EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Reynolds number: 200,000 Max Cl/Cd: 69.49 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ste87391-il-200000.txt Download as CSV file: xf-ste87391-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5260 0.10468 0.10174 -0.0285 1.0019 0.0767
-8.500 -0.6001 0.09398 0.09120 -0.0359 1.0019 0.0797
-8.000 -0.7163 0.04588 0.04061 -0.0618 0.9964 0.0364
-7.750 -0.6920 0.04189 0.03622 -0.0637 0.9939 0.0351
-7.500 -0.6616 0.03793 0.03152 -0.0663 0.9921 0.0339
-7.250 -0.6301 0.03624 0.02951 -0.0683 0.9907 0.0346
-7.000 -0.6039 0.03471 0.02763 -0.0690 0.9882 0.0358
-6.750 -0.5705 0.03335 0.02589 -0.0707 0.9854 0.0365
-6.500 -0.5352 0.03242 0.02468 -0.0725 0.9838 0.0368
-6.250 -0.5105 0.03123 0.02349 -0.0726 0.9812 0.0375
-6.000 -0.4782 0.03051 0.02278 -0.0740 0.9781 0.0386
-5.750 -0.4406 0.03019 0.02241 -0.0763 0.9762 0.0401
-5.500 -0.4135 0.02948 0.02171 -0.0769 0.9712 0.0422
-5.250 -0.3737 0.02933 0.02153 -0.0798 0.9684 0.0451
-5.000 -0.3424 0.02876 0.02102 -0.0813 0.9630 0.0475
-4.750 -0.2943 0.02843 0.02066 -0.0857 0.9537 0.0526
-4.500 -0.2294 0.02765 0.01998 -0.0930 0.9404 0.0754
-4.250 -0.1851 0.02704 0.02001 -0.0971 0.9327 0.2178
-4.000 -0.1453 0.02724 0.02019 -0.0998 0.9283 0.2421
-3.750 -0.1139 0.02728 0.02024 -0.1009 0.9213 0.2641
-3.500 -0.0773 0.02739 0.02038 -0.1030 0.9168 0.2877
-3.250 -0.0333 0.02760 0.02061 -0.1064 0.9144 0.3107
-3.000 -0.0116 0.02742 0.02044 -0.1057 0.9061 0.3276
-2.750 0.0288 0.02741 0.02048 -0.1084 0.9029 0.3497
-2.500 0.0733 0.02740 0.02059 -0.1120 0.9011 0.3769
-2.250 0.0944 0.02712 0.02045 -0.1113 0.8924 0.4078
-2.000 0.1372 0.02683 0.02053 -0.1147 0.8898 0.4836
-1.750 0.1761 0.02659 0.02107 -0.1164 0.8878 0.6430
-1.500 0.1876 0.02681 0.02145 -0.1127 0.8784 0.7188
-1.250 0.2214 0.02706 0.02164 -0.1132 0.8748 0.7569
-1.000 0.2444 0.02727 0.02182 -0.1117 0.8685 0.7784
-0.750 0.2680 0.02734 0.02186 -0.1103 0.8621 0.7959
-0.500 0.3014 0.02729 0.02178 -0.1105 0.8593 0.8120
-0.250 0.3178 0.02734 0.02181 -0.1081 0.8502 0.8256
0.000 0.3469 0.02709 0.02155 -0.1075 0.8461 0.8379
0.250 0.3805 0.02671 0.02113 -0.1075 0.8438 0.8496
0.500 0.3951 0.02660 0.02102 -0.1049 0.8334 0.8608
0.750 0.4272 0.02601 0.02041 -0.1047 0.8302 0.8715
1.000 0.4614 0.02531 0.01970 -0.1049 0.8276 0.8810
1.250 0.4783 0.02505 0.01944 -0.1027 0.8168 0.8907
1.500 0.5100 0.02416 0.01855 -0.1023 0.8142 0.8997
1.750 0.5270 0.02393 0.01832 -0.1002 0.8037 0.9085
2.000 0.5564 0.02307 0.01747 -0.0996 0.8003 0.9175
2.250 0.5873 0.02207 0.01649 -0.0991 0.7981 0.9281
2.500 0.5906 0.02167 0.01612 -0.0939 0.7861 0.9445
2.750 0.6108 0.02039 0.01487 -0.0909 0.7832 0.9700
3.000 0.6335 0.01989 0.01442 -0.0900 0.7717 0.9981
3.250 0.6740 0.01905 0.01359 -0.0920 0.7685 0.9981
