RAE 103 AIRFOIL (rae103-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: RAE 103 AIRFOIL (rae103-il) Reynolds number: 50,000 Max Cl/Cd: 27.08 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae103-il-50000-n5.txt Download as CSV file: xf-rae103-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6510 0.09714 0.08996 -0.0171 1.0000 0.0470
-10.500 -0.6622 0.09001 0.08286 -0.0218 1.0000 0.0465
-10.250 -0.6779 0.08346 0.07632 -0.0260 1.0000 0.0457
-10.000 -0.6976 0.07758 0.07040 -0.0292 1.0000 0.0447
-9.750 -0.7181 0.07275 0.06549 -0.0305 1.0000 0.0442
-9.500 -0.7369 0.06883 0.06146 -0.0297 1.0000 0.0440
-9.250 -0.7508 0.06505 0.05750 -0.0285 1.0000 0.0439
-9.000 -0.7601 0.06134 0.05355 -0.0271 1.0000 0.0443
-8.750 -0.7651 0.05771 0.04963 -0.0254 1.0000 0.0450
-8.500 -0.7664 0.05412 0.04569 -0.0236 1.0000 0.0457
-8.250 -0.7640 0.05053 0.04169 -0.0216 1.0000 0.0462
-8.000 -0.7574 0.04708 0.03781 -0.0197 1.0000 0.0468
-7.750 -0.7472 0.04378 0.03402 -0.0178 1.0000 0.0476
-7.500 -0.7332 0.04076 0.03046 -0.0160 1.0000 0.0491
-7.250 -0.7166 0.03813 0.02750 -0.0146 1.0000 0.0519
-7.000 -0.6980 0.03612 0.02536 -0.0136 1.0000 0.0559
-6.750 -0.6753 0.03389 0.02276 -0.0126 1.0000 0.0592
-6.500 -0.6495 0.03183 0.02034 -0.0116 1.0000 0.0634
-6.250 -0.6276 0.03022 0.01879 -0.0108 1.0000 0.0705
-6.000 -0.6031 0.02864 0.01704 -0.0097 1.0000 0.0780
-5.750 -0.5825 0.02731 0.01563 -0.0083 1.0000 0.0879
-5.500 -0.5647 0.02606 0.01436 -0.0067 1.0000 0.1021
-5.250 -0.5495 0.02470 0.01307 -0.0047 1.0000 0.1193
-5.000 -0.5367 0.02329 0.01190 -0.0025 1.0000 0.1520
-4.750 -0.5272 0.02160 0.01075 -0.0001 1.0000 0.2188
-4.500 -0.5239 0.01964 0.00995 0.0035 1.0000 0.3824
-4.250 -0.5164 0.01907 0.01033 0.0087 1.0000 0.5763
-4.000 -0.5040 0.01915 0.01049 0.0131 1.0000 0.6603
-3.750 -0.4891 0.01938 0.01066 0.0172 1.0000 0.7174
-3.500 -0.4715 0.01972 0.01093 0.0210 1.0000 0.7633
-3.250 -0.4497 0.02008 0.01118 0.0240 1.0000 0.8009
-3.000 -0.4214 0.02042 0.01134 0.0255 1.0000 0.8307
-2.750 -0.3941 0.02055 0.01124 0.0263 1.0000 0.8544
-2.500 -0.3602 0.02064 0.01113 0.0255 1.0000 0.8718
-2.250 -0.3275 0.02064 0.01094 0.0245 1.0000 0.8868
-2.000 -0.2958 0.02058 0.01072 0.0233 1.0000 0.9005
-1.750 -0.2645 0.02050 0.01047 0.0220 1.0000 0.9135
-1.500 -0.2279 0.02044 0.01027 0.0195 1.0000 0.9244
-1.250 -0.1910 0.02036 0.01009 0.0168 1.0000 0.9347
-1.000 -0.1572 0.02030 0.00992 0.0145 1.0000 0.9460
-0.750 -0.1243 0.02025 0.00981 0.0122 1.0000 0.9579
