RAE 104 AIRFOIL (rae104-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE 104 AIRFOIL (rae104-il) Reynolds number: 1,000,000 Max Cl/Cd: 61.92 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae104-il-1000000-n5.txt Download as CSV file: xf-rae104-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAE 104 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -1.0635 0.05398 0.05165 -0.0414 1.0000 0.0034
-14.500 -1.0754 0.04929 0.04682 -0.0434 1.0000 0.0035
-14.250 -1.0999 0.04367 0.04097 -0.0446 1.0000 0.0035
-14.000 -1.0993 0.04138 0.03859 -0.0446 1.0000 0.0036
-13.750 -1.1078 0.03833 0.03538 -0.0439 1.0000 0.0036
-13.500 -1.1152 0.03560 0.03248 -0.0426 1.0000 0.0036
-13.250 -1.1206 0.03323 0.02993 -0.0408 1.0000 0.0036
-13.000 -1.1245 0.03113 0.02766 -0.0384 1.0000 0.0037
-12.750 -1.1153 0.03023 0.02669 -0.0369 1.0000 0.0039
-12.500 -1.1145 0.02867 0.02496 -0.0342 1.0000 0.0039
-12.250 -1.1139 0.02714 0.02327 -0.0311 1.0000 0.0040
-12.000 -1.1056 0.02632 0.02234 -0.0286 1.0000 0.0041
-11.750 -1.1043 0.02492 0.02077 -0.0249 1.0000 0.0041
-11.500 -1.0934 0.02401 0.01974 -0.0227 1.0000 0.0042
-11.250 -1.0843 0.02274 0.01831 -0.0201 1.0000 0.0043
-11.000 -1.0710 0.02185 0.01729 -0.0182 1.0000 0.0044
-10.750 -1.0581 0.02085 0.01616 -0.0161 1.0000 0.0044
-10.500 -1.0427 0.02009 0.01530 -0.0143 1.0000 0.0045
-10.250 -1.0273 0.01930 0.01439 -0.0125 1.0000 0.0046
-10.000 -1.0109 0.01860 0.01360 -0.0108 1.0000 0.0046
-9.750 -0.9947 0.01787 0.01277 -0.0090 1.0000 0.0047
-9.500 -0.9821 0.01678 0.01153 -0.0065 1.0000 0.0049
-9.250 -0.9660 0.01610 0.01077 -0.0046 1.0000 0.0051
-9.000 -0.9423 0.01543 0.01004 -0.0044 0.9987 0.0054
-8.500 -0.8874 0.01434 0.00884 -0.0053 0.9896 0.0059
-8.250 -0.8579 0.01386 0.00832 -0.0061 0.9852 0.0063
-8.000 -0.8280 0.01339 0.00778 -0.0070 0.9805 0.0067
-7.750 -0.7965 0.01292 0.00725 -0.0082 0.9751 0.0070
-7.500 -0.7630 0.01246 0.00673 -0.0099 0.9700 0.0072
-7.250 -0.7319 0.01182 0.00602 -0.0111 0.9613 0.0081
-7.000 -0.6990 0.01139 0.00556 -0.0126 0.9523 0.0089
-6.750 -0.6679 0.01103 0.00514 -0.0137 0.9404 0.0095
-6.500 -0.6400 0.01074 0.00478 -0.0139 0.9260 0.0103
-6.250 -0.6143 0.01050 0.00447 -0.0136 0.9113 0.0108
-6.000 -0.5905 0.01021 0.00411 -0.0130 0.8974 0.0123
-5.500 -0.5419 0.00979 0.00359 -0.0118 0.8737 0.0155
-5.250 -0.5174 0.00958 0.00332 -0.0112 0.8635 0.0175
-5.000 -0.4931 0.00937 0.00309 -0.0106 0.8540 0.0207
-4.750 -0.4681 0.00919 0.00288 -0.0101 0.8452 0.0240
-4.500 -0.4434 0.00898 0.00268 -0.0096 0.8378 0.0302
-4.250 -0.4183 0.00880 0.00248 -0.0092 0.8306 0.0372
-4.000 -0.3931 0.00862 0.00231 -0.0088 0.8244 0.0466
-3.750 -0.3683 0.00839 0.00213 -0.0083 0.8181 0.0640
-3.500 -0.3434 0.00818 0.00197 -0.0078 0.8126 0.0844
-3.250 -0.3190 0.00789 0.00180 -0.0073 0.8071 0.1185
-3.000 -0.2950 0.00760 0.00164 -0.0067 0.8017 0.1618
-2.750 -0.2715 0.00725 0.00149 -0.0061 0.7968 0.2181
-2.500 -0.2485 0.00685 0.00133 -0.0053 0.7916 0.2897
-2.250 -0.2263 0.00641 0.00117 -0.0045 0.7868 0.3729
-2.000 -0.2045 0.00595 0.00102 -0.0035 0.7825 0.4645
-1.750 -0.1839 0.00543 0.00088 -0.0022 0.7776 0.5708
-1.500 -0.1608 0.00518 0.00086 -0.0013 0.7729 0.6437
-1.250 -0.1346 0.00511 0.00084 -0.0010 0.7684 0.6710
