RAE 101 AIRFOIL (rae101-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE 101 AIRFOIL (rae101-il) Reynolds number: 500,000 Max Cl/Cd: 56.36 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae101-il-500000-n5.txt Download as CSV file: xf-rae101-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.9323 0.09329 0.09070 -0.0028 1.0000 0.0072
-14.500 -0.9872 0.07672 0.07387 -0.0131 1.0000 0.0069
-14.250 -1.0136 0.06752 0.06449 -0.0192 1.0000 0.0069
-14.000 -1.0334 0.06017 0.05697 -0.0240 1.0000 0.0069
-13.750 -1.0486 0.05418 0.05080 -0.0277 1.0000 0.0069
-13.500 -1.0647 0.04858 0.04500 -0.0307 1.0000 0.0069
-13.250 -1.0731 0.04456 0.04081 -0.0324 1.0000 0.0070
-13.000 -1.0819 0.04090 0.03698 -0.0333 1.0000 0.0071
-12.750 -1.0873 0.03802 0.03392 -0.0333 1.0000 0.0072
-12.500 -1.0931 0.03538 0.03110 -0.0324 1.0000 0.0073
-12.250 -1.0962 0.03325 0.02879 -0.0307 1.0000 0.0074
-12.000 -1.0986 0.03133 0.02669 -0.0283 1.0000 0.0075
-11.750 -1.0969 0.02985 0.02504 -0.0256 1.0000 0.0076
-11.500 -1.0927 0.02839 0.02341 -0.0231 1.0000 0.0078
-11.250 -1.0835 0.02699 0.02184 -0.0212 1.0000 0.0079
-11.000 -1.0711 0.02579 0.02044 -0.0195 1.0000 0.0081
-10.750 -1.0573 0.02465 0.01915 -0.0179 1.0000 0.0082
-10.500 -1.0461 0.02314 0.01751 -0.0161 1.0000 0.0085
-10.250 -1.0304 0.02209 0.01636 -0.0147 1.0000 0.0088
-10.000 -1.0126 0.02124 0.01543 -0.0135 1.0000 0.0091
-9.750 -0.9940 0.02043 0.01454 -0.0124 1.0000 0.0094
-9.500 -0.9746 0.01970 0.01372 -0.0113 1.0000 0.0098
-9.250 -0.9551 0.01893 0.01284 -0.0102 1.0000 0.0102
-9.000 -0.9349 0.01825 0.01207 -0.0091 1.0000 0.0107
-8.750 -0.9141 0.01762 0.01135 -0.0081 1.0000 0.0112
-8.500 -0.8939 0.01692 0.01057 -0.0070 1.0000 0.0117
-8.250 -0.8739 0.01620 0.00980 -0.0059 1.0000 0.0124
-8.000 -0.8525 0.01565 0.00922 -0.0049 1.0000 0.0131
-7.750 -0.8308 0.01514 0.00863 -0.0039 1.0000 0.0139
-7.500 -0.8091 0.01464 0.00807 -0.0029 1.0000 0.0147
-7.250 -0.7871 0.01418 0.00755 -0.0019 1.0000 0.0154
-7.000 -0.7661 0.01361 0.00694 -0.0007 1.0000 0.0167
-6.750 -0.7440 0.01320 0.00652 0.0002 1.0000 0.0183
-6.500 -0.7216 0.01283 0.00611 0.0012 1.0000 0.0198
-6.250 -0.6989 0.01249 0.00572 0.0021 1.0000 0.0211
-6.000 -0.6773 0.01204 0.00526 0.0033 1.0000 0.0236
-5.750 -0.6548 0.01171 0.00492 0.0042 1.0000 0.0263
-5.500 -0.6324 0.01139 0.00458 0.0053 1.0000 0.0297
-5.250 -0.6032 0.01104 0.00424 0.0047 0.9976 0.0349
-5.000 -0.5701 0.01070 0.00392 0.0034 0.9921 0.0419
-4.750 -0.5371 0.01036 0.00362 0.0021 0.9857 0.0529
-4.500 -0.5043 0.01002 0.00332 0.0009 0.9785 0.0679
-4.250 -0.4700 0.00963 0.00304 -0.0007 0.9710 0.0928
-4.000 -0.4373 0.00921 0.00276 -0.0020 0.9604 0.1283
-3.750 -0.4042 0.00870 0.00247 -0.0035 0.9480 0.1825
-3.500 -0.3718 0.00813 0.00218 -0.0048 0.9317 0.2542
-3.250 -0.3416 0.00764 0.00196 -0.0055 0.9115 0.3339
-3.000 -0.3138 0.00740 0.00182 -0.0055 0.8871 0.3799
-2.750 -0.2873 0.00725 0.00169 -0.0051 0.8626 0.4128
-2.500 -0.2615 0.00715 0.00159 -0.0045 0.8385 0.4411
-2.250 -0.2359 0.00706 0.00150 -0.0040 0.8155 0.4674
-2.000 -0.2103 0.00699 0.00142 -0.0034 0.7935 0.4924
-1.750 -0.1844 0.00693 0.00136 -0.0029 0.7732 0.5167
-1.500 -0.1585 0.00688 0.00130 -0.0024 0.7534 0.5405