-0.500 -0.0906 0.02022 0.00974 0.0097 1.0000 0.9702
-0.250 -0.0476 0.02019 0.00967 0.0053 0.9953 0.9789
0.000 0.0001 0.02018 0.00965 0.0000 0.9868 0.9868
0.250 0.0477 0.02019 0.00966 -0.0052 0.9789 0.9953
0.500 0.0907 0.02022 0.00974 -0.0097 0.9702 1.0000
0.750 0.1242 0.02025 0.00981 -0.0122 0.9579 1.0000
1.000 0.1572 0.02030 0.00992 -0.0145 0.9461 1.0000
1.250 0.1910 0.02036 0.01009 -0.0168 0.9347 1.0000
1.500 0.2280 0.02044 0.01027 -0.0195 0.9244 1.0000
1.750 0.2645 0.02050 0.01047 -0.0220 0.9135 1.0000
2.000 0.2958 0.02058 0.01072 -0.0233 0.9005 1.0000
2.250 0.3275 0.02064 0.01094 -0.0244 0.8868 1.0000
2.500 0.3603 0.02064 0.01113 -0.0255 0.8718 1.0000
2.750 0.3940 0.02055 0.01124 -0.0263 0.8543 1.0000
3.000 0.4214 0.02042 0.01134 -0.0254 0.8307 1.0000
3.250 0.4497 0.02008 0.01118 -0.0240 0.8009 1.0000
3.500 0.4715 0.01972 0.01093 -0.0210 0.7633 1.0000
3.750 0.4891 0.01937 0.01066 -0.0171 0.7173 1.0000
4.000 0.5040 0.01915 0.01049 -0.0130 0.6601 1.0000
4.250 0.5164 0.01907 0.01033 -0.0087 0.5765 1.0000
4.500 0.5238 0.01964 0.00995 -0.0035 0.3819 1.0000
4.750 0.5271 0.02161 0.01075 0.0001 0.2182 1.0000
5.000 0.5367 0.02330 0.01191 0.0025 0.1516 1.0000
5.250 0.5495 0.02471 0.01306 0.0047 0.1189 1.0000
5.500 0.5647 0.02605 0.01436 0.0067 0.1020 1.0000
5.750 0.5825 0.02732 0.01564 0.0083 0.0878 1.0000
6.000 0.6031 0.02865 0.01704 0.0097 0.0779 1.0000
6.250 0.6277 0.03023 0.01879 0.0108 0.0707 1.0000
6.500 0.6495 0.03186 0.02036 0.0116 0.0632 1.0000
6.750 0.6753 0.03388 0.02275 0.0126 0.0593 1.0000
7.000 0.6981 0.03612 0.02536 0.0136 0.0558 1.0000
7.250 0.7167 0.03812 0.02749 0.0147 0.0520 1.0000
7.500 0.7332 0.04075 0.03045 0.0160 0.0491 1.0000
7.750 0.7472 0.04381 0.03405 0.0178 0.0476 1.0000
8.000 0.7575 0.04707 0.03779 0.0197 0.0468 1.0000
8.250 0.7640 0.05055 0.04172 0.0216 0.0462 1.0000
8.500 0.7666 0.05411 0.04568 0.0236 0.0458 1.0000
8.750 0.7652 0.05775 0.04967 0.0254 0.0451 1.0000
9.000 0.7601 0.06138 0.05360 0.0270 0.0444 1.0000
9.250 0.7508 0.06512 0.05758 0.0285 0.0440 1.0000
9.500 0.7368 0.06887 0.06150 0.0297 0.0439 1.0000
9.750 0.7176 0.07287 0.06561 0.0304 0.0442 1.0000
10.000 0.6978 0.07763 0.07044 0.0291 0.0447 1.0000
10.250 0.6787 0.08346 0.07632 0.0260 0.0458 1.0000
10.500 0.6623 0.09013 0.08298 0.0216 0.0464 1.0000
10.750 0.6523 0.09702 0.08984 0.0172 0.0472 1.0000
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Polar data table (+)
Polar graphs
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