S6062 8% (s6062-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S6062 8% (s6062-il) Reynolds number: 100,000 Max Cl/Cd: 48.39 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s6062-il-100000-n5.txt Download as CSV file: xf-s6062-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5244 0.09396 0.08906 -0.0112 1.0000 0.0234
-8.750 -0.5226 0.09001 0.08514 -0.0128 1.0000 0.0229
-8.500 -0.5222 0.08578 0.08097 -0.0150 1.0000 0.0223
-8.250 -0.5236 0.08128 0.07653 -0.0177 1.0000 0.0217
-8.000 -0.5268 0.07657 0.07189 -0.0212 1.0000 0.0211
-7.750 -0.5302 0.07088 0.06623 -0.0263 1.0000 0.0206
-7.500 -0.5312 0.06456 0.05985 -0.0311 1.0000 0.0199
-7.250 -0.5319 0.05742 0.05254 -0.0350 1.0000 0.0189
-7.000 -0.5305 0.04947 0.04402 -0.0377 1.0000 0.0176
-6.750 -0.5219 0.04539 0.03969 -0.0380 1.0000 0.0175
-6.500 -0.5111 0.04145 0.03543 -0.0380 1.0000 0.0173
-6.250 -0.4984 0.03772 0.03130 -0.0375 1.0000 0.0172
-6.000 -0.4838 0.03432 0.02745 -0.0367 1.0000 0.0172
-5.750 -0.4670 0.03143 0.02401 -0.0355 1.0000 0.0176
-5.500 -0.4509 0.02901 0.02140 -0.0346 1.0000 0.0188
-5.250 -0.4324 0.02725 0.01939 -0.0335 1.0000 0.0198
-5.000 -0.4130 0.02530 0.01711 -0.0322 1.0000 0.0205
-4.750 -0.3929 0.02338 0.01483 -0.0307 1.0000 0.0210
-4.500 -0.3726 0.02175 0.01295 -0.0293 1.0000 0.0215
-4.250 -0.3524 0.02036 0.01139 -0.0278 1.0000 0.0223
-4.000 -0.3324 0.01922 0.01010 -0.0264 1.0000 0.0232
-3.750 -0.3124 0.01826 0.00901 -0.0250 1.0000 0.0243
-3.500 -0.2929 0.01730 0.00798 -0.0238 1.0000 0.0270
-3.250 -0.2577 0.01647 0.00701 -0.0255 0.9933 0.0356
-3.000 -0.2228 0.01530 0.00597 -0.0271 0.9864 0.0702
-2.750 -0.1910 0.01391 0.00555 -0.0290 0.9795 0.2510
-2.500 -0.1596 0.01277 0.00534 -0.0304 0.9727 0.4677
-2.250 -0.1304 0.01212 0.00526 -0.0303 0.9650 0.6412
-2.000 -0.0988 0.01184 0.00528 -0.0299 0.9585 0.7747
-1.750 -0.0651 0.01175 0.00523 -0.0300 0.9510 0.8637
-1.500 -0.0180 0.01171 0.00506 -0.0332 0.9464 0.9274
-1.250 0.0383 0.01164 0.00479 -0.0387 0.9433 0.9687
-1.000 0.0934 0.01152 0.00450 -0.0443 0.9375 0.9988
-0.750 0.1278 0.01150 0.00434 -0.0458 0.9260 1.0000
-0.500 0.1590 0.01148 0.00419 -0.0466 0.9134 1.0000
-0.250 0.1880 0.01148 0.00409 -0.0469 0.9002 1.0000
0.000 0.2149 0.01149 0.00402 -0.0466 0.8863 1.0000
0.250 0.2409 0.01152 0.00396 -0.0461 0.8721 1.0000
0.500 0.2660 0.01155 0.00393 -0.0454 0.8575 1.0000
0.750 0.2905 0.01159 0.00392 -0.0446 0.8424 1.0000