-1.250 -0.1325 0.00684 0.00126 -0.0019 0.7346 0.5627
-1.000 -0.1063 0.00680 0.00122 -0.0015 0.7169 0.5840
-0.500 -0.0533 0.00675 0.00118 -0.0007 0.6833 0.6200
-0.250 -0.0267 0.00675 0.00116 -0.0003 0.6665 0.6358
0.000 0.0000 0.00675 0.00116 0.0000 0.6507 0.6507
0.250 0.0267 0.00675 0.00116 0.0003 0.6357 0.6663
0.500 0.0533 0.00675 0.00118 0.0007 0.6200 0.6833
1.000 0.1062 0.00680 0.00122 0.0015 0.5840 0.7169
1.250 0.1325 0.00684 0.00126 0.0019 0.5628 0.7346
1.500 0.1585 0.00688 0.00130 0.0024 0.5404 0.7535
1.750 0.1843 0.00693 0.00136 0.0029 0.5166 0.7731
2.000 0.2102 0.00699 0.00142 0.0034 0.4923 0.7935
2.250 0.2358 0.00706 0.00150 0.0040 0.4676 0.8152
2.500 0.2615 0.00715 0.00159 0.0046 0.4412 0.8384
2.750 0.2872 0.00726 0.00169 0.0051 0.4120 0.8627
3.000 0.3138 0.00740 0.00181 0.0055 0.3799 0.8871
3.250 0.3416 0.00764 0.00196 0.0055 0.3336 0.9115
3.750 0.4041 0.00870 0.00247 0.0035 0.1829 0.9479
4.000 0.4374 0.00921 0.00276 0.0020 0.1283 0.9605
4.250 0.4701 0.00963 0.00304 0.0007 0.0926 0.9711
4.500 0.5044 0.01002 0.00332 -0.0009 0.0679 0.9787
4.750 0.5372 0.01036 0.00362 -0.0021 0.0528 0.9858
5.000 0.5701 0.01070 0.00392 -0.0034 0.0421 0.9921
5.250 0.6033 0.01104 0.00424 -0.0048 0.0349 0.9977
5.500 0.6322 0.01140 0.00458 -0.0052 0.0294 1.0000
5.750 0.6547 0.01170 0.00492 -0.0042 0.0263 1.0000
6.000 0.6771 0.01203 0.00526 -0.0032 0.0237 1.0000
6.250 0.6988 0.01249 0.00571 -0.0021 0.0211 1.0000
6.500 0.7214 0.01283 0.00611 -0.0012 0.0199 1.0000
6.750 0.7439 0.01320 0.00653 -0.0002 0.0183 1.0000
7.000 0.7660 0.01362 0.00695 0.0008 0.0168 1.0000
7.250 0.7870 0.01419 0.00755 0.0019 0.0155 1.0000
7.500 0.8091 0.01464 0.00807 0.0029 0.0147 1.0000
7.750 0.8308 0.01514 0.00863 0.0039 0.0139 1.0000
8.000 0.8524 0.01566 0.00922 0.0049 0.0132 1.0000
8.250 0.8739 0.01621 0.00981 0.0059 0.0125 1.0000
8.500 0.8940 0.01692 0.01057 0.0070 0.0118 1.0000
8.750 0.9141 0.01764 0.01137 0.0081 0.0112 1.0000
9.000 0.9351 0.01825 0.01206 0.0091 0.0107 1.0000
9.250 0.9551 0.01896 0.01287 0.0102 0.0102 1.0000
9.500 0.9747 0.01971 0.01373 0.0113 0.0098 1.0000
9.750 0.9942 0.02045 0.01456 0.0123 0.0094 1.0000
10.000 1.0130 0.02124 0.01542 0.0134 0.0091 1.0000
10.250 1.0308 0.02210 0.01637 0.0146 0.0088 1.0000
10.500 1.0464 0.02316 0.01753 0.0160 0.0085 1.0000
10.750 1.0581 0.02462 0.01912 0.0178 0.0083 1.0000
11.000 1.0720 0.02575 0.02040 0.0193 0.0081 1.0000
11.250 1.0840 0.02700 0.02184 0.0210 0.0079 1.0000
11.500 1.0931 0.02843 0.02344 0.0230 0.0078 1.0000
11.750 1.0976 0.02987 0.02506 0.0255 0.0077 1.0000
12.000 1.0990 0.03138 0.02674 0.0282 0.0075 1.0000
12.250 1.0974 0.03323 0.02876 0.0305 0.0075 1.0000
12.500 1.0948 0.03531 0.03102 0.0322 0.0073 1.0000
12.750 1.0897 0.03787 0.03376 0.0331 0.0071 1.0000
13.000 1.0868 0.04045 0.03650 0.0332 0.0071 1.0000
13.250 1.0778 0.04409 0.04033 0.0324 0.0070 1.0000
13.500 1.0654 0.04866 0.04509 0.0305 0.0069 1.0000
13.750 1.0520 0.05384 0.05046 0.0277 0.0069 1.0000
14.000 1.0349 0.06017 0.05697 0.0237 0.0069 1.0000
14.250 1.0130 0.06789 0.06487 0.0187 0.0069 1.0000
14.500 0.9894 0.07659 0.07374 0.0130 0.0069 1.0000
14.750 0.9510 0.08934 0.08670 0.0049 0.0071 1.0000
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