RAE 103 AIRFOIL (rae103-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE 103 AIRFOIL (rae103-il) Reynolds number: 500,000 Max Cl/Cd: 52.56 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae103-il-500000-n5.txt Download as CSV file: xf-rae103-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.8669 0.07270 0.07025 -0.0233 1.0000 0.0060
-13.000 -0.8990 0.06169 0.05904 -0.0315 1.0000 0.0059
-12.750 -0.9282 0.05386 0.05099 -0.0360 1.0000 0.0059
-12.500 -0.9464 0.04878 0.04571 -0.0379 1.0000 0.0059
-12.250 -0.9730 0.04340 0.04006 -0.0382 1.0000 0.0059
-12.000 -0.9836 0.04031 0.03676 -0.0373 1.0000 0.0060
-11.750 -0.9973 0.03717 0.03337 -0.0351 1.0000 0.0060
-11.500 -1.0061 0.03465 0.03061 -0.0322 1.0000 0.0061
-11.250 -1.0109 0.03259 0.02833 -0.0288 1.0000 0.0062
-11.000 -1.0120 0.03065 0.02615 -0.0255 1.0000 0.0064
-10.750 -1.0069 0.02877 0.02401 -0.0230 1.0000 0.0065
-10.500 -0.9978 0.02716 0.02218 -0.0208 1.0000 0.0066
-10.250 -0.9842 0.02602 0.02085 -0.0192 1.0000 0.0068
-10.000 -0.9752 0.02414 0.01875 -0.0169 1.0000 0.0071
-9.750 -0.9610 0.02291 0.01739 -0.0152 1.0000 0.0073
-9.500 -0.9439 0.02210 0.01649 -0.0139 1.0000 0.0076
-9.250 -0.9267 0.02121 0.01547 -0.0125 1.0000 0.0079
-9.000 -0.9091 0.02032 0.01448 -0.0110 1.0000 0.0082
-8.750 -0.8912 0.01947 0.01352 -0.0096 1.0000 0.0085
-8.500 -0.8735 0.01859 0.01253 -0.0080 1.0000 0.0088
-8.250 -0.8552 0.01783 0.01166 -0.0065 1.0000 0.0092
-8.000 -0.8370 0.01709 0.01082 -0.0050 1.0000 0.0096
-7.750 -0.8180 0.01647 0.01010 -0.0035 1.0000 0.0099
-7.500 -0.8012 0.01563 0.00917 -0.0017 1.0000 0.0104
-7.250 -0.7831 0.01499 0.00849 0.0000 1.0000 0.0110
-7.000 -0.7636 0.01454 0.00800 0.0014 1.0000 0.0118
-6.750 -0.7418 0.01411 0.00754 0.0023 0.9995 0.0128
-6.500 -0.7101 0.01363 0.00699 0.0011 0.9949 0.0140
-6.250 -0.6807 0.01303 0.00634 0.0004 0.9892 0.0151
-6.000 -0.6496 0.01250 0.00577 -0.0007 0.9839 0.0170
-5.750 -0.6190 0.01210 0.00533 -0.0016 0.9772 0.0189
-5.500 -0.5858 0.01170 0.00489 -0.0031 0.9713 0.0217
-5.250 -0.5543 0.01128 0.00448 -0.0041 0.9629 0.0257
-5.000 -0.5204 0.01094 0.00409 -0.0057 0.9552 0.0300
-4.750 -0.4883 0.01058 0.00375 -0.0068 0.9444 0.0379
-4.500 -0.4566 0.01025 0.00343 -0.0078 0.9321 0.0495
-4.250 -0.4267 0.00992 0.00313 -0.0085 0.9175 0.0663
-4.000 -0.3995 0.00956 0.00285 -0.0085 0.9013 0.0944
-3.750 -0.3743 0.00920 0.00259 -0.0082 0.8849 0.1331
-3.250 -0.3285 0.00827 0.00208 -0.0067 0.8550 0.2676
-3.000 -0.3071 0.00771 0.00183 -0.0057 0.8415 0.3614
-2.750 -0.2868 0.00712 0.00162 -0.0044 0.8288 0.4704
-2.500 -0.2643 0.00680 0.00155 -0.0034 0.8170 0.5523
-2.250 -0.2393 0.00669 0.00149 -0.0028 0.8062 0.5891
-2.000 -0.2136 0.00662 0.00143 -0.0023 0.7962 0.6160
-1.750 -0.1874 0.00657 0.00139 -0.0019 0.7868 0.6377
-1.500 -0.1610 0.00653 0.00136 -0.0015 0.7784 0.6558
-1.250 -0.1345 0.00650 0.00133 -0.0012 0.7700 0.6715
-1.000 -0.1078 0.00648 0.00131 -0.0009 0.7617 0.6858