1.000 0.3149 0.01164 0.00392 -0.0437 0.8271 1.0000
1.250 0.3393 0.01169 0.00396 -0.0427 0.8113 1.0000
1.500 0.3638 0.01175 0.00398 -0.0418 0.7949 1.0000
1.750 0.3883 0.01181 0.00401 -0.0408 0.7782 1.0000
2.000 0.4130 0.01188 0.00405 -0.0398 0.7608 1.0000
2.250 0.4374 0.01196 0.00416 -0.0389 0.7410 1.0000
2.500 0.4622 0.01205 0.00424 -0.0380 0.7213 1.0000
2.750 0.4869 0.01216 0.00434 -0.0371 0.6998 1.0000
3.000 0.5117 0.01229 0.00445 -0.0361 0.6777 1.0000
3.250 0.5364 0.01243 0.00463 -0.0352 0.6530 1.0000
3.500 0.5611 0.01260 0.00480 -0.0343 0.6265 1.0000
3.750 0.5857 0.01280 0.00498 -0.0334 0.5977 1.0000
4.000 0.6100 0.01304 0.00519 -0.0325 0.5659 1.0000
4.250 0.6341 0.01331 0.00548 -0.0316 0.5301 1.0000
4.500 0.6580 0.01364 0.00577 -0.0306 0.4911 1.0000
4.750 0.6809 0.01407 0.00609 -0.0296 0.4421 1.0000
5.000 0.7010 0.01478 0.00641 -0.0283 0.3581 1.0000
5.250 0.7191 0.01587 0.00688 -0.0271 0.2494 1.0000
5.500 0.7393 0.01689 0.00754 -0.0263 0.1743 1.0000
5.750 0.7585 0.01819 0.00842 -0.0255 0.0942 1.0000
6.000 0.7777 0.01959 0.00953 -0.0245 0.0484 1.0000
6.250 0.7982 0.02082 0.01078 -0.0234 0.0372 1.0000
6.500 0.8187 0.02199 0.01209 -0.0223 0.0331 1.0000
6.750 0.8394 0.02305 0.01330 -0.0214 0.0292 1.0000
7.000 0.8582 0.02437 0.01470 -0.0204 0.0263 1.0000
7.250 0.8769 0.02579 0.01626 -0.0192 0.0251 1.0000
7.500 0.8963 0.02727 0.01797 -0.0180 0.0242 1.0000
7.750 0.9162 0.02895 0.01982 -0.0169 0.0235 1.0000
8.000 0.9364 0.03083 0.02190 -0.0159 0.0229 1.0000
8.250 0.9566 0.03296 0.02427 -0.0149 0.0224 1.0000
8.500 0.9757 0.03536 0.02698 -0.0139 0.0220 1.0000
8.750 0.9926 0.03805 0.03002 -0.0128 0.0218 1.0000
9.000 1.0064 0.04093 0.03330 -0.0115 0.0214 1.0000
9.250 1.0177 0.04352 0.03620 -0.0102 0.0206 1.0000
9.500 1.0261 0.04611 0.03908 -0.0090 0.0198 1.0000
9.750 1.0310 0.04891 0.04212 -0.0077 0.0191 1.0000
10.000 1.0303 0.05244 0.04596 -0.0063 0.0186 1.0000
10.250 1.0247 0.05603 0.04987 -0.0047 0.0186 1.0000
10.500 1.0127 0.05942 0.05352 -0.0028 0.0186 1.0000
10.750 0.9984 0.06300 0.05734 -0.0018 0.0186 1.0000
11.000 0.9821 0.06712 0.06169 -0.0022 0.0186 1.0000
11.250 0.9647 0.07192 0.06672 -0.0041 0.0188 1.0000
11.500 0.9444 0.07803 0.07303 -0.0077 0.0189 1.0000
11.750 0.9190 0.08651 0.08167 -0.0142 0.0192 1.0000
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Polar data table (+)
Polar graphs
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