RAE 101 AIRFOIL (rae101-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE 101 AIRFOIL (rae101-il) Reynolds number: 100,000 Max Cl/Cd: 38.99 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae101-il-100000.txt Download as CSV file: xf-rae101-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: RAE 101 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 -0.6508 0.09807 0.09314 -0.0001 1.0000 0.1572
-9.500 -0.6408 0.09456 0.08962 0.0005 1.0000 0.1612
-9.000 -0.8156 0.06067 0.05478 -0.0223 1.0000 0.0718
-8.750 -0.8073 0.05523 0.04931 -0.0219 1.0000 0.0697
-8.500 -0.8070 0.05077 0.04454 -0.0206 1.0000 0.0687
-8.250 -0.8034 0.04642 0.03980 -0.0190 1.0000 0.0672
-8.000 -0.7967 0.04215 0.03505 -0.0171 1.0000 0.0657
-7.750 -0.7869 0.03803 0.03033 -0.0151 1.0000 0.0642
-7.500 -0.7718 0.03475 0.02656 -0.0133 1.0000 0.0641
-7.250 -0.7532 0.03219 0.02366 -0.0119 1.0000 0.0658
-7.000 -0.7334 0.03022 0.02129 -0.0104 1.0000 0.0697
-6.750 -0.7120 0.02846 0.01905 -0.0089 1.0000 0.0724
-6.500 -0.6883 0.02563 0.01628 -0.0082 1.0000 0.0764
-6.250 -0.6655 0.02429 0.01478 -0.0071 1.0000 0.0838
-6.000 -0.6426 0.02245 0.01302 -0.0061 1.0000 0.0911
-5.750 -0.6207 0.02100 0.01153 -0.0049 1.0000 0.1015
-5.500 -0.6012 0.01964 0.01032 -0.0034 1.0000 0.1169
-5.250 -0.5831 0.01835 0.00915 -0.0015 1.0000 0.1406
-5.000 -0.5698 0.01663 0.00794 0.0008 1.0000 0.1901
-4.750 -0.5645 0.01451 0.00716 0.0043 1.0000 0.3857
-4.500 -0.5495 0.01410 0.00706 0.0072 1.0000 0.4905
-4.250 -0.5313 0.01394 0.00699 0.0095 1.0000 0.5457
-4.000 -0.5123 0.01384 0.00691 0.0118 1.0000 0.5878
-3.750 -0.4928 0.01374 0.00688 0.0140 1.0000 0.6220
-3.500 -0.4734 0.01365 0.00683 0.0163 1.0000 0.6537
-3.250 -0.4542 0.01355 0.00674 0.0185 1.0000 0.6830
-3.000 -0.4353 0.01345 0.00669 0.0208 1.0000 0.7111
-2.750 -0.4169 0.01335 0.00662 0.0232 1.0000 0.7385
-2.500 -0.3992 0.01325 0.00656 0.0257 1.0000 0.7658
-2.250 -0.3819 0.01316 0.00650 0.0283 1.0000 0.7929
-2.000 -0.3642 0.01310 0.00649 0.0307 1.0000 0.8189
-1.750 -0.3452 0.01307 0.00651 0.0328 1.0000 0.8457
-1.500 -0.3222 0.01312 0.00657 0.0340 1.0000 0.8739
-1.250 -0.2902 0.01325 0.00667 0.0333 1.0000 0.9020
-1.000 -0.2458 0.01346 0.00685 0.0299 1.0000 0.9282
-0.750 -0.1880 0.01372 0.00703 0.0237 1.0000 0.9485
-0.500 -0.1245 0.01392 0.00717 0.0161 1.0000 0.9660
-0.250 -0.0611 0.01404 0.00726 0.0082 1.0000 0.9838
0.000 0.0000 0.01406 0.00725 0.0000 1.0000 1.0000
0.250 0.0611 0.01404 0.00725 -0.0082 0.9838 1.0000
0.500 0.1244 0.01392 0.00717 -0.0161 0.9660 1.0000
0.750 0.1878 0.01372 0.00703 -0.0237 0.9486 1.0000
1.000 0.2457 0.01346 0.00684 -0.0299 0.9282 1.0000
1.250 0.2900 0.01325 0.00667 -0.0333 0.9020 1.0000
1.500 0.3221 0.01311 0.00657 -0.0340 0.8739 1.0000
1.750 0.3451 0.01307 0.00650 -0.0328 0.8458 1.0000
2.000 0.3640 0.01309 0.00649 -0.0307 0.8190 1.0000
2.250 0.3818 0.01315 0.00649 -0.0282 0.7930 1.0000
2.500 0.3990 0.01325 0.00656 -0.0257 0.7659 1.0000
2.750 0.4168 0.01335 0.00662 -0.0232 0.7386 1.0000
3.000 0.4351 0.01345 0.00668 -0.0208 0.7111 1.0000
3.250 0.4540 0.01355 0.00674 -0.0185 0.6831 1.0000
3.500 0.4732 0.01365 0.00682 -0.0162 0.6536 1.0000
3.750 0.4927 0.01374 0.00688 -0.0140 0.6221 1.0000
4.000 0.5122 0.01384 0.00691 -0.0118 0.5879 1.0000
4.250 0.5311 0.01394 0.00698 -0.0095 0.5457 1.0000
4.500 0.5494 0.01409 0.00706 -0.0072 0.4905 1.0000
4.750 0.5644 0.01451 0.00716 -0.0043 0.3857 1.0000
5.000 0.5697 0.01663 0.00794 -0.0008 0.1902 1.0000
5.250 0.5830 0.01835 0.00916 0.0015 0.1408 1.0000
5.500 0.6011 0.01965 0.01032 0.0034 0.1167 1.0000
5.750 0.6207 0.02100 0.01153 0.0049 0.1015 1.0000
6.000 0.6426 0.02245 0.01302 0.0062 0.0912 1.0000
6.250 0.6655 0.02428 0.01478 0.0071 0.0837 1.0000
6.500 0.6883 0.02563 0.01628 0.0082 0.0764 1.0000
6.750 0.7120 0.02847 0.01905 0.0088 0.0724 1.0000
7.000 0.7335 0.03026 0.02132 0.0104 0.0699 1.0000
7.250 0.7533 0.03222 0.02369 0.0119 0.0659 1.0000
7.500 0.7719 0.03474 0.02655 0.0133 0.0641 1.0000
7.750 0.7870 0.03802 0.03032 0.0150 0.0641 1.0000
8.000 0.7969 0.04214 0.03504 0.0171 0.0658 1.0000
8.250 0.8037 0.04644 0.03981 0.0189 0.0675 1.0000
8.500 0.8072 0.05077 0.04454 0.0205 0.0687 1.0000
8.750 0.8084 0.05527 0.04934 0.0218 0.0700 1.0000
9.000 0.7897 0.06317 0.05781 0.0229 0.0833 1.0000
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Polar data table (+)
Polar graphs
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