S8066 (10% version of S8065 w/ lower surface aerodynamically similar) (s8066-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8066 (10% version of S8065 w/ lower surface aerodynamically similar) (s8066-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.22 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8066-il-1000000.txt Download as CSV file: xf-s8066-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S8066 (10% version of S8065 w/ lower surface aer
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.4637 0.14895 0.14744 0.0031 1.0000 0.0091
-14.250 -0.4615 0.14583 0.14432 0.0011 1.0000 0.0092
-9.750 -0.8072 0.03374 0.03085 -0.0442 1.0000 0.0066
-9.500 -0.8046 0.03186 0.02877 -0.0414 1.0000 0.0065
-9.250 -0.7954 0.02843 0.02499 -0.0409 0.9943 0.0064
-9.000 -0.7798 0.02400 0.02007 -0.0416 0.9881 0.0066
-8.750 -0.7546 0.02151 0.01729 -0.0427 0.9843 0.0066
-8.500 -0.7301 0.01943 0.01496 -0.0432 0.9790 0.0067
-8.250 -0.7042 0.01784 0.01316 -0.0437 0.9737 0.0067
-8.000 -0.6794 0.01654 0.01171 -0.0437 0.9681 0.0069
-7.750 -0.6574 0.01546 0.01048 -0.0430 0.9612 0.0069
-7.500 -0.6353 0.01453 0.00942 -0.0421 0.9553 0.0070
-7.250 -0.6139 0.01375 0.00856 -0.0411 0.9492 0.0072
-7.000 -0.5916 0.01313 0.00785 -0.0402 0.9439 0.0074
-6.750 -0.5685 0.01257 0.00721 -0.0395 0.9392 0.0077
-6.500 -0.5457 0.01193 0.00649 -0.0387 0.9343 0.0078
-6.250 -0.5228 0.01136 0.00581 -0.0378 0.9299 0.0079
-6.000 -0.4988 0.01083 0.00521 -0.0371 0.9258 0.0082
-5.750 -0.4742 0.01039 0.00470 -0.0366 0.9215 0.0085
-5.500 -0.4493 0.01001 0.00424 -0.0360 0.9176 0.0090
-5.250 -0.4247 0.00957 0.00371 -0.0354 0.9138 0.0104
-5.000 -0.3988 0.00925 0.00337 -0.0351 0.9099 0.0125
-4.750 -0.3739 0.00881 0.00300 -0.0346 0.9059 0.0280
-4.500 -0.3485 0.00849 0.00275 -0.0342 0.9022 0.0468
-4.250 -0.3227 0.00820 0.00255 -0.0339 0.8985 0.0695
-4.000 -0.2967 0.00791 0.00236 -0.0337 0.8945 0.0970
-3.750 -0.2711 0.00757 0.00217 -0.0334 0.8904 0.1355
-3.500 -0.2459 0.00721 0.00198 -0.0331 0.8866 0.1874
-3.250 -0.2208 0.00678 0.00180 -0.0328 0.8825 0.2577
-3.000 -0.1967 0.00624 0.00162 -0.0324 0.8780 0.3570
-2.750 -0.1718 0.00583 0.00148 -0.0320 0.8739 0.4421
-2.500 -0.1462 0.00553 0.00139 -0.0317 0.8698 0.5118
-2.250 -0.1200 0.00529 0.00131 -0.0315 0.8651 0.5630
-2.000 -0.0932 0.00513 0.00124 -0.0312 0.8606 0.6003
-1.750 -0.0667 0.00498 0.00119 -0.0310 0.8562 0.6415
-1.500 -0.0398 0.00485 0.00117 -0.0307 0.8510 0.6783
-1.250 -0.0126 0.00478 0.00115 -0.0305 0.8459 0.7066
-1.000 0.0150 0.00474 0.00113 -0.0304 0.8406 0.7279
-0.750 0.0425 0.00469 0.00112 -0.0303 0.8341 0.7449
-0.500 0.0701 0.00467 0.00109 -0.0301 0.8278 0.7592
-0.250 0.0978 0.00464 0.00108 -0.0300 0.8198 0.7727
0.000 0.1253 0.00463 0.00107 -0.0299 0.8119 0.7853
0.250 0.1529 0.00460 0.00106 -0.0297 0.8022 0.7965
0.500 0.1804 0.00458 0.00105 -0.0296 0.7913 0.8061
0.750 0.2079 0.00459 0.00104 -0.0294 0.7790 0.8150
1.000 0.2352 0.00459 0.00104 -0.0292 0.7644 0.8229
1.250 0.2624 0.00463 0.00104 -0.0290 0.7472 0.8303