-0.750 -0.0810 0.00647 0.00129 -0.0006 0.7539 0.6986
-0.500 -0.0540 0.00645 0.00128 -0.0004 0.7458 0.7101
-0.250 -0.0271 0.00644 0.00128 -0.0002 0.7379 0.7201
0.000 0.0000 0.00644 0.00127 0.0000 0.7292 0.7292
0.250 0.0271 0.00644 0.00128 0.0002 0.7202 0.7379
0.500 0.0540 0.00645 0.00128 0.0004 0.7101 0.7457
0.750 0.0810 0.00647 0.00129 0.0006 0.6985 0.7540
1.000 0.1078 0.00648 0.00131 0.0009 0.6858 0.7617
1.250 0.1345 0.00650 0.00133 0.0012 0.6717 0.7701
1.500 0.1610 0.00653 0.00136 0.0015 0.6558 0.7784
1.750 0.1874 0.00657 0.00139 0.0019 0.6375 0.7869
2.000 0.2136 0.00662 0.00143 0.0023 0.6160 0.7962
2.250 0.2393 0.00669 0.00148 0.0028 0.5896 0.8062
2.500 0.2643 0.00681 0.00155 0.0034 0.5519 0.8170
2.750 0.2870 0.00711 0.00162 0.0044 0.4720 0.8287
3.000 0.3072 0.00771 0.00183 0.0057 0.3626 0.8415
3.250 0.3286 0.00828 0.00208 0.0067 0.2674 0.8550
3.750 0.3743 0.00921 0.00260 0.0082 0.1326 0.8850
4.000 0.3996 0.00956 0.00285 0.0085 0.0950 0.9013
4.250 0.4268 0.00991 0.00313 0.0085 0.0673 0.9176
4.500 0.4566 0.01025 0.00343 0.0079 0.0494 0.9322
4.750 0.4883 0.01059 0.00375 0.0068 0.0378 0.9444
5.000 0.5203 0.01094 0.00409 0.0057 0.0299 0.9552
5.250 0.5543 0.01128 0.00448 0.0041 0.0257 0.9630
5.500 0.5858 0.01169 0.00489 0.0031 0.0217 0.9713
5.750 0.6189 0.01210 0.00534 0.0016 0.0190 0.9773
6.000 0.6495 0.01250 0.00577 0.0008 0.0170 0.9839
6.250 0.6807 0.01302 0.00633 -0.0003 0.0152 0.9892
6.500 0.7100 0.01365 0.00702 -0.0010 0.0140 0.9949
6.750 0.7416 0.01413 0.00756 -0.0022 0.0129 0.9994
7.000 0.7637 0.01453 0.00800 -0.0014 0.0118 1.0000
7.250 0.7830 0.01500 0.00850 0.0001 0.0112 1.0000
7.500 0.8014 0.01561 0.00915 0.0016 0.0105 1.0000
7.750 0.8182 0.01644 0.01008 0.0035 0.0099 1.0000
8.000 0.8366 0.01713 0.01086 0.0050 0.0096 1.0000
8.250 0.8552 0.01783 0.01166 0.0065 0.0093 1.0000
8.500 0.8732 0.01862 0.01256 0.0081 0.0089 1.0000
8.750 0.8912 0.01947 0.01352 0.0096 0.0085 1.0000
9.000 0.9088 0.02036 0.01453 0.0111 0.0082 1.0000
9.250 0.9265 0.02122 0.01549 0.0125 0.0079 1.0000
9.500 0.9443 0.02202 0.01640 0.0138 0.0076 1.0000
9.750 0.9612 0.02285 0.01731 0.0152 0.0073 1.0000
10.000 0.9751 0.02410 0.01871 0.0169 0.0070 1.0000
10.250 0.9860 0.02572 0.02052 0.0189 0.0067 1.0000
10.500 0.9984 0.02708 0.02209 0.0208 0.0066 1.0000
10.750 1.0077 0.02866 0.02389 0.0229 0.0065 1.0000
11.000 1.0137 0.03044 0.02592 0.0253 0.0063 1.0000
11.250 1.0116 0.03252 0.02825 0.0287 0.0063 1.0000
11.500 1.0071 0.03458 0.03053 0.0320 0.0061 1.0000
11.750 0.9977 0.03715 0.03335 0.0350 0.0061 1.0000
12.000 0.9859 0.04011 0.03655 0.0371 0.0060 1.0000
12.250 0.9710 0.04368 0.04035 0.0382 0.0059 1.0000
12.500 0.9484 0.04860 0.04553 0.0378 0.0059 1.0000
12.750 0.9310 0.05358 0.05070 0.0360 0.0059 1.0000
13.000 0.9022 0.06128 0.05863 0.0316 0.0059 1.0000
13.250 0.8706 0.07200 0.06955 0.0237 0.0061 1.0000
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Polar data table (+)
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