S8025 (8%) (s8025-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8025 (8%) (s8025-il) Reynolds number: 100,000 Max Cl/Cd: 37.18 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8025-il-100000-n5.txt Download as CSV file: xf-s8025-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6969 0.08994 0.08515 0.0133 1.0000 0.0181
-9.500 -0.7065 0.08253 0.07779 0.0089 1.0000 0.0178
-9.250 -0.7201 0.07329 0.06858 0.0022 1.0000 0.0174
-9.000 -0.7407 0.06428 0.05950 -0.0065 1.0000 0.0170
-8.750 -0.7587 0.05823 0.05328 -0.0099 1.0000 0.0166
-8.500 -0.7697 0.05228 0.04698 -0.0119 1.0000 0.0165
-8.250 -0.7721 0.04702 0.04130 -0.0128 1.0000 0.0165
-8.000 -0.7680 0.04222 0.03598 -0.0128 1.0000 0.0167
-7.750 -0.7580 0.03798 0.03120 -0.0124 1.0000 0.0169
-7.500 -0.7433 0.03440 0.02710 -0.0118 1.0000 0.0171
-7.250 -0.7253 0.03131 0.02353 -0.0110 1.0000 0.0176
-7.000 -0.7049 0.02876 0.02056 -0.0102 1.0000 0.0183
-6.750 -0.6830 0.02662 0.01808 -0.0093 1.0000 0.0190
-6.500 -0.6622 0.02454 0.01586 -0.0085 1.0000 0.0202
-6.250 -0.6396 0.02321 0.01439 -0.0079 1.0000 0.0229
-6.000 -0.6159 0.02196 0.01293 -0.0071 1.0000 0.0267
-5.750 -0.5936 0.02048 0.01141 -0.0064 1.0000 0.0316
-5.500 -0.5701 0.01926 0.01014 -0.0057 1.0000 0.0423
-5.250 -0.5465 0.01806 0.00898 -0.0050 1.0000 0.0627
-5.000 -0.5223 0.01716 0.00818 -0.0045 1.0000 0.0915
-4.750 -0.4976 0.01643 0.00749 -0.0041 1.0000 0.1218
-4.500 -0.4728 0.01577 0.00688 -0.0036 1.0000 0.1521
-4.250 -0.4479 0.01514 0.00632 -0.0031 1.0000 0.1824
-4.000 -0.4231 0.01455 0.00584 -0.0026 1.0000 0.2177
-3.750 -0.3981 0.01402 0.00540 -0.0020 1.0000 0.2562
-3.500 -0.3734 0.01351 0.00501 -0.0015 1.0000 0.3022
-3.250 -0.3489 0.01301 0.00470 -0.0008 1.0000 0.3553
-3.000 -0.3246 0.01256 0.00444 -0.0001 1.0000 0.4114
-2.750 -0.3004 0.01214 0.00423 0.0008 1.0000 0.4686
-2.500 -0.2763 0.01177 0.00405 0.0017 1.0000 0.5271
-2.250 -0.2523 0.01145 0.00391 0.0028 1.0000 0.5852
-2.000 -0.2287 0.01116 0.00381 0.0040 1.0000 0.6411
-1.750 -0.2054 0.01091 0.00373 0.0054 1.0000 0.6958
-1.500 -0.1822 0.01068 0.00366 0.0069 1.0000 0.7494
-1.250 -0.1582 0.01049 0.00362 0.0083 1.0000 0.8028
-1.000 -0.1297 0.01036 0.00361 0.0088 1.0000 0.8588
-0.750 -0.0894 0.01028 0.00358 0.0068 1.0000 0.9159
-0.500 -0.0313 0.01026 0.00353 0.0007 0.9711 0.9599
-0.250 0.0316 0.01028 0.00345 -0.0063 0.9138 0.9887
0.000 0.0802 0.01035 0.00334 -0.0101 0.8425 1.0000
0.250 0.1064 0.01051 0.00324 -0.0092 0.7800 1.0000