3.500 0.7165 0.01810 0.01266 -0.0943 0.7660 0.9981
3.750 0.7418 0.01795 0.01254 -0.0941 0.7532 0.9981
4.000 0.7774 0.01736 0.01197 -0.0954 0.7442 0.9981
4.250 0.8167 0.01663 0.01125 -0.0972 0.7345 0.9981
4.500 0.8534 0.01611 0.01075 -0.0987 0.7200 0.9981
4.750 0.8948 0.01544 0.01006 -0.1009 0.7032 0.9981
5.000 0.9378 0.01484 0.00939 -0.1034 0.6816 0.9981
5.250 0.9769 0.01453 0.00898 -0.1053 0.6529 0.9981
5.500 1.0104 0.01454 0.00879 -0.1064 0.6180 0.9981
5.750 1.0349 0.01491 0.00897 -0.1061 0.5801 0.9981
6.000 1.0545 0.01547 0.00935 -0.1050 0.5427 0.9981
6.250 1.0717 0.01614 0.00984 -0.1037 0.5064 0.9981
6.500 1.0879 0.01690 0.01041 -0.1022 0.4729 0.9981
6.750 1.1039 0.01768 0.01104 -0.1007 0.4424 0.9981
7.000 1.1209 0.01849 0.01168 -0.0995 0.4167 0.9981
7.250 1.1393 0.01925 0.01233 -0.0986 0.3942 0.9981
7.500 1.1584 0.02000 0.01298 -0.0978 0.3748 0.9981
7.750 1.1784 0.02072 0.01365 -0.0971 0.3580 0.9981
8.000 1.1997 0.02139 0.01432 -0.0967 0.3435 0.9981
8.250 1.2215 0.02209 0.01498 -0.0963 0.3310 0.9981
8.500 1.2432 0.02278 0.01563 -0.0959 0.3197 0.9981
8.750 1.2652 0.02343 0.01634 -0.0956 0.3093 0.9981
9.000 1.2875 0.02414 0.01697 -0.0953 0.2992 0.9981
9.250 1.3066 0.02480 0.01776 -0.0946 0.2895 0.9981
9.500 1.3264 0.02557 0.01844 -0.0939 0.2792 0.9981
9.750 1.3396 0.02631 0.01932 -0.0924 0.2684 0.9981
10.000 1.3531 0.02714 0.02017 -0.0909 0.2567 0.9981
10.250 1.3646 0.02807 0.02103 -0.0892 0.2446 0.9981
10.500 1.3754 0.02893 0.02203 -0.0875 0.2323 0.9981
10.750 1.3868 0.02988 0.02305 -0.0859 0.2201 0.9981
11.000 1.3982 0.03089 0.02407 -0.0843 0.2088 0.9981
11.250 1.4095 0.03193 0.02516 -0.0828 0.1982 0.9981
11.500 1.4216 0.03297 0.02629 -0.0814 0.1856 0.9981
11.750 1.4312 0.03418 0.02755 -0.0798 0.1709 0.9981
12.000 1.4392 0.03557 0.02895 -0.0781 0.1480 0.9981
12.250 1.4342 0.03803 0.03110 -0.0753 0.0994 0.9981
12.500 1.4129 0.04204 0.03464 -0.0711 0.0527 0.9981
12.750 1.3982 0.04571 0.03817 -0.0678 0.0358 0.9981
13.000 1.3917 0.04879 0.04129 -0.0655 0.0298 0.9981
13.250 1.3869 0.05182 0.04441 -0.0637 0.0268 0.9981
13.500 1.3816 0.05501 0.04770 -0.0621 0.0249 0.9981
13.750 1.3761 0.05837 0.05120 -0.0609 0.0235 0.9981
14.000 1.3700 0.06193 0.05487 -0.0599 0.0224 0.9981
14.250 1.3610 0.06594 0.05898 -0.0592 0.0217 0.9981
14.500 1.3543 0.06982 0.06301 -0.0587 0.0210 0.9981
14.750 1.3480 0.07378 0.06710 -0.0585 0.0204 0.9981
15.000 1.3409 0.07793 0.07136 -0.0585 0.0198 0.9981
15.250 1.3337 0.08214 0.07566 -0.0587 0.0194 0.9981
15.500 1.3265 0.08636 0.07993 -0.0590 0.0190 0.9981
15.750 1.3209 0.09034 0.08398 -0.0593 0.0186 0.9981
16.000 1.3184 0.09399 0.08775 -0.0596 0.0182 0.9981
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Polar data table (+)
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