1.500 0.2893 0.00468 0.00106 -0.0288 0.7280 0.8378
1.750 0.3159 0.00476 0.00108 -0.0285 0.7040 0.8451
2.000 0.3422 0.00486 0.00112 -0.0281 0.6772 0.8527
2.250 0.3685 0.00497 0.00118 -0.0278 0.6500 0.8600
2.500 0.3945 0.00510 0.00124 -0.0274 0.6206 0.8679
2.750 0.4204 0.00524 0.00132 -0.0270 0.5907 0.8756
3.000 0.4451 0.00548 0.00143 -0.0264 0.5447 0.8844
3.250 0.4683 0.00581 0.00156 -0.0256 0.4804 0.8935
3.500 0.4909 0.00622 0.00173 -0.0247 0.4082 0.9038
3.750 0.5123 0.00672 0.00195 -0.0237 0.3288 0.9161
4.000 0.5339 0.00719 0.00219 -0.0226 0.2592 0.9305
4.250 0.5568 0.00762 0.00242 -0.0218 0.2017 0.9471
4.500 0.5844 0.00807 0.00268 -0.0220 0.1514 0.9631
4.750 0.6159 0.00856 0.00297 -0.0233 0.1069 0.9759
5.000 0.6489 0.00897 0.00326 -0.0248 0.0772 0.9861
5.250 0.6832 0.00933 0.00353 -0.0265 0.0596 0.9935
5.750 0.7452 0.00995 0.00408 -0.0285 0.0409 1.0000
6.000 0.7667 0.01023 0.00433 -0.0274 0.0357 1.0000
6.250 0.7889 0.01051 0.00461 -0.0264 0.0309 1.0000
6.500 0.8117 0.01078 0.00486 -0.0256 0.0265 1.0000
6.750 0.8346 0.01111 0.00517 -0.0248 0.0208 1.0000
7.000 0.8564 0.01157 0.00559 -0.0238 0.0140 1.0000
7.250 0.8781 0.01210 0.00613 -0.0228 0.0113 1.0000
7.500 0.9008 0.01250 0.00658 -0.0220 0.0104 1.0000
7.750 0.9233 0.01296 0.00707 -0.0212 0.0097 1.0000
8.000 0.9450 0.01349 0.00764 -0.0202 0.0089 1.0000
8.250 0.9626 0.01449 0.00876 -0.0186 0.0081 1.0000
8.500 0.9830 0.01516 0.00951 -0.0175 0.0079 1.0000
8.750 1.0038 0.01579 0.01023 -0.0164 0.0077 1.0000
9.000 1.0247 0.01637 0.01088 -0.0155 0.0073 1.0000
9.250 1.0445 0.01708 0.01166 -0.0143 0.0070 1.0000
9.500 1.0636 0.01783 0.01249 -0.0131 0.0068 1.0000
9.750 1.0811 0.01873 0.01350 -0.0117 0.0066 1.0000
10.000 1.0988 0.01957 0.01442 -0.0104 0.0064 1.0000
10.250 1.1148 0.02058 0.01553 -0.0088 0.0062 1.0000
10.500 1.1298 0.02161 0.01667 -0.0071 0.0061 1.0000
10.750 1.1431 0.02275 0.01793 -0.0053 0.0060 1.0000
11.000 1.1524 0.02406 0.01938 -0.0028 0.0059 1.0000
11.250 1.1590 0.02536 0.02082 -0.0001 0.0058 1.0000
11.500 1.1619 0.02701 0.02262 0.0030 0.0057 1.0000
11.750 1.1538 0.02976 0.02564 0.0069 0.0055 1.0000
12.000 1.1483 0.03221 0.02831 0.0100 0.0055 1.0000
12.250 1.1330 0.03561 0.03199 0.0134 0.0054 1.0000
12.500 1.1378 0.03697 0.03344 0.0149 0.0055 1.0000
12.750 1.1251 0.04025 0.03693 0.0169 0.0055 1.0000
13.000 1.1019 0.04484 0.04179 0.0183 0.0054 1.0000
13.250 1.0797 0.04981 0.04699 0.0183 0.0054 1.0000
13.500 1.0582 0.05534 0.05272 0.0169 0.0054 1.0000
13.750 1.0383 0.06140 0.05895 0.0142 0.0054 1.0000
14.000 1.0293 0.06647 0.06414 0.0114 0.0054 1.0000
14.250 1.0216 0.07182 0.06959 0.0080 0.0054 1.0000
14.500 0.9886 0.08346 0.08144 0.0001 0.0054 1.0000
14.750 0.9708 0.09296 0.09106 -0.0062 0.0054 1.0000
15.000 0.9545 0.10259 0.10079 -0.0121 0.0054 1.0000
15.250 0.9329 0.11372 0.11201 -0.0184 0.0054 1.0000
15.500 0.9421 0.11681 0.11513 -0.0199 0.0057 1.0000
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Polar data table (+)
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