RAE 103 AIRFOIL (rae103-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE 103 AIRFOIL (rae103-il) Reynolds number: 100,000 Max Cl/Cd: 40.16 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae103-il-100000.txt Download as CSV file: xf-rae103-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5330 0.09932 0.09466 -0.0130 1.0000 0.1435
-10.000 -0.5234 0.09462 0.08996 -0.0122 1.0000 0.1471
-9.750 -0.6472 0.09474 0.08989 -0.0154 1.0000 0.1433
-9.500 -0.6410 0.09029 0.08546 -0.0147 1.0000 0.1472
-9.250 -0.6357 0.08683 0.08201 -0.0146 1.0000 0.1531
-9.000 -0.6879 0.08070 0.07597 -0.0219 1.0000 0.1570
-8.750 -0.6730 0.07658 0.07189 -0.0205 1.0000 0.1631
-8.500 -0.6919 0.07304 0.06834 -0.0205 1.0000 0.1687
-7.750 -0.7530 0.04746 0.04091 -0.0193 1.0000 0.0728
-7.500 -0.7510 0.04333 0.03572 -0.0148 1.0000 0.0629
-7.250 -0.7378 0.03867 0.03085 -0.0133 1.0000 0.0615
-7.000 -0.7237 0.03536 0.02714 -0.0112 1.0000 0.0610
-6.750 -0.7083 0.03348 0.02471 -0.0087 1.0000 0.0628
-6.500 -0.6906 0.03004 0.02101 -0.0073 1.0000 0.0650
-6.250 -0.6691 0.02770 0.01846 -0.0059 1.0000 0.0668
-6.000 -0.6463 0.02574 0.01635 -0.0047 1.0000 0.0699
-5.750 -0.6247 0.02454 0.01484 -0.0031 1.0000 0.0759
-5.500 -0.6021 0.02246 0.01292 -0.0021 1.0000 0.0829
-5.250 -0.5807 0.02099 0.01139 -0.0006 1.0000 0.0912
-5.000 -0.5633 0.01972 0.01023 0.0013 1.0000 0.1052
-4.750 -0.5489 0.01844 0.00913 0.0037 1.0000 0.1224
-4.500 -0.5378 0.01712 0.00812 0.0067 1.0000 0.1604
-4.250 -0.5400 0.01465 0.00700 0.0113 1.0000 0.3342
-4.000 -0.5440 0.01354 0.00733 0.0183 1.0000 0.6242
-3.750 -0.5335 0.01370 0.00759 0.0228 1.0000 0.6986
-3.500 -0.5209 0.01394 0.00783 0.0270 1.0000 0.7447
-3.250 -0.5086 0.01419 0.00806 0.0311 1.0000 0.7816
-3.000 -0.4956 0.01446 0.00829 0.0350 1.0000 0.8129
-2.750 -0.4815 0.01475 0.00854 0.0388 1.0000 0.8415
-2.500 -0.4644 0.01509 0.00883 0.0420 1.0000 0.8692
-2.250 -0.4329 0.01568 0.00928 0.0427 1.0000 0.8952
-2.000 -0.3773 0.01647 0.00988 0.0388 1.0000 0.9172
-1.750 -0.3158 0.01696 0.01019 0.0327 1.0000 0.9314
-1.500 -0.2658 0.01715 0.01022 0.0279 1.0000 0.9430
-1.250 -0.2168 0.01725 0.01020 0.0229 1.0000 0.9525
-1.000 -0.1710 0.01728 0.01013 0.0183 1.0000 0.9618
-0.750 -0.1303 0.01730 0.01010 0.0143 1.0000 0.9722
-0.500 -0.0874 0.01733 0.01008 0.0098 1.0000 0.9823
-0.250 -0.0412 0.01730 0.01003 0.0046 1.0000 0.9914
0.000 0.0000 0.01732 0.01003 0.0000 1.0000 1.0000
0.250 0.0413 0.01730 0.01003 -0.0046 0.9914 1.0000
0.500 0.0873 0.01732 0.01008 -0.0098 0.9823 1.0000
0.750 0.1301 0.01730 0.01009 -0.0143 0.9722 1.0000
1.000 0.1710 0.01727 0.01013 -0.0183 0.9618 1.0000
1.250 0.2166 0.01725 0.01020 -0.0229 0.9526 1.0000
1.500 0.2662 0.01715 0.01021 -0.0279 0.9430 1.0000
1.750 0.3158 0.01696 0.01019 -0.0327 0.9314 1.0000
2.000 0.3770 0.01647 0.00989 -0.0387 0.9173 1.0000
2.250 0.4328 0.01567 0.00927 -0.0427 0.8950 1.0000
2.500 0.4641 0.01509 0.00882 -0.0419 0.8687 1.0000
2.750 0.4815 0.01475 0.00854 -0.0388 0.8415 1.0000
3.000 0.4956 0.01445 0.00828 -0.0350 0.8127 1.0000
3.250 0.5085 0.01419 0.00805 -0.0311 0.7814 1.0000
3.500 0.5209 0.01394 0.00783 -0.0270 0.7447 1.0000
3.750 0.5334 0.01369 0.00758 -0.0228 0.6983 1.0000
4.000 0.5438 0.01354 0.00733 -0.0182 0.6229 1.0000
4.250 0.5400 0.01464 0.00700 -0.0113 0.3349 1.0000
4.500 0.5377 0.01713 0.00812 -0.0067 0.1603 1.0000
4.750 0.5489 0.01844 0.00913 -0.0037 0.1225 1.0000
5.000 0.5632 0.01973 0.01023 -0.0013 0.1051 1.0000
5.250 0.5808 0.02099 0.01140 0.0006 0.0912 1.0000
5.500 0.6021 0.02246 0.01292 0.0022 0.0829 1.0000
5.750 0.6247 0.02453 0.01483 0.0031 0.0759 1.0000
6.000 0.6463 0.02574 0.01635 0.0047 0.0699 1.0000
6.250 0.6691 0.02769 0.01846 0.0059 0.0669 1.0000
6.500 0.6906 0.03007 0.02103 0.0073 0.0650 1.0000
6.750 0.7083 0.03344 0.02467 0.0087 0.0628 1.0000
7.000 0.7236 0.03536 0.02714 0.0112 0.0609 1.0000
7.250 0.7379 0.03867 0.03083 0.0133 0.0615 1.0000
7.500 0.7512 0.04340 0.03577 0.0148 0.0630 1.0000
7.750 0.7530 0.04752 0.04098 0.0193 0.0729 1.0000
9.500 0.6427 0.09026 0.08543 0.0149 0.1471 1.0000
9.750 0.6412 0.09523 0.09035 0.0140 0.1430 1.0000
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Polar data table (+)
Polar graphs
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