S6062 8% (s6062-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S6062 8% (s6062-il) Reynolds number: 500,000 Max Cl/Cd: 81.99 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s6062-il-500000.txt Download as CSV file: xf-s6062-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S6062 8%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4512 0.09244 0.09037 -0.0081 1.0000 0.0163
-9.500 -0.4485 0.08874 0.08669 -0.0090 1.0000 0.0167
-9.250 -0.4443 0.08544 0.08339 -0.0098 1.0000 0.0172
-9.000 -0.4427 0.08153 0.07949 -0.0110 1.0000 0.0178
-8.750 -0.4421 0.07755 0.07552 -0.0125 1.0000 0.0187
-8.500 -0.4458 0.07242 0.07041 -0.0146 1.0000 0.0185
-8.250 -0.4482 0.06794 0.06595 -0.0167 1.0000 0.0197
-8.000 -0.4539 0.06286 0.06089 -0.0193 1.0000 0.0198
-7.750 -0.4629 0.05762 0.05569 -0.0226 1.0000 0.0201
-7.500 -0.4795 0.05134 0.04942 -0.0287 1.0000 0.0192
-7.250 -0.4850 0.04480 0.04279 -0.0334 1.0000 0.0194
-7.000 -0.4848 0.03873 0.03660 -0.0364 1.0000 0.0201
-6.750 -0.4792 0.03295 0.03059 -0.0383 1.0000 0.0216
-6.500 -0.4636 0.03050 0.02780 -0.0384 1.0000 0.0229
-6.250 -0.4578 0.02710 0.02415 -0.0373 1.0000 0.0230
-6.000 -0.4902 0.03271 0.02911 -0.0362 1.0000 0.0242
-5.750 -0.4817 0.03068 0.02704 -0.0340 1.0000 0.0250
-5.500 -0.4528 0.02845 0.02467 -0.0358 0.9970 0.0264
-5.250 -0.4192 0.02606 0.02200 -0.0380 0.9934 0.0292
-4.750 -0.3505 0.01593 0.01044 -0.0389 0.9858 0.0143
-4.500 -0.3148 0.01363 0.00786 -0.0403 0.9835 0.0132
-4.250 -0.2828 0.01225 0.00633 -0.0410 0.9778 0.0132
-4.000 -0.2487 0.01125 0.00523 -0.0423 0.9730 0.0140
-3.750 -0.2168 0.01055 0.00442 -0.0431 0.9666 0.0148
-3.500 -0.1865 0.00998 0.00378 -0.0435 0.9589 0.0161
-3.250 -0.1593 0.00942 0.00314 -0.0432 0.9495 0.0188
-3.000 -0.1325 0.00909 0.00273 -0.0427 0.9405 0.0221
-2.750 -0.1088 0.00828 0.00229 -0.0418 0.9302 0.1132
-2.500 -0.0850 0.00772 0.00208 -0.0411 0.9194 0.2145
-2.250 -0.0616 0.00709 0.00193 -0.0405 0.9092 0.3509
-2.000 -0.0385 0.00649 0.00181 -0.0396 0.8992 0.4980
-1.750 -0.0160 0.00595 0.00174 -0.0385 0.8885 0.6427
-1.500 0.0070 0.00562 0.00172 -0.0372 0.8774 0.7441
-1.250 0.0300 0.00544 0.00171 -0.0356 0.8666 0.8170
-1.000 0.0539 0.00536 0.00168 -0.0343 0.8558 0.8589
-0.750 0.0776 0.00531 0.00165 -0.0329 0.8448 0.8935
-0.500 0.1022 0.00528 0.00161 -0.0317 0.8327 0.9244
-0.250 0.1309 0.00528 0.00157 -0.0315 0.8207 0.9495
0.000 0.1648 0.00529 0.00152 -0.0325 0.8084 0.9687
0.250 0.2029 0.00531 0.00147 -0.0346 0.7954 0.9821
0.500 0.2445 0.00532 0.00141 -0.0374 0.7809 0.9912
0.750 0.2857 0.00534 0.00135 -0.0403 0.7653 1.0000
1.000 0.3091 0.00539 0.00132 -0.0394 0.7491 1.0000
1.500 0.3575 0.00552 0.00132 -0.0379 0.7147 1.0000
1.750 0.3822 0.00561 0.00133 -0.0372 0.6959 1.0000
2.250 0.4325 0.00582 0.00141 -0.0361 0.6552 1.0000
2.500 0.4580 0.00596 0.00148 -0.0355 0.6327 1.0000
2.750 0.4836 0.00611 0.00155 -0.0351 0.6077 1.0000
3.000 0.5095 0.00627 0.00163 -0.0347 0.5814 1.0000
3.250 0.5346 0.00652 0.00173 -0.0341 0.5389 1.0000
3.500 0.5593 0.00685 0.00186 -0.0336 0.4849 1.0000
3.750 0.5835 0.00729 0.00203 -0.0331 0.4196 1.0000
4.000 0.6083 0.00770 0.00223 -0.0327 0.3648 1.0000
4.250 0.6330 0.00817 0.00247 -0.0323 0.3078 1.0000
4.500 0.6568 0.00879 0.00279 -0.0319 0.2361 1.0000
4.750 0.6794 0.00962 0.00319 -0.0314 0.1496 1.0000
5.000 0.7014 0.01061 0.00373 -0.0308 0.0627 1.0000
5.250 0.7246 0.01145 0.00435 -0.0302 0.0230 1.0000
5.500 0.7499 0.01191 0.00487 -0.0298 0.0201 1.0000
5.750 0.7746 0.01252 0.00555 -0.0292 0.0179 1.0000
6.000 0.7982 0.01327 0.00642 -0.0285 0.0171 1.0000
6.250 0.8200 0.01431 0.00758 -0.0275 0.0164 1.0000
6.500 0.8440 0.01492 0.00826 -0.0270 0.0159 1.0000
6.750 0.8663 0.01583 0.00927 -0.0261 0.0156 1.0000
7.000 0.8883 0.01686 0.01042 -0.0252 0.0153 1.0000
7.250 0.9099 0.01803 0.01170 -0.0243 0.0150 1.0000
7.500 0.9314 0.01941 0.01320 -0.0233 0.0148 1.0000
7.750 0.9527 0.02111 0.01505 -0.0222 0.0147 1.0000
8.000 0.9736 0.02327 0.01741 -0.0211 0.0149 1.0000
8.250 0.9930 0.02601 0.02043 -0.0199 0.0153 1.0000
8.500 1.0115 0.02838 0.02307 -0.0187 0.0152 1.0000
8.750 1.0253 0.03180 0.02686 -0.0171 0.0155 1.0000
10.250 0.9998 0.05842 0.05570 -0.0027 0.0210 1.0000
10.500 0.9797 0.06205 0.05948 -0.0016 0.0209 1.0000
10.750 0.9579 0.06664 0.06422 -0.0027 0.0208 1.0000
11.000 0.9342 0.07260 0.07030 -0.0059 0.0214 1.0000
11.250 0.9086 0.08038 0.07820 -0.0117 0.0220 1.0000
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Polar data table (+)
Polar graphs
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