RAE 103 AIRFOIL (rae103-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE 103 AIRFOIL (rae103-il) Reynolds number: 1,000,000 Max Cl/Cd: 66 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae103-il-1000000-n5.txt Download as CSV file: xf-rae103-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAE 103 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
------ -------- --------- --------- -------- -------- --------
-15.500 -0.9789 0.09057 0.08867 -0.0117 1.0000 0.0041
-15.250 -1.0544 0.06810 0.06590 -0.0259 1.0000 0.0039
-15.000 -1.0880 0.05795 0.05553 -0.0327 1.0000 0.0038
-14.750 -1.1005 0.05261 0.05006 -0.0356 1.0000 0.0039
-14.500 -1.1243 0.04637 0.04360 -0.0383 1.0000 0.0039
-14.250 -1.1338 0.04252 0.03959 -0.0393 1.0000 0.0039
-14.000 -1.1384 0.03953 0.03646 -0.0395 1.0000 0.0040
-13.750 -1.1499 0.03612 0.03286 -0.0390 1.0000 0.0040
-13.500 -1.1534 0.03376 0.03034 -0.0379 1.0000 0.0040
-13.250 -1.1574 0.03154 0.02796 -0.0362 1.0000 0.0040
-13.000 -1.1556 0.02995 0.02623 -0.0343 1.0000 0.0041
-12.750 -1.1547 0.02838 0.02451 -0.0319 1.0000 0.0041
-12.500 -1.1499 0.02719 0.02320 -0.0294 1.0000 0.0042
-12.250 -1.1492 0.02577 0.02162 -0.0261 1.0000 0.0042
-12.000 -1.1402 0.02494 0.02068 -0.0237 1.0000 0.0043
-11.750 -1.1303 0.02383 0.01945 -0.0215 1.0000 0.0043
-11.500 -1.1175 0.02287 0.01836 -0.0196 1.0000 0.0043
-11.250 -1.1028 0.02202 0.01740 -0.0180 1.0000 0.0044
-11.000 -1.0939 0.02049 0.01569 -0.0155 1.0000 0.0046
-10.750 -1.0794 0.01950 0.01456 -0.0137 1.0000 0.0047
-10.500 -1.0630 0.01866 0.01364 -0.0122 1.0000 0.0049
-10.250 -1.0449 0.01799 0.01290 -0.0108 1.0000 0.0051
-10.000 -1.0261 0.01740 0.01224 -0.0096 1.0000 0.0052
-9.750 -1.0075 0.01676 0.01153 -0.0082 1.0000 0.0054
-9.500 -0.9881 0.01621 0.01092 -0.0069 1.0000 0.0056
-9.250 -0.9685 0.01569 0.01034 -0.0057 1.0000 0.0058
-9.000 -0.9482 0.01525 0.00983 -0.0045 1.0000 0.0061
-8.750 -0.9281 0.01477 0.00930 -0.0032 1.0000 0.0064
-8.500 -0.9082 0.01428 0.00875 -0.0019 1.0000 0.0065
-8.250 -0.8878 0.01387 0.00829 -0.0007 1.0000 0.0067
-8.000 -0.8680 0.01335 0.00770 0.0006 0.9999 0.0069
-7.750 -0.8385 0.01271 0.00701 -0.0002 0.9969 0.0075
-7.500 -0.8099 0.01226 0.00653 -0.0007 0.9923 0.0081
-7.250 -0.7806 0.01187 0.00610 -0.0014 0.9873 0.0086
-6.750 -0.7177 0.01115 0.00530 -0.0036 0.9771 0.0098
-6.500 -0.6843 0.01073 0.00485 -0.0051 0.9710 0.0108
-6.250 -0.6515 0.01037 0.00448 -0.0065 0.9625 0.0122
-6.000 -0.6173 0.01008 0.00416 -0.0081 0.9522 0.0137
-5.750 -0.5853 0.00980 0.00384 -0.0092 0.9373 0.0151
-5.500 -0.5572 0.00954 0.00354 -0.0094 0.9176 0.0176
-5.250 -0.5313 0.00936 0.00328 -0.0091 0.8974 0.0197
-5.000 -0.5064 0.00918 0.00304 -0.0085 0.8777 0.0234
-4.750 -0.4816 0.00901 0.00283 -0.0079 0.8602 0.0276
-4.500 -0.4567 0.00885 0.00263 -0.0074 0.8447 0.0333
-4.250 -0.4314 0.00869 0.00244 -0.0069 0.8307 0.0402
-4.000 -0.4064 0.00850 0.00225 -0.0064 0.8179 0.0534
-3.750 -0.3812 0.00830 0.00207 -0.0060 0.8063 0.0690
-3.500 -0.3562 0.00808 0.00190 -0.0055 0.7952 0.0929
-3.250 -0.3315 0.00783 0.00173 -0.0050 0.7843 0.1263
-3.000 -0.3069 0.00752 0.00156 -0.0045 0.7741 0.1725
-2.750 -0.2827 0.00718 0.00140 -0.0040 0.7650 0.2292
-2.500 -0.2591 0.00678 0.00124 -0.0034 0.7563 0.3021
-2.250 -0.2356 0.00636 0.00107 -0.0028 0.7484 0.3826
-1.750 -0.1883 0.00562 0.00087 -0.0014 0.7332 0.5457
-1.500 -0.1621 0.00553 0.00083 -0.0010 0.7257 0.5783
