RAE 102 AIRFOIL (rae102-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE 102 AIRFOIL (rae102-il) Reynolds number: 100,000 Max Cl/Cd: 39.63 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae102-il-100000.txt Download as CSV file: xf-rae102-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: RAE 102 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 -0.5374 0.10150 0.09681 -0.0056 1.0000 0.1500
-10.000 -0.5223 0.09753 0.09283 -0.0042 1.0000 0.1560
-9.750 -0.5388 0.09282 0.08818 -0.0070 1.0000 0.1635
-9.500 -0.5394 0.08781 0.08320 -0.0075 1.0000 0.1680
-9.250 -0.5345 0.08377 0.07916 -0.0074 1.0000 0.1731
-9.000 -0.5601 0.07779 0.07328 -0.0107 1.0000 0.1815
-8.750 -0.5531 0.07358 0.06907 -0.0102 1.0000 0.1850
-8.250 -0.7931 0.05135 0.04476 -0.0198 1.0000 0.0703
-8.000 -0.7774 0.04679 0.04011 -0.0189 1.0000 0.0660
-7.750 -0.7695 0.04241 0.03532 -0.0170 1.0000 0.0632
-7.500 -0.7586 0.03904 0.03152 -0.0150 1.0000 0.0638
-7.250 -0.7447 0.03606 0.02808 -0.0130 1.0000 0.0648
-7.000 -0.7279 0.03309 0.02466 -0.0112 1.0000 0.0652
-6.750 -0.7084 0.03038 0.02152 -0.0095 1.0000 0.0660
-6.500 -0.6869 0.02825 0.01896 -0.0079 1.0000 0.0680
-6.250 -0.6651 0.02594 0.01657 -0.0070 1.0000 0.0732
-6.000 -0.6417 0.02428 0.01478 -0.0058 1.0000 0.0786
-5.750 -0.6181 0.02246 0.01288 -0.0047 1.0000 0.0847
-5.500 -0.5967 0.02131 0.01168 -0.0034 1.0000 0.0955
-5.250 -0.5773 0.01976 0.01030 -0.0017 1.0000 0.1080
-5.000 -0.5612 0.01839 0.00917 0.0003 1.0000 0.1289
-4.750 -0.5480 0.01689 0.00798 0.0029 1.0000 0.1689
-4.500 -0.5477 0.01425 0.00688 0.0070 1.0000 0.3696
-4.250 -0.5402 0.01362 0.00702 0.0117 1.0000 0.5634
-4.000 -0.5248 0.01359 0.00711 0.0150 1.0000 0.6272
-3.750 -0.5083 0.01363 0.00719 0.0181 1.0000 0.6715
-3.500 -0.4916 0.01367 0.00720 0.0211 1.0000 0.7069
-3.250 -0.4752 0.01370 0.00724 0.0241 1.0000 0.7381
-3.000 -0.4592 0.01375 0.00729 0.0272 1.0000 0.7663
-2.750 -0.4432 0.01381 0.00738 0.0304 1.0000 0.7921
-2.500 -0.4277 0.01388 0.00745 0.0335 1.0000 0.8171
-2.250 -0.4123 0.01396 0.00750 0.0365 1.0000 0.8425
-2.000 -0.3954 0.01406 0.00758 0.0390 1.0000 0.8678
-1.750 -0.3691 0.01427 0.00775 0.0398 1.0000 0.8901
-1.500 -0.3393 0.01443 0.00786 0.0392 1.0000 0.9124
-1.250 -0.2938 0.01471 0.00802 0.0355 1.0000 0.9290
-1.000 -0.2434 0.01496 0.00818 0.0304 1.0000 0.9438
-0.750 -0.1890 0.01519 0.00832 0.0243 1.0000 0.9571
-0.500 -0.1346 0.01538 0.00845 0.0178 1.0000 0.9703
-0.250 -0.0679 0.01552 0.00855 0.0090 0.9949 0.9788
0.000 0.0000 0.01556 0.00856 0.0000 0.9868 0.9868
0.250 0.0681 0.01552 0.00854 -0.0091 0.9788 0.9949
0.500 0.1344 0.01538 0.00845 -0.0178 0.9703 1.0000
0.750 0.1890 0.01519 0.00832 -0.0243 0.9571 1.0000
1.000 0.2433 0.01496 0.00818 -0.0304 0.9439 1.0000
1.250 0.2936 0.01470 0.00802 -0.0354 0.9291 1.0000
1.500 0.3391 0.01443 0.00785 -0.0392 0.9124 1.0000
1.750 0.3689 0.01426 0.00774 -0.0397 0.8901 1.0000
2.000 0.3951 0.01406 0.00758 -0.0390 0.8678 1.0000
2.250 0.4119 0.01395 0.00750 -0.0364 0.8426 1.0000
2.500 0.4273 0.01388 0.00745 -0.0334 0.8173 1.0000
2.750 0.4428 0.01381 0.00737 -0.0303 0.7922 1.0000
3.000 0.4588 0.01375 0.00729 -0.0271 0.7664 1.0000
3.250 0.4748 0.01371 0.00724 -0.0240 0.7382 1.0000
3.500 0.4912 0.01367 0.00720 -0.0210 0.7073 1.0000
3.750 0.5077 0.01362 0.00718 -0.0180 0.6712 1.0000
4.000 0.5243 0.01359 0.00711 -0.0149 0.6273 1.0000
4.250 0.5398 0.01362 0.00702 -0.0116 0.5639 1.0000
4.500 0.5476 0.01423 0.00688 -0.0070 0.3728 1.0000
4.750 0.5477 0.01689 0.00797 -0.0028 0.1691 1.0000
5.000 0.5610 0.01839 0.00917 -0.0003 0.1290 1.0000
5.250 0.5770 0.01975 0.01029 0.0018 0.1082 1.0000
5.500 0.5965 0.02130 0.01167 0.0034 0.0956 1.0000
5.750 0.6179 0.02246 0.01287 0.0047 0.0846 1.0000
6.000 0.6415 0.02428 0.01478 0.0059 0.0786 1.0000
6.250 0.6649 0.02593 0.01655 0.0070 0.0732 1.0000
6.500 0.6868 0.02823 0.01894 0.0079 0.0680 1.0000
6.750 0.7083 0.03039 0.02153 0.0095 0.0659 1.0000
7.000 0.7280 0.03308 0.02465 0.0112 0.0652 1.0000
7.250 0.7448 0.03604 0.02807 0.0130 0.0647 1.0000
7.500 0.7588 0.03894 0.03140 0.0149 0.0633 1.0000
7.750 0.7698 0.04241 0.03532 0.0169 0.0632 1.0000
8.000 0.7778 0.04678 0.04009 0.0188 0.0660 1.0000
8.250 0.7934 0.05140 0.04480 0.0197 0.0703 1.0000
9.000 0.6918 0.08167 0.07698 0.0161 0.1639 1.0000
9.250 0.6480 0.08877 0.08396 0.0078 0.1619 1.0000
9.500 0.7033 0.08979 0.08505 0.0171 0.1508 1.0000
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Polar data table (+)
Polar graphs
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