-1.000 -0.1079 0.00506 0.00083 -0.0007 0.7630 0.6895
-0.750 -0.0812 0.00504 0.00082 -0.0005 0.7571 0.7035
-0.500 -0.0540 0.00502 0.00081 -0.0004 0.7503 0.7154
-0.250 -0.0271 0.00502 0.00080 -0.0001 0.7428 0.7257
0.000 0.0000 0.00501 0.00080 0.0000 0.7344 0.7344
0.250 0.0271 0.00502 0.00080 0.0001 0.7256 0.7428
0.500 0.0540 0.00502 0.00081 0.0004 0.7154 0.7503
0.750 0.0812 0.00504 0.00082 0.0005 0.7036 0.7571
1.000 0.1079 0.00506 0.00083 0.0007 0.6892 0.7630
1.250 0.1346 0.00511 0.00084 0.0009 0.6710 0.7684
1.500 0.1608 0.00518 0.00086 0.0013 0.6443 0.7729
1.750 0.1839 0.00543 0.00088 0.0022 0.5709 0.7777
2.000 0.2044 0.00595 0.00102 0.0035 0.4630 0.7825
2.250 0.2265 0.00640 0.00117 0.0044 0.3761 0.7868
2.500 0.2484 0.00686 0.00133 0.0054 0.2866 0.7916
2.750 0.2715 0.00725 0.00148 0.0061 0.2190 0.7968
3.000 0.2949 0.00760 0.00164 0.0067 0.1609 0.8017
3.250 0.3190 0.00790 0.00180 0.0073 0.1179 0.8070
3.500 0.3435 0.00818 0.00197 0.0078 0.0848 0.8125
3.750 0.3683 0.00839 0.00213 0.0083 0.0641 0.8180
4.000 0.3931 0.00862 0.00231 0.0088 0.0469 0.8244
4.250 0.4183 0.00880 0.00248 0.0092 0.0373 0.8306
4.500 0.4434 0.00899 0.00268 0.0096 0.0301 0.8378
4.750 0.4681 0.00919 0.00288 0.0101 0.0241 0.8452
5.000 0.4931 0.00936 0.00309 0.0106 0.0208 0.8540
5.250 0.5175 0.00957 0.00332 0.0112 0.0179 0.8634
5.500 0.5419 0.00978 0.00358 0.0118 0.0155 0.8737
6.000 0.5905 0.01020 0.00410 0.0130 0.0123 0.8975
6.250 0.6143 0.01051 0.00447 0.0137 0.0108 0.9115
6.500 0.6400 0.01074 0.00478 0.0139 0.0103 0.9262
6.750 0.6679 0.01102 0.00515 0.0137 0.0095 0.9405
7.000 0.6990 0.01139 0.00556 0.0126 0.0088 0.9524
7.250 0.7319 0.01182 0.00602 0.0111 0.0080 0.9614
7.500 0.7629 0.01246 0.00673 0.0099 0.0073 0.9700
7.750 0.7966 0.01290 0.00723 0.0083 0.0070 0.9751
8.000 0.8277 0.01340 0.00780 0.0071 0.0067 0.9806
8.250 0.8578 0.01388 0.00833 0.0061 0.0062 0.9852
8.500 0.8872 0.01436 0.00887 0.0053 0.0059 0.9897
9.000 0.9422 0.01544 0.01005 0.0044 0.0053 0.9987
9.250 0.9660 0.01610 0.01078 0.0046 0.0051 1.0000
9.500 0.9822 0.01677 0.01152 0.0065 0.0050 1.0000
9.750 0.9955 0.01779 0.01268 0.0088 0.0047 1.0000
10.000 1.0107 0.01862 0.01362 0.0108 0.0046 1.0000
10.250 1.0256 0.01949 0.01460 0.0127 0.0046 1.0000
10.500 1.0423 0.02013 0.01534 0.0144 0.0045 1.0000
10.750 1.0571 0.02096 0.01629 0.0162 0.0045 1.0000
11.000 1.0699 0.02197 0.01743 0.0183 0.0044 1.0000
11.250 1.0835 0.02283 0.01841 0.0203 0.0043 1.0000
11.500 1.0955 0.02380 0.01950 0.0224 0.0042 1.0000
11.750 1.1049 0.02487 0.02071 0.0248 0.0041 1.0000
12.000 1.1090 0.02605 0.02203 0.0281 0.0041 1.0000
12.250 1.1150 0.02707 0.02319 0.0309 0.0039 1.0000
12.500 1.1150 0.02864 0.02494 0.0341 0.0039 1.0000
12.750 1.1153 0.03026 0.02672 0.0368 0.0038 1.0000
13.000 1.1120 0.03227 0.02891 0.0394 0.0038 1.0000
13.250 1.1168 0.03361 0.03035 0.0410 0.0037 1.0000
13.500 1.1142 0.03573 0.03262 0.0426 0.0036 1.0000
13.750 1.1156 0.03759 0.03459 0.0436 0.0036 1.0000
14.000 1.1098 0.04031 0.03746 0.0444 0.0035 1.0000
14.250 1.0993 0.04382 0.04113 0.0445 0.0035 1.0000
14.500 1.0602 0.05147 0.04909 0.0424 0.0035 1.0000
14.750 1.0519 0.05589 0.05363 0.0401 0.0035 1.0000
15.000 1.0338 0.06293 0.06082 0.0354 0.0034 1.0000
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