S8052 (11.88%) (s8052-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8052 (11.88%) (s8052-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.54 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8052-il-1000000-n5.txt Download as CSV file: xf-s8052-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8052 (11.88%)
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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8192 0.08842 0.08627 -0.0244 1.0000 0.0053
-14.500 -0.8402 0.07931 0.07706 -0.0297 1.0000 0.0052
-14.250 -0.8754 0.06708 0.06464 -0.0378 1.0000 0.0052
-14.000 -0.9036 0.05699 0.05435 -0.0453 1.0000 0.0052
-13.750 -0.9119 0.05164 0.04889 -0.0492 1.0000 0.0052
-13.500 -0.9296 0.04572 0.04280 -0.0529 1.0000 0.0052
-13.250 -0.9436 0.04116 0.03808 -0.0550 1.0000 0.0052
-13.000 -0.9536 0.03763 0.03439 -0.0558 1.0000 0.0052
-12.750 -0.9670 0.03419 0.03077 -0.0556 1.0000 0.0052
-12.500 -0.9753 0.03164 0.02806 -0.0544 1.0000 0.0052
-12.250 -0.9809 0.02959 0.02586 -0.0523 1.0000 0.0052
-12.000 -0.9828 0.02807 0.02422 -0.0496 1.0000 0.0053
-11.750 -0.9826 0.02662 0.02263 -0.0467 1.0000 0.0053
-11.500 -0.9757 0.02514 0.02100 -0.0447 1.0000 0.0054
-11.250 -0.9635 0.02401 0.01977 -0.0432 1.0000 0.0054
-11.000 -0.9346 0.02256 0.01816 -0.0451 0.9607 0.0055
-10.750 -0.9093 0.02174 0.01721 -0.0457 0.9285 0.0057
-10.500 -0.8934 0.02092 0.01622 -0.0442 0.9019 0.0057
-10.250 -0.8771 0.02006 0.01519 -0.0426 0.8823 0.0058
-9.750 -0.8392 0.01855 0.01340 -0.0404 0.8542 0.0059
-9.500 -0.8186 0.01785 0.01257 -0.0395 0.8437 0.0060
-9.250 -0.7976 0.01716 0.01176 -0.0386 0.8343 0.0061
-9.000 -0.7758 0.01649 0.01099 -0.0378 0.8254 0.0062
-8.750 -0.7533 0.01590 0.01030 -0.0371 0.8175 0.0063
-8.500 -0.7304 0.01532 0.00961 -0.0365 0.8094 0.0064
-8.250 -0.7069 0.01478 0.00899 -0.0359 0.8026 0.0065
-8.000 -0.6831 0.01426 0.00839 -0.0353 0.7960 0.0067
-7.750 -0.6588 0.01380 0.00785 -0.0348 0.7898 0.0068
-7.500 -0.6341 0.01336 0.00733 -0.0344 0.7836 0.0069
-7.250 -0.6091 0.01296 0.00685 -0.0339 0.7774 0.0071
-7.000 -0.5837 0.01259 0.00643 -0.0336 0.7721 0.0072
-6.750 -0.5581 0.01222 0.00601 -0.0332 0.7666 0.0073
-6.500 -0.5323 0.01189 0.00562 -0.0329 0.7616 0.0074
-6.250 -0.5069 0.01146 0.00513 -0.0325 0.7573 0.0076
-6.000 -0.4812 0.01106 0.00468 -0.0322 0.7528 0.0079
-5.750 -0.4549 0.01075 0.00433 -0.0319 0.7484 0.0082
-5.500 -0.4284 0.01048 0.00402 -0.0317 0.7442 0.0085
-5.250 -0.4015 0.01023 0.00374 -0.0315 0.7403 0.0088
-5.000 -0.3744 0.01000 0.00348 -0.0314 0.7360 0.0091
