RAE 104 AIRFOIL (rae104-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE 104 AIRFOIL (rae104-il) Reynolds number: 100,000 Max Cl/Cd: 39.8 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae104-il-100000.txt Download as CSV file: xf-rae104-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6399 0.09188 0.08704 -0.0260 1.0000 0.1351
-9.500 -0.6139 0.08973 0.08486 -0.0207 1.0000 0.1443
-9.250 -0.6470 0.08367 0.07889 -0.0271 1.0000 0.1480
-9.000 -0.6840 0.07976 0.07499 -0.0281 1.0000 0.1488
-8.750 -0.6613 0.07590 0.07118 -0.0267 1.0000 0.1581
-8.250 -0.6904 0.06887 0.06415 -0.0245 1.0000 0.1700
-7.500 -0.7488 0.04837 0.04158 -0.0167 1.0000 0.0826
-7.250 -0.7374 0.04274 0.03541 -0.0135 1.0000 0.0670
-7.000 -0.7276 0.03879 0.03121 -0.0109 1.0000 0.0643
-6.750 -0.7168 0.03544 0.02745 -0.0080 1.0000 0.0620
-6.500 -0.7037 0.03251 0.02405 -0.0051 1.0000 0.0610
-6.250 -0.6881 0.03030 0.02150 -0.0026 1.0000 0.0625
-6.000 -0.6723 0.02871 0.01955 -0.0002 1.0000 0.0662
-5.750 -0.6538 0.02701 0.01748 0.0021 1.0000 0.0680
-5.500 -0.6313 0.02450 0.01493 0.0032 1.0000 0.0712
-5.250 -0.6128 0.02323 0.01359 0.0050 1.0000 0.0776
-5.000 -0.5947 0.02181 0.01218 0.0068 1.0000 0.0857
-4.750 -0.5779 0.02074 0.01104 0.0091 1.0000 0.0947
-4.500 -0.5652 0.01958 0.01004 0.0117 1.0000 0.1097
-4.250 -0.5550 0.01844 0.00909 0.0147 1.0000 0.1316
-4.000 -0.5483 0.01694 0.00812 0.0183 1.0000 0.1938
-3.750 -0.5620 0.01412 0.00777 0.0258 1.0000 0.5714
-3.500 -0.5575 0.01441 0.00852 0.0326 1.0000 0.7509
-3.250 -0.5459 0.01491 0.00898 0.0377 1.0000 0.8095
-3.000 -0.5285 0.01556 0.00955 0.0418 1.0000 0.8523
-2.750 -0.4875 0.01676 0.01056 0.0423 1.0000 0.8919
-2.500 -0.3263 0.01932 0.01249 0.0218 1.0000 0.9301
-2.250 -0.2426 0.01956 0.01244 0.0117 1.0000 0.9466
-2.000 -0.1915 0.01945 0.01217 0.0066 1.0000 0.9592
-1.750 -0.1503 0.01931 0.01192 0.0030 1.0000 0.9704
-1.500 -0.1032 0.01901 0.01151 -0.0018 1.0000 0.9792
-1.250 -0.0625 0.01876 0.01119 -0.0057 1.0000 0.9875
-1.000 -0.0223 0.01854 0.01092 -0.0095 1.0000 0.9955
-0.750 0.0037 0.01842 0.01078 -0.0108 1.0000 1.0000
-0.500 0.0018 0.01851 0.01086 -0.0071 1.0000 1.0000
-0.250 0.0008 0.01855 0.01091 -0.0035 1.0000 1.0000
0.000 0.0000 0.01857 0.01092 0.0000 1.0000 1.0000
0.250 -0.0008 0.01855 0.01091 0.0035 1.0000 1.0000
0.500 -0.0019 0.01850 0.01086 0.0071 1.0000 1.0000
0.750 -0.0037 0.01842 0.01077 0.0108 1.0000 1.0000
1.000 0.0220 0.01853 0.01092 0.0095 0.9955 1.0000
1.250 0.0622 0.01875 0.01119 0.0057 0.9876 1.0000
1.500 0.1032 0.01901 0.01151 0.0018 0.9791 1.0000
1.750 0.1503 0.01930 0.01191 -0.0030 0.9704 1.0000
2.000 0.1919 0.01944 0.01217 -0.0066 0.9591 1.0000
2.250 0.2426 0.01956 0.01243 -0.0116 0.9466 1.0000
2.500 0.3251 0.01932 0.01250 -0.0216 0.9303 1.0000
2.750 0.4874 0.01676 0.01055 -0.0423 0.8919 1.0000
3.000 0.5284 0.01556 0.00954 -0.0418 0.8522 1.0000
3.250 0.5460 0.01491 0.00898 -0.0377 0.8098 1.0000
3.500 0.5576 0.01441 0.00852 -0.0327 0.7513 1.0000
3.750 0.5620 0.01412 0.00777 -0.0258 0.5705 1.0000
4.000 0.5484 0.01694 0.00813 -0.0183 0.1941 1.0000
4.250 0.5550 0.01844 0.00909 -0.0147 0.1318 1.0000
4.500 0.5653 0.01957 0.01003 -0.0117 0.1099 1.0000
4.750 0.5779 0.02075 0.01104 -0.0091 0.0948 1.0000
5.000 0.5947 0.02180 0.01217 -0.0068 0.0860 1.0000
5.250 0.6129 0.02324 0.01360 -0.0050 0.0779 1.0000
5.500 0.6313 0.02449 0.01492 -0.0032 0.0713 1.0000
5.750 0.6539 0.02702 0.01748 -0.0021 0.0680 1.0000
6.000 0.6723 0.02869 0.01953 0.0002 0.0662 1.0000
6.250 0.6883 0.03037 0.02158 0.0026 0.0628 1.0000
6.500 0.7037 0.03252 0.02406 0.0051 0.0610 1.0000
6.750 0.7168 0.03543 0.02744 0.0079 0.0620 1.0000
7.000 0.7275 0.03881 0.03124 0.0110 0.0643 1.0000
7.250 0.7375 0.04276 0.03542 0.0134 0.0670 1.0000
7.500 0.7488 0.04831 0.04152 0.0167 0.0827 1.0000
8.250 0.6908 0.06888 0.06415 0.0245 0.1697 1.0000
8.500 0.6134 0.06362 0.05920 0.0284 0.1767 1.0000
8.750 0.5541 0.06832 0.06388 0.0269 0.1741 1.0000
9.000 0.5363 0.07356 0.06906 0.0246 0.1682 1.0000
9.250 0.5508 0.07754 0.07304 0.0269 0.1628 1.0000
9.500 0.5097 0.08387 0.07926 0.0211 0.1563 1.0000
9.750 0.5566 0.08637 0.08184 0.0276 0.1497 1.0000
10.000 0.4998 0.09316 0.08848 0.0191 0.1463 1.0000
10.250 0.4970 0.09724 0.09254 0.0182 0.1401 1.0000
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Polar data table (+)
Polar graphs
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