EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Reynolds number: 100,000 Max Cl/Cd: 45.46 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ste87391-il-100000-n5.txt Download as CSV file: xf-ste87391-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER STE 87(-3)-914 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5170 0.08485 0.07977 -0.0776 0.9775 0.0272
-10.750 -0.5404 0.07712 0.07195 -0.0834 0.9753 0.0269
-10.500 -0.5648 0.07126 0.06596 -0.0869 0.9726 0.0267
-10.250 -0.5921 0.06734 0.06194 -0.0866 0.9683 0.0265
-10.000 -0.6177 0.06393 0.05839 -0.0860 0.9642 0.0264
-9.750 -0.6296 0.05942 0.05351 -0.0885 0.9608 0.0266
-9.500 -0.6429 0.05617 0.04994 -0.0867 0.9564 0.0269
-9.000 -0.6323 0.04957 0.04266 -0.0874 0.9504 0.0279
-8.750 -0.6146 0.04700 0.03983 -0.0885 0.9485 0.0285
-8.500 -0.5952 0.04464 0.03717 -0.0893 0.9465 0.0290
-8.250 -0.5826 0.04272 0.03502 -0.0881 0.9434 0.0294
-8.000 -0.5632 0.04092 0.03297 -0.0881 0.9408 0.0299
-7.750 -0.5398 0.03929 0.03109 -0.0885 0.9385 0.0306
-7.500 -0.5138 0.03787 0.02945 -0.0892 0.9367 0.0316
-7.250 -0.4858 0.03674 0.02810 -0.0902 0.9351 0.0332
-7.000 -0.4552 0.03582 0.02694 -0.0914 0.9337 0.0348
-6.750 -0.4375 0.03457 0.02568 -0.0905 0.9302 0.0360
-6.500 -0.4136 0.03361 0.02465 -0.0907 0.9274 0.0371
-6.250 -0.3855 0.03279 0.02373 -0.0916 0.9249 0.0387
-6.000 -0.3544 0.03208 0.02287 -0.0930 0.9229 0.0408
-5.750 -0.3211 0.03149 0.02210 -0.0948 0.9212 0.0435
-5.500 -0.2860 0.03080 0.02133 -0.0971 0.9199 0.0494
-5.250 -0.2660 0.03018 0.02066 -0.0963 0.9154 0.0565
-5.000 -0.2355 0.02928 0.01993 -0.0977 0.9128 0.0815
-4.750 -0.2031 0.02872 0.01979 -0.0996 0.9105 0.1664
-4.500 -0.1697 0.02871 0.01975 -0.1012 0.9083 0.2043
-4.250 -0.1342 0.02878 0.01989 -0.1033 0.9066 0.2468
-4.000 -0.1142 0.02874 0.01982 -0.1024 0.9013 0.2708
-3.750 -0.0855 0.02869 0.01980 -0.1031 0.8978 0.2913
-3.500 -0.0529 0.02864 0.01972 -0.1044 0.8952 0.3076
-3.250 -0.0181 0.02859 0.01964 -0.1060 0.8932 0.3220
-3.000 0.0037 0.02853 0.01959 -0.1053 0.8880 0.3360
-2.750 0.0315 0.02845 0.01954 -0.1057 0.8838 0.3535
-2.500 0.0648 0.02836 0.01951 -0.1070 0.8810 0.3785
-2.250 0.1005 0.02824 0.01950 -0.1088 0.8789 0.4141
-2.000 0.1205 0.02813 0.01956 -0.1079 0.8724 0.4544
-1.750 0.1504 0.02795 0.01967 -0.1085 0.8685 0.5202
-1.500 0.1771 0.02787 0.02002 -0.1076 0.8656 0.6085
-1.250 0.1859 0.02807 0.02044 -0.1031 0.8580 0.6728
-1.000 0.2147 0.02825 0.02055 -0.1031 0.8535 0.7237
-0.750 0.2494 0.02837 0.02057 -0.1042 0.8507 0.7543
-0.500 0.2641 0.02855 0.02073 -0.1017 0.8418 0.7731
-0.250 0.2940 0.02855 0.02066 -0.1017 0.8381 0.7914
0.000 0.3110 0.02864 0.02073 -0.0996 0.8298 0.8056
0.250 0.3384 0.02852 0.02058 -0.0991 0.8250 0.8197
0.500 0.3570 0.02852 0.02055 -0.0972 0.8168 0.8319
0.750 0.3844 0.02830 0.02031 -0.0967 0.8114 0.8443
1.000 0.4031 0.02823 0.02023 -0.0949 0.8026 0.8560
