 0.1751
-6.250 -0.6781 0.05022 0.04240 -0.0131 1.0000 0.1785
-6.000 -0.6701 0.04820 0.04023 -0.0112 1.0000 0.1820
-5.750 -0.6633 0.04573 0.03742 -0.0092 1.0000 0.1848
-5.500 -0.6557 0.04336 0.03457 -0.0072 1.0000 0.1891
-5.250 -0.6452 0.04134 0.03223 -0.0053 1.0000 0.1947
-5.000 -0.6311 0.04005 0.03087 -0.0038 1.0000 0.2015
-4.750 -0.6189 0.03832 0.02864 -0.0019 1.0000 0.2097
-4.500 -0.6036 0.03728 0.02766 -0.0005 1.0000 0.2193
-4.250 -0.5888 0.03604 0.02622 0.0010 1.0000 0.2303
-4.000 -0.5736 0.03505 0.02502 0.0025 1.0000 0.2443
-3.750 -0.5415 0.03439 0.02439 0.0009 0.9937 0.2656
-3.500 -0.5031 0.03389 0.02372 -0.0017 0.9834 0.2951
-3.250 -0.4674 0.03341 0.02337 -0.0039 0.9729 0.3267
-3.000 -0.4323 0.03306 0.02309 -0.0058 0.9624 0.3640
-2.750 -0.3941 0.03283 0.02314 -0.0081 0.9521 0.4087
-2.500 -0.3581 0.03254 0.02311 -0.0099 0.9412 0.4653
-2.250 -0.3282 0.03211 0.02313 -0.0104 0.9306 0.5404
-2.000 -0.2930 0.03177 0.02385 -0.0100 0.9213 0.6902
-1.750 0.0543 0.03555 0.02724 -0.0615 0.9110 1.0000
-1.500 0.0619 0.03548 0.02698 -0.0611 0.8984 1.0000
-1.250 0.0852 0.03567 0.02695 -0.0624 0.8869 1.0000
-1.000 0.0956 0.03595 0.02706 -0.0613 0.8744 1.0000
-0.750 0.0975 0.03638 0.02735 -0.0587 0.8620 1.0000
-0.500 0.1173 0.03691 0.02771 -0.0586 0.8509 1.0000
-0.250 0.1352 0.03747 0.02811 -0.0581 0.8399 1.0000
0.000 0.1352 0.03818 0.02869 -0.0549 0.8286 1.0000
0.250 0.1727 0.03886 0.02920 -0.0571 0.8194 1.0000
0.500 0.1645 0.03971 0.02993 -0.0526 0.8083 1.0000
0.750 0.1847 0.04057 0.03067 -0.0523 0.7993 1.0000
1.000 0.1920 0.04150 0.03148 -0.0501 0.7900 1.0000
1.250 0.2080 0.04247 0.03234 -0.0492 0.7812 1.0000
1.500 0.2177 0.04349 0.03326 -0.0474 0.7725 1.0000
1.750 0.2362 0.04456 0.03424 -0.0468 0.7648 1.0000
2.000 0.2386 0.04573 0.03532 -0.0443 0.7567 1.0000
2.250 0.2695 0.04677 0.03629 -0.0452 0.7490 1.0000
2.500 0.2610 0.04814 0.03759 -0.0415 0.7418 1.0000
2.750 0.2936 0.04921 0.03860 -0.0427 0.7340 1.0000
3.000 0.2881 0.05069 0.04002 -0.0395 0.7272 1.0000
3.250 0.3017 0.05199 0.04127 -0.0386 0.7199 1.0000
3.500 0.3201 0.05333 0.04257 -0.0382 0.7122 1.0000
3.750 0.3209 0.05487 0.04408 -0.0361 0.7058 1.0000
4.000 0.3555 0.05607 0.04526 -0.0373 0.6966 1.0000
4.250 0.3469 0.05777 0.04693 -0.0345 0.6902 1.0000
4.500 0.3852 0.05892 0.04807 -0.0358 0.6796 1.0000
4.750 0.3740 0.06076 0.04989 -0.0330 0.6730 1.0000
5.000 0.4085 0.06196 0.05110 -0.0338 0.6617 1.0000
5.250 0.4010 0.06385 0.05299 -0.0316 0.6543 1.0000
5.500 0.4269 0.06519 0.05433 -0.0317 0.6428 1.0000
5.750 0.4377 0.06678 0.05595 -0.0308 0.6327 1.0000
6.000 0.4459 0.06856 0.05774 -0.0298 0.6223 1.0000
6.250 0.4726 0.06980 0.05900 -0.0297 0.6091 1.0000
6.500 0.5096 0.07064 0.05990 -0.0301 0.5950 1.0000
6.750 0.4895 0.07338 0.06264 -0.0279 0.5862 1.0000
7.000 0.5080 0.07488 0.06418 -0.0273 0.5730 1.0000
7.250 0.5346 0.07610 0.06546 -0.0271 0.5595 1.0000
7.500 0.5699 0.07680 0.06624 -0.0270 0.5452 1.0000
7.750 0.5455 0.08032 0.06974 -0.0254 0.5358 1.0000
8.000 0.5606 0.08210 0.07158 -0.0248 0.5231 1.0000
8.250 0.5834 0.08342 0.07297 -0.0243 0.5093 1.0000
8.500 0.5986 0.08528 0.07488 -0.0239 0.4979 1.0000
8.750 0.5895 0.08861 0.07824 -0.0232 0.4880 1.0000
9.000 0.6090 0.09032 0.08003 -0.0228 0.4757 1.0000
9.250 0.6076 0.09355 0.08330 -0.0226 0.4677 1.0000
9.500 0.6143 0.09618 0.08598 -0.0223 0.4572 1.0000
9.750 0.5639 0.10604 0.09588 -0.0261 0.4997 1.0000
10.000 0.5813 0.10797 0.09787 -0.0256 0.4824 1.0000
10.250 0.5990 0.11168 0.10165 -0.0264 0.4787 1.0000
10.500 0.6465 0.10827 0.09833 -0.0226 0.4283 1.0000
10.750 0.6518 0.11276 0.10290 -0.0236 0.4296 1.0000
11.000 0.5607 0.12419 0.11428 -0.0294 0.5074 1.0000
11.250 0.5968 0.12872 0.11893 -0.0305 0.4958 1.0000
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