0.500 0.1292 0.01071 0.00319 -0.0078 0.7282 1.0000
0.750 0.1521 0.01091 0.00317 -0.0065 0.6832 1.0000
1.000 0.1756 0.01112 0.00318 -0.0054 0.6418 1.0000
1.250 0.1994 0.01133 0.00321 -0.0044 0.6035 1.0000
1.500 0.2236 0.01156 0.00327 -0.0034 0.5681 1.0000
1.750 0.2484 0.01179 0.00335 -0.0027 0.5341 1.0000
2.000 0.2732 0.01203 0.00344 -0.0020 0.5015 1.0000
2.250 0.2981 0.01229 0.00356 -0.0013 0.4702 1.0000
2.500 0.3232 0.01257 0.00373 -0.0006 0.4401 1.0000
2.750 0.3484 0.01285 0.00389 0.0000 0.4116 1.0000
3.000 0.3738 0.01314 0.00409 0.0005 0.3850 1.0000
3.250 0.3992 0.01345 0.00432 0.0011 0.3598 1.0000
3.500 0.4246 0.01377 0.00460 0.0016 0.3365 1.0000
3.750 0.4502 0.01411 0.00488 0.0020 0.3133 1.0000
4.000 0.4758 0.01446 0.00520 0.0025 0.2915 1.0000
4.250 0.5012 0.01484 0.00556 0.0029 0.2695 1.0000
4.500 0.5267 0.01523 0.00593 0.0034 0.2487 1.0000
4.750 0.5522 0.01565 0.00633 0.0038 0.2281 1.0000
5.000 0.5775 0.01610 0.00676 0.0042 0.2094 1.0000
5.250 0.6029 0.01657 0.00728 0.0046 0.1914 1.0000
5.500 0.6281 0.01708 0.00782 0.0050 0.1742 1.0000
5.750 0.6530 0.01764 0.00839 0.0054 0.1578 1.0000
6.000 0.6778 0.01824 0.00903 0.0058 0.1431 1.0000
6.250 0.7023 0.01889 0.00969 0.0062 0.1281 1.0000
6.750 0.7506 0.02035 0.01126 0.0070 0.1012 1.0000
7.000 0.7745 0.02116 0.01221 0.0075 0.0902 1.0000
7.250 0.7980 0.02207 0.01322 0.0080 0.0801 1.0000
7.500 0.8207 0.02307 0.01430 0.0085 0.0717 1.0000
7.750 0.8431 0.02417 0.01557 0.0091 0.0652 1.0000
8.000 0.8645 0.02550 0.01703 0.0098 0.0597 1.0000
8.250 0.8862 0.02667 0.01837 0.0103 0.0539 1.0000
8.500 0.9058 0.02825 0.02001 0.0109 0.0501 1.0000
8.750 0.9260 0.03004 0.02216 0.0117 0.0469 1.0000
9.000 0.9450 0.03169 0.02405 0.0123 0.0433 1.0000
9.250 0.9625 0.03326 0.02567 0.0129 0.0402 1.0000
9.500 0.9774 0.03578 0.02861 0.0136 0.0379 1.0000
9.750 0.9898 0.03846 0.03174 0.0143 0.0355 1.0000
10.000 1.0014 0.04055 0.03410 0.0148 0.0328 1.0000
10.250 1.0122 0.04241 0.03604 0.0153 0.0307 1.0000
10.500 1.0139 0.04578 0.03965 0.0157 0.0294 1.0000
10.750 1.0071 0.04963 0.04396 0.0159 0.0284 1.0000
11.000 0.9918 0.05364 0.04826 0.0157 0.0279 1.0000
11.250 0.9726 0.05884 0.05369 0.0126 0.0278 1.0000
11.500 0.9520 0.06573 0.06075 0.0070 0.0283 1.0000
11.750 0.9289 0.07426 0.06941 0.0000 0.0288 1.0000
12.000 0.9050 0.08361 0.07883 -0.0069 0.0294 1.0000
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Polar data table (+)
Polar graphs
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