1.250 0.4293 0.02784 0.01982 -0.0939 0.7972 0.8676
1.500 0.4455 0.02767 0.01967 -0.0915 0.7872 0.8797
1.750 0.4696 0.02703 0.01903 -0.0897 0.7822 0.8990
2.000 0.4761 0.02662 0.01867 -0.0849 0.7710 0.9207
2.250 0.4890 0.02596 0.01805 -0.0812 0.7620 0.9453
2.500 0.5159 0.02525 0.01736 -0.0805 0.7545 0.9624
2.750 0.5423 0.02499 0.01712 -0.0804 0.7433 0.9717
3.250 0.6035 0.02398 0.01612 -0.0813 0.7247 0.9981
3.500 0.6319 0.02387 0.01603 -0.0817 0.7125 0.9981
3.750 0.6628 0.02365 0.01582 -0.0824 0.7006 0.9981
4.000 0.6963 0.02329 0.01547 -0.0833 0.6886 0.9981
4.250 0.7311 0.02289 0.01509 -0.0845 0.6758 0.9981
4.500 0.7653 0.02253 0.01472 -0.0855 0.6602 0.9981
4.750 0.8001 0.02219 0.01435 -0.0866 0.6422 0.9981
5.000 0.8371 0.02177 0.01391 -0.0880 0.6218 0.9981
5.250 0.8736 0.02146 0.01352 -0.0893 0.5979 0.9981
5.500 0.9094 0.02126 0.01320 -0.0906 0.5713 0.9981
5.750 0.9414 0.02130 0.01314 -0.0914 0.5421 0.9981
6.000 0.9698 0.02154 0.01327 -0.0917 0.5130 0.9981
6.250 0.9955 0.02193 0.01354 -0.0917 0.4851 0.9981
6.500 1.0193 0.02242 0.01392 -0.0915 0.4588 0.9981
7.000 1.0629 0.02361 0.01495 -0.0905 0.4123 0.9981
7.250 1.0842 0.02424 0.01552 -0.0900 0.3930 0.9981
7.500 1.1052 0.02491 0.01614 -0.0894 0.3758 0.9981
7.750 1.1259 0.02559 0.01681 -0.0888 0.3601 0.9981
8.000 1.1464 0.02628 0.01749 -0.0883 0.3458 0.9981
8.250 1.1672 0.02698 0.01820 -0.0877 0.3332 0.9981
8.500 1.1884 0.02768 0.01892 -0.0872 0.3225 0.9981
8.750 1.2089 0.02841 0.01967 -0.0867 0.3127 0.9981
9.000 1.2294 0.02913 0.02048 -0.0861 0.3026 0.9981
9.250 1.2498 0.02988 0.02126 -0.0855 0.2940 0.9981
9.500 1.2697 0.03065 0.02211 -0.0849 0.2855 0.9981
9.750 1.2891 0.03144 0.02297 -0.0842 0.2772 0.9981
10.000 1.3067 0.03228 0.02389 -0.0833 0.2688 0.9981
10.250 1.3230 0.03315 0.02489 -0.0822 0.2599 0.9981
10.500 1.3381 0.03407 0.02583 -0.0810 0.2516 0.9981
10.750 1.3507 0.03505 0.02699 -0.0795 0.2419 0.9981
11.000 1.3615 0.03611 0.02814 -0.0778 0.2323 0.9981
11.250 1.3686 0.03730 0.02937 -0.0758 0.2214 0.9981
11.500 1.3730 0.03863 0.03081 -0.0735 0.2085 0.9981
11.750 1.3748 0.04016 0.03242 -0.0712 0.1933 0.9981
12.000 1.3770 0.04181 0.03416 -0.0692 0.1743 0.9981
12.250 1.3786 0.04367 0.03603 -0.0672 0.1532 0.9981
12.500 1.3810 0.04562 0.03798 -0.0655 0.1313 0.9981
12.750 1.3805 0.04792 0.04023 -0.0637 0.1081 0.9981
13.000 1.3757 0.05073 0.04294 -0.0618 0.0863 0.9981
13.250 1.3685 0.05393 0.04606 -0.0599 0.0675 0.9981
13.500 1.3591 0.05750 0.04960 -0.0582 0.0533 0.9981
13.750 1.3493 0.06129 0.05342 -0.0569 0.0435 0.9981
14.000 1.3384 0.06540 0.05762 -0.0559 0.0366 0.9981
14.500 1.3150 0.07442 0.06690 -0.0552 0.0296 0.9981
14.750 1.3021 0.07943 0.07206 -0.0556 0.0275 0.9981
15.000 1.2871 0.08499 0.07778 -0.0564 0.0262 0.9981
15.250 1.2715 0.09091 0.08383 -0.0578 0.0253 0.9981
15.500 1.2575 0.09680 0.08996 -0.0594 0.0240 0.9981
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