-1.250 -0.1353 0.00545 0.00080 -0.0009 0.7183 0.6008
-1.000 -0.1084 0.00541 0.00078 -0.0006 0.7108 0.6193
-0.750 -0.0813 0.00538 0.00077 -0.0005 0.7025 0.6348
-0.500 -0.0542 0.00536 0.00076 -0.0003 0.6937 0.6486
-0.250 -0.0272 0.00535 0.00075 -0.0001 0.6835 0.6610
0.000 0.0000 0.00534 0.00075 0.0000 0.6725 0.6725
0.250 0.0272 0.00535 0.00075 0.0001 0.6609 0.6835
0.500 0.0542 0.00536 0.00076 0.0003 0.6485 0.6937
0.750 0.0813 0.00538 0.00077 0.0005 0.6349 0.7025
1.000 0.1085 0.00541 0.00078 0.0006 0.6194 0.7109
1.250 0.1353 0.00545 0.00080 0.0009 0.6008 0.7183
1.750 0.1884 0.00562 0.00087 0.0014 0.5469 0.7332
2.250 0.2356 0.00635 0.00107 0.0027 0.3832 0.7484
2.500 0.2590 0.00679 0.00124 0.0034 0.3000 0.7563
2.750 0.2827 0.00719 0.00140 0.0040 0.2283 0.7650
3.000 0.3068 0.00754 0.00157 0.0046 0.1697 0.7740
3.250 0.3315 0.00783 0.00173 0.0050 0.1261 0.7842
3.500 0.3564 0.00807 0.00190 0.0055 0.0948 0.7951
3.750 0.3812 0.00830 0.00207 0.0060 0.0689 0.8063
4.000 0.4063 0.00851 0.00225 0.0065 0.0523 0.8180
4.250 0.4314 0.00869 0.00243 0.0069 0.0403 0.8307
4.500 0.4567 0.00885 0.00263 0.0074 0.0332 0.8448
4.750 0.4817 0.00901 0.00283 0.0079 0.0276 0.8602
5.000 0.5064 0.00918 0.00304 0.0085 0.0234 0.8776
5.250 0.5313 0.00936 0.00328 0.0091 0.0198 0.8973
5.500 0.5572 0.00954 0.00354 0.0094 0.0176 0.9178
5.750 0.5853 0.00980 0.00384 0.0092 0.0151 0.9373
6.000 0.6173 0.01008 0.00416 0.0081 0.0137 0.9522
6.250 0.6515 0.01037 0.00448 0.0065 0.0122 0.9625
6.500 0.6842 0.01074 0.00486 0.0051 0.0107 0.9711
6.750 0.7176 0.01115 0.00530 0.0036 0.0098 0.9773
7.250 0.7804 0.01187 0.00611 0.0014 0.0087 0.9873
7.500 0.8098 0.01227 0.00654 0.0008 0.0082 0.9922
7.750 0.8382 0.01270 0.00699 0.0002 0.0075 0.9967
8.000 0.8676 0.01330 0.00765 -0.0006 0.0070 0.9997
8.250 0.8878 0.01388 0.00829 0.0007 0.0067 1.0000
8.500 0.9079 0.01431 0.00878 0.0020 0.0066 1.0000
8.750 0.9280 0.01478 0.00931 0.0033 0.0064 1.0000
9.000 0.9486 0.01519 0.00977 0.0044 0.0061 1.0000
9.250 0.9685 0.01568 0.01033 0.0056 0.0058 1.0000
9.500 0.9882 0.01620 0.01091 0.0069 0.0056 1.0000
9.750 1.0078 0.01672 0.01149 0.0081 0.0053 1.0000
10.000 1.0263 0.01737 0.01221 0.0095 0.0052 1.0000
10.250 1.0453 0.01795 0.01286 0.0108 0.0051 1.0000
10.500 1.0633 0.01864 0.01361 0.0121 0.0049 1.0000
10.750 1.0801 0.01943 0.01450 0.0136 0.0047 1.0000
11.000 1.0941 0.02049 0.01567 0.0155 0.0045 1.0000
11.250 1.1051 0.02180 0.01716 0.0177 0.0044 1.0000
11.500 1.1182 0.02283 0.01831 0.0195 0.0044 1.0000
11.750 1.1301 0.02388 0.01949 0.0215 0.0043 1.0000
12.000 1.1413 0.02488 0.02062 0.0235 0.0043 1.0000
12.250 1.1484 0.02587 0.02173 0.0262 0.0042 1.0000
12.500 1.1514 0.02713 0.02313 0.0292 0.0042 1.0000
12.750 1.1569 0.02826 0.02438 0.0316 0.0041 1.0000
13.000 1.1592 0.02972 0.02598 0.0339 0.0041 1.0000
13.250 1.1590 0.03148 0.02789 0.0360 0.0040 1.0000
13.500 1.1548 0.03373 0.03032 0.0377 0.0040 1.0000
13.750 1.1520 0.03602 0.03276 0.0388 0.0040 1.0000
14.000 1.1459 0.03888 0.03577 0.0393 0.0039 1.0000
14.250 1.1384 0.04216 0.03922 0.0392 0.0038 1.0000
14.500 1.1195 0.04718 0.04445 0.0378 0.0039 1.0000
14.750 1.1145 0.05086 0.04826 0.0363 0.0039 1.0000
15.000 1.1001 0.05631 0.05386 0.0334 0.0038 1.0000
15.250 1.0639 0.06659 0.06435 0.0266 0.0039 1.0000
15.500 1.0143 0.08266 0.08067 0.0158 0.0040 1.0000
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