-4.750 -0.3473 0.00979 0.00324 -0.0312 0.7319 0.0096
-4.500 -0.3201 0.00961 0.00302 -0.0311 0.7279 0.0101
-4.250 -0.2928 0.00938 0.00279 -0.0310 0.7235 0.0114
-4.000 -0.2654 0.00919 0.00258 -0.0308 0.7189 0.0129
-3.750 -0.2381 0.00900 0.00239 -0.0307 0.7148 0.0173
-3.500 -0.2111 0.00873 0.00220 -0.0306 0.7111 0.0326
-3.250 -0.1839 0.00848 0.00203 -0.0305 0.7070 0.0519
-3.000 -0.1568 0.00824 0.00187 -0.0304 0.7025 0.0765
-2.750 -0.1299 0.00799 0.00172 -0.0303 0.6980 0.1100
-2.500 -0.1031 0.00766 0.00158 -0.0302 0.6932 0.1592
-2.250 -0.0765 0.00733 0.00145 -0.0301 0.6882 0.2155
-2.000 -0.0501 0.00701 0.00133 -0.0299 0.6835 0.2803
-1.750 -0.0237 0.00663 0.00122 -0.0298 0.6780 0.3579
-1.500 0.0031 0.00635 0.00113 -0.0297 0.6716 0.4222
-1.250 0.0301 0.00611 0.00106 -0.0296 0.6651 0.4792
-1.000 0.0570 0.00588 0.00100 -0.0294 0.6567 0.5395
-0.750 0.0845 0.00575 0.00098 -0.0293 0.6480 0.5839
-0.500 0.1123 0.00570 0.00096 -0.0293 0.6380 0.6118
-0.250 0.1405 0.00567 0.00095 -0.0292 0.6254 0.6324
0.000 0.1685 0.00567 0.00094 -0.0292 0.6112 0.6499
0.250 0.1965 0.00570 0.00095 -0.0292 0.5952 0.6653
0.500 0.2241 0.00576 0.00096 -0.0291 0.5733 0.6779
0.750 0.2514 0.00587 0.00099 -0.0289 0.5463 0.6890
1.000 0.2789 0.00598 0.00103 -0.0289 0.5228 0.6991
1.250 0.3064 0.00609 0.00108 -0.0288 0.5001 0.7089
1.500 0.3336 0.00624 0.00115 -0.0286 0.4728 0.7179
1.750 0.3609 0.00639 0.00122 -0.0286 0.4487 0.7272
2.000 0.3881 0.00652 0.00130 -0.0284 0.4262 0.7362
2.250 0.4150 0.00671 0.00139 -0.0283 0.3987 0.7454
2.500 0.4415 0.00691 0.00150 -0.0281 0.3698 0.7555
2.750 0.4684 0.00707 0.00161 -0.0280 0.3466 0.7648
3.000 0.4952 0.00726 0.00173 -0.0278 0.3243 0.7733
3.250 0.5218 0.00745 0.00185 -0.0276 0.2997 0.7803
3.500 0.5481 0.00769 0.00200 -0.0275 0.2734 0.7874
3.750 0.5740 0.00794 0.00215 -0.0272 0.2465 0.7944
4.000 0.6004 0.00815 0.00230 -0.0270 0.2270 0.8020
4.250 0.6269 0.00832 0.00244 -0.0268 0.2127 0.8093
4.500 0.6532 0.00852 0.00260 -0.0266 0.1974 0.8180
4.750 0.6792 0.00871 0.00276 -0.0263 0.1833 0.8270
5.000 0.7054 0.00888 0.00293 -0.0261 0.1726 0.8364
5.250 0.7311 0.00908 0.00311 -0.0258 0.1607 0.8470
5.500 0.7564 0.00928 0.00330 -0.0254 0.1485 0.8590
5.750 0.7815 0.00947 0.00349 -0.0249 0.1381 0.8733
6.000 0.8063 0.00963 0.00368 -0.0244 0.1296 0.8901
6.500 0.8551 0.00998 0.00411 -0.0232 0.1127 0.9423
6.750 0.8903 0.01025 0.00437 -0.0250 0.1030 0.9737
7.000 0.9245 0.01057 0.00464 -0.0267 0.0939 0.9995
7.250 0.9489 0.01084 0.00489 -0.0262 0.0865 1.0000
7.500 0.9729 0.01113 0.00515 -0.0257 0.0796 1.0000
