S8025 (8%) (s8025-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8025 (8%) (s8025-il) Reynolds number: 1,000,000 Max Cl/Cd: 77.99 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8025-il-1000000-n5.txt Download as CSV file: xf-s8025-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8025 (8%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.8858 0.08045 0.07867 0.0123 1.0000 0.0022
-11.750 -0.9282 0.06634 0.06448 0.0039 1.0000 0.0022
-11.500 -0.9597 0.05168 0.04964 -0.0080 1.0000 0.0022
-11.250 -0.9784 0.04397 0.04176 -0.0159 1.0000 0.0022
-11.000 -1.0058 0.03941 0.03700 -0.0160 1.0000 0.0022
-10.750 -1.0135 0.03576 0.03309 -0.0153 1.0000 0.0022
-10.500 -1.0136 0.03235 0.02940 -0.0145 1.0000 0.0022
-10.250 -1.0071 0.02943 0.02619 -0.0136 1.0000 0.0022
-10.000 -0.9967 0.02679 0.02327 -0.0127 1.0000 0.0022
-9.750 -0.9817 0.02474 0.02097 -0.0118 1.0000 0.0022
-9.500 -0.9649 0.02281 0.01880 -0.0110 1.0000 0.0022
-9.250 -0.9461 0.02117 0.01693 -0.0102 1.0000 0.0022
-9.000 -0.9260 0.01971 0.01527 -0.0095 1.0000 0.0022
-8.750 -0.9046 0.01845 0.01383 -0.0088 1.0000 0.0022
-8.500 -0.8825 0.01729 0.01252 -0.0081 1.0000 0.0022
-8.250 -0.8595 0.01630 0.01139 -0.0075 1.0000 0.0022
-8.000 -0.8360 0.01539 0.01035 -0.0070 1.0000 0.0023
-7.750 -0.8119 0.01458 0.00943 -0.0064 1.0000 0.0023
-7.500 -0.7874 0.01386 0.00862 -0.0059 1.0000 0.0023
-7.250 -0.7625 0.01319 0.00785 -0.0054 1.0000 0.0023
-7.000 -0.7373 0.01261 0.00719 -0.0050 1.0000 0.0024
-6.750 -0.7123 0.01192 0.00641 -0.0044 1.0000 0.0025
-6.500 -0.6872 0.01126 0.00566 -0.0039 1.0000 0.0026
-6.250 -0.6614 0.01076 0.00511 -0.0035 1.0000 0.0029
-6.000 -0.6353 0.01037 0.00467 -0.0031 1.0000 0.0031
-5.750 -0.6091 0.01002 0.00429 -0.0027 1.0000 0.0035
-5.500 -0.5827 0.00970 0.00394 -0.0023 1.0000 0.0038
-5.250 -0.5562 0.00942 0.00362 -0.0019 1.0000 0.0041
-5.000 -0.5299 0.00910 0.00329 -0.0015 1.0000 0.0049
-4.750 -0.5035 0.00883 0.00300 -0.0011 1.0000 0.0062
-4.500 -0.4772 0.00854 0.00273 -0.0007 1.0000 0.0100
-4.250 -0.4507 0.00817 0.00244 -0.0004 0.9992 0.0223
-4.000 -0.4139 0.00777 0.00218 -0.0024 0.9719 0.0453
-3.750 -0.3762 0.00759 0.00195 -0.0044 0.8977 0.0654
-3.250 -0.3278 0.00743 0.00160 -0.0025 0.7737 0.1170
-3.000 -0.3016 0.00736 0.00146 -0.0021 0.7323 0.1388
-2.750 -0.2748 0.00731 0.00133 -0.0018 0.6976 0.1565
-2.500 -0.2477 0.00724 0.00122 -0.0015 0.6678 0.1746
-2.000 -0.1936 0.00711 0.00103 -0.0010 0.6000 0.2231
-1.750 -0.1664 0.00708 0.00094 -0.0008 0.5664 0.2460
-1.500 -0.1392 0.00702 0.00087 -0.0006 0.5357 0.2743
-1.250 -0.1120 0.00692 0.00081 -0.0005 0.5079 0.3123
-0.750 -0.0573 0.00677 0.00072 -0.0002 0.4619 0.3813
-0.250 -0.0026 0.00665 0.00068 0.0002 0.4183 0.4524
0.000 0.0246 0.00660 0.00067 0.0004 0.3953 0.4949
0.250 0.0518 0.00657 0.00068 0.0005 0.3678 0.5354
0.500 0.0790 0.00654 0.00070 0.0007 0.3457 0.5744
0.750 0.1065 0.00653 0.00072 0.0009 0.3290 0.6050
1.000 0.1338 0.00653 0.00075 0.0011 0.3111 0.6359
1.250 0.1612 0.00654 0.00079 0.0013 0.2932 0.6658
1.500 0.1882 0.00651 0.00084 0.0016 0.2791 0.7045
1.750 0.2150 0.00648 0.00090 0.0020 0.2654 0.7459
2.000 0.2415 0.00647 0.00097 0.0024 0.2497 0.7859
2.250 0.2676 0.00646 0.00104 0.0029 0.2340 0.8269
2.500 0.2928 0.00647 0.00113 0.0037 0.2134 0.8719
2.750 0.3181 0.00648 0.00123 0.0045 0.1976 0.9257
3.250 0.3932 0.00674 0.00143 0.0005 0.1665 0.9905
3.500 0.4269 0.00691 0.00155 -0.0007 0.1541 1.0000
3.750 0.4533 0.00706 0.00167 -0.0003 0.1433 1.0000
4.000 0.4798 0.00722 0.00179 0.0000 0.1334 1.0000
4.250 0.5063 0.00741 0.00194 0.0004 0.1215 1.0000
4.500 0.5327 0.00763 0.00210 0.0007 0.1075 1.0000
4.750 0.5592 0.00786 0.00227 0.0010 0.0953 1.0000
5.000 0.5857 0.00808 0.00245 0.0013 0.0853 1.0000
5.250 0.6122 0.00833 0.00266 0.0016 0.0748 1.0000
5.500 0.6388 0.00857 0.00287 0.0019 0.0654 1.0000
5.750 0.6654 0.00880 0.00309 0.0022 0.0586 1.0000
6.000 0.6919 0.00908 0.00334 0.0025 0.0516 1.0000
6.250 0.7186 0.00931 0.00358 0.0027 0.0472 1.0000
6.500 0.7449 0.00961 0.00386 0.0030 0.0408 1.0000
6.750 0.7713 0.00989 0.00414 0.0033 0.0358 1.0000
7.000 0.7974 0.01025 0.00447 0.0036 0.0291 1.0000
7.250 0.8235 0.01057 0.00479 0.0039 0.0253 1.0000
7.500 0.8496 0.01094 0.00517 0.0042 0.0218 1.0000
7.750 0.8758 0.01124 0.00551 0.0044 0.0205 1.0000
8.000 0.9018 0.01158 0.00588 0.0047 0.0186 1.0000
8.250 0.9274 0.01198 0.00628 0.0050 0.0166 1.0000
8.500 0.9530 0.01238 0.00672 0.0053 0.0150 1.0000
8.750 0.9788 0.01272 0.00713 0.0056 0.0141 1.0000
9.000 1.0042 0.01313 0.00756 0.0059 0.0126 1.0000
9.250 1.0291 0.01360 0.00805 0.0063 0.0109 1.0000
9.500 1.0543 0.01403 0.00853 0.0066 0.0099 1.0000
9.750 1.0790 0.01452 0.00906 0.0069 0.0083 1.0000
10.000 1.1031 0.01510 0.00966 0.0073 0.0067 1.0000
10.250 1.1268 0.01572 0.01032 0.0077 0.0053 1.0000
10.500 1.1502 0.01637 0.01105 0.0082 0.0044 1.0000
10.750 1.1732 0.01705 0.01180 0.0087 0.0038 1.0000
11.000 1.1956 0.01781 0.01263 0.0092 0.0033 1.0000
11.250 1.2173 0.01865 0.01356 0.0097 0.0030 1.0000
11.500 1.2394 0.01938 0.01438 0.0102 0.0028 1.0000
11.750 1.2606 0.02019 0.01530 0.0108 0.0027 1.0000
12.000 1.2810 0.02106 0.01627 0.0114 0.0026 1.0000
12.250 1.3006 0.02200 0.01732 0.0121 0.0024 1.0000
12.500 1.3191 0.02302 0.01847 0.0128 0.0023 1.0000
12.750 1.3362 0.02413 0.01969 0.0135 0.0022 1.0000
13.000 1.3511 0.02541 0.02110 0.0144 0.0021 1.0000
13.250 1.3644 0.02676 0.02257 0.0154 0.0020 1.0000
13.500 1.3725 0.02850 0.02447 0.0166 0.0019 1.0000
13.750 1.3776 0.03029 0.02640 0.0180 0.0018 1.0000
14.000 1.3716 0.03227 0.02853 0.0205 0.0018 1.0000
14.250 1.3551 0.03537 0.03179 0.0215 0.0017 1.0000
14.500 1.3429 0.03954 0.03612 0.0193 0.0017 1.0000
14.750 1.3206 0.04699 0.04377 0.0135 0.0017 1.0000
15.000 1.2984 0.05528 0.05224 0.0074 0.0018 1.0000
15.250 1.2608 0.06631 0.06345 0.0002 0.0018 1.0000
15.500 1.2299 0.07586 0.07313 -0.0055 0.0019 1.0000
15.750 1.1852 0.08811 0.08553 -0.0127 0.0020 1.0000
16.000 1.1413 0.10065 0.09821 -0.0200 0.0021 1.0000
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Polar data table (+)
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