7.750 0.9964 0.01147 0.00545 -0.0251 0.0721 1.0000
8.000 1.0202 0.01177 0.00574 -0.0246 0.0662 1.0000
8.250 1.0434 0.01213 0.00606 -0.0240 0.0604 1.0000
8.500 1.0671 0.01242 0.00636 -0.0234 0.0567 1.0000
8.750 1.0901 0.01277 0.00671 -0.0228 0.0522 1.0000
9.000 1.1125 0.01316 0.00707 -0.0221 0.0469 1.0000
9.250 1.1344 0.01357 0.00745 -0.0214 0.0421 1.0000
9.500 1.1562 0.01397 0.00784 -0.0206 0.0384 1.0000
9.750 1.1779 0.01435 0.00823 -0.0198 0.0356 1.0000
10.000 1.1987 0.01478 0.00867 -0.0189 0.0330 1.0000
10.250 1.2194 0.01520 0.00910 -0.0180 0.0310 1.0000
10.500 1.2401 0.01558 0.00951 -0.0171 0.0297 1.0000
10.750 1.2599 0.01600 0.00996 -0.0160 0.0283 1.0000
11.000 1.2782 0.01648 0.01045 -0.0148 0.0266 1.0000
11.250 1.2938 0.01699 0.01097 -0.0131 0.0247 1.0000
11.500 1.3093 0.01743 0.01146 -0.0114 0.0240 1.0000
11.750 1.3240 0.01792 0.01198 -0.0096 0.0229 1.0000
12.000 1.3380 0.01846 0.01256 -0.0078 0.0218 1.0000
12.250 1.3509 0.01910 0.01321 -0.0061 0.0205 1.0000
12.500 1.3631 0.01980 0.01395 -0.0044 0.0190 1.0000
12.750 1.3768 0.02046 0.01465 -0.0029 0.0183 1.0000
13.000 1.3890 0.02122 0.01546 -0.0014 0.0169 1.0000
13.250 1.4002 0.02210 0.01636 0.0001 0.0155 1.0000
13.500 1.4109 0.02303 0.01733 0.0015 0.0143 1.0000
13.750 1.4218 0.02399 0.01834 0.0027 0.0133 1.0000
14.000 1.4289 0.02526 0.01963 0.0042 0.0110 1.0000
14.250 1.4353 0.02664 0.02103 0.0055 0.0087 1.0000
14.500 1.4420 0.02805 0.02249 0.0067 0.0074 1.0000
14.750 1.4427 0.03000 0.02448 0.0080 0.0053 1.0000
15.250 1.4500 0.03361 0.02824 0.0097 0.0042 1.0000
15.500 1.4543 0.03547 0.03019 0.0104 0.0040 1.0000
15.750 1.4535 0.03787 0.03267 0.0109 0.0035 1.0000
16.000 1.4574 0.03989 0.03478 0.0113 0.0036 1.0000
16.250 1.4556 0.04258 0.03756 0.0114 0.0033 1.0000
16.500 1.4526 0.04552 0.04060 0.0114 0.0031 1.0000
16.750 1.4502 0.04855 0.04373 0.0110 0.0030 1.0000
17.000 1.4477 0.05176 0.04704 0.0104 0.0030 1.0000
17.250 1.4431 0.05538 0.05078 0.0095 0.0029 1.0000
17.500 1.4370 0.05940 0.05492 0.0082 0.0029 1.0000
17.750 1.4301 0.06373 0.05936 0.0066 0.0029 1.0000
18.000 1.4202 0.06870 0.06445 0.0045 0.0029 1.0000
18.250 1.4083 0.07418 0.07006 0.0020 0.0028 1.0000
18.500 1.3931 0.08043 0.07645 -0.0010 0.0028 1.0000
18.750 1.3759 0.08724 0.08341 -0.0045 0.0028 1.0000
19.000 1.3548 0.09499 0.09130 -0.0086 0.0028 1.0000
19.250 1.3309 0.10348 0.09995 -0.0132 0.0028 1.0000
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Polar data table (+)
Polar graphs
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