S6061 9% (s6061-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S6061 9% (s6061-il) Reynolds number: 200,000 Max Cl/Cd: 63.29 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s6061-il-200000-n5.txt Download as CSV file: xf-s6061-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S6061 9%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5065 0.10345 0.09987 -0.0102 1.0000 0.0154
-9.750 -0.5045 0.09954 0.09598 -0.0116 1.0000 0.0147
-9.500 -0.5034 0.09532 0.09180 -0.0136 1.0000 0.0142
-9.250 -0.5033 0.09090 0.08741 -0.0158 1.0000 0.0137
-9.000 -0.5059 0.08588 0.08244 -0.0185 1.0000 0.0131
-8.750 -0.5099 0.08060 0.07722 -0.0217 1.0000 0.0127
-8.500 -0.5181 0.07435 0.07102 -0.0260 1.0000 0.0121
-8.250 -0.5311 0.06722 0.06396 -0.0328 1.0000 0.0118
-8.000 -0.5504 0.05394 0.05047 -0.0404 1.0000 0.0106
-7.750 -0.5493 0.04947 0.04577 -0.0415 1.0000 0.0104
-7.500 -0.5503 0.04485 0.04092 -0.0418 1.0000 0.0102
-7.250 -0.5484 0.04036 0.03613 -0.0414 1.0000 0.0101
-7.000 -0.5443 0.03633 0.03175 -0.0402 1.0000 0.0100
-6.750 -0.5388 0.03281 0.02784 -0.0383 1.0000 0.0100
-6.500 -0.5314 0.02986 0.02451 -0.0360 1.0000 0.0099
-6.250 -0.5038 0.02634 0.02039 -0.0374 0.9930 0.0100
-6.000 -0.4733 0.02356 0.01710 -0.0387 0.9866 0.0101
-5.750 -0.4412 0.02142 0.01455 -0.0400 0.9810 0.0103
-5.500 -0.4104 0.01940 0.01222 -0.0409 0.9743 0.0106
-5.250 -0.3792 0.01767 0.01033 -0.0420 0.9685 0.0115
-5.000 -0.3485 0.01683 0.00940 -0.0430 0.9610 0.0131
-4.750 -0.3168 0.01584 0.00824 -0.0438 0.9545 0.0145
-4.500 -0.2875 0.01493 0.00719 -0.0442 0.9462 0.0154
-4.250 -0.2584 0.01413 0.00626 -0.0445 0.9380 0.0166
-4.000 -0.2292 0.01347 0.00551 -0.0448 0.9300 0.0194
-3.750 -0.2023 0.01288 0.00489 -0.0446 0.9204 0.0281
-3.500 -0.1757 0.01221 0.00436 -0.0444 0.9116 0.0678
-3.250 -0.1502 0.01158 0.00402 -0.0442 0.9024 0.1356
-3.000 -0.1260 0.01091 0.00375 -0.0438 0.8924 0.2334
-2.750 -0.1011 0.01042 0.00351 -0.0434 0.8831 0.3143
-2.500 -0.0769 0.00991 0.00331 -0.0427 0.8738 0.4103
-2.250 -0.0536 0.00943 0.00316 -0.0418 0.8634 0.5158
-2.000 -0.0306 0.00905 0.00309 -0.0406 0.8538 0.6151
-1.500 0.0168 0.00867 0.00301 -0.0379 0.8340 0.7501
-1.250 0.0412 0.00859 0.00296 -0.0366 0.8238 0.7937
-1.000 0.0659 0.00855 0.00290 -0.0354 0.8137 0.8290
-0.750 0.0910 0.00852 0.00285 -0.0343 0.8031 0.8590
-0.250 0.1457 0.00849 0.00273 -0.0332 0.7800 0.9091
0.000 0.1768 0.00849 0.00267 -0.0335 0.7683 0.9306
0.250 0.2117 0.00849 0.00260 -0.0347 0.7561 0.9490
0.500 0.2483 0.00850 0.00253 -0.0364 0.7434 0.9650
0.750 0.2858 0.00851 0.00247 -0.0384 0.7300 0.9786
1.000 0.3241 0.00853 0.00241 -0.0406 0.7154 0.9902
1.250 0.3601 0.00855 0.00238 -0.0424 0.7000 1.0000
1.500 0.3832 0.00862 0.00238 -0.0415 0.6848 1.0000
1.750 0.4066 0.00870 0.00239 -0.0406 0.6694 1.0000
2.000 0.4304 0.00880 0.00243 -0.0398 0.6537 1.0000
2.250 0.4545 0.00891 0.00249 -0.0391 0.6374 1.0000
2.500 0.4789 0.00904 0.00256 -0.0384 0.6204 1.0000
2.750 0.5036 0.00917 0.00265 -0.0378 0.6017 1.0000
3.000 0.5284 0.00933 0.00275 -0.0371 0.5815 1.0000
3.250 0.5534 0.00950 0.00289 -0.0366 0.5605 1.0000
3.500 0.5784 0.00969 0.00302 -0.0360 0.5382 1.0000
3.750 0.6034 0.00989 0.00318 -0.0355 0.5139 1.0000
4.000 0.6282 0.01013 0.00336 -0.0349 0.4871 1.0000
4.250 0.6528 0.01040 0.00359 -0.0344 0.4570 1.0000
4.500 0.6771 0.01072 0.00382 -0.0338 0.4247 1.0000
4.750 0.7013 0.01108 0.00409 -0.0332 0.3896 1.0000
5.000 0.7240 0.01159 0.00440 -0.0325 0.3419 1.0000
5.250 0.7449 0.01232 0.00481 -0.0317 0.2733 1.0000
5.500 0.7659 0.01309 0.00526 -0.0310 0.2096 1.0000
5.750 0.7887 0.01370 0.00572 -0.0304 0.1711 1.0000
6.000 0.8104 0.01444 0.00626 -0.0298 0.1264 1.0000
6.250 0.8319 0.01523 0.00686 -0.0291 0.0863 1.0000
6.500 0.8526 0.01614 0.00758 -0.0283 0.0505 1.0000
6.750 0.8734 0.01705 0.00841 -0.0274 0.0314 1.0000
7.250 0.9164 0.01861 0.01015 -0.0258 0.0225 1.0000
7.500 0.9377 0.01938 0.01102 -0.0250 0.0203 1.0000
7.750 0.9575 0.02028 0.01203 -0.0240 0.0191 1.0000
8.000 0.9753 0.02141 0.01327 -0.0228 0.0181 1.0000
8.250 0.9912 0.02271 0.01468 -0.0214 0.0174 1.0000
8.500 1.0085 0.02387 0.01598 -0.0201 0.0170 1.0000
8.750 1.0252 0.02515 0.01744 -0.0187 0.0166 1.0000
9.000 1.0418 0.02650 0.01893 -0.0174 0.0160 1.0000
9.250 1.0586 0.02777 0.02035 -0.0162 0.0151 1.0000
9.500 1.0743 0.02912 0.02185 -0.0149 0.0142 1.0000
9.750 1.0890 0.03071 0.02360 -0.0136 0.0137 1.0000
10.000 1.1023 0.03246 0.02553 -0.0122 0.0132 1.0000
10.250 1.1138 0.03432 0.02757 -0.0107 0.0128 1.0000
10.500 1.1218 0.03636 0.02979 -0.0088 0.0124 1.0000
10.750 1.1258 0.03875 0.03238 -0.0068 0.0120 1.0000
11.250 1.1188 0.04447 0.03868 -0.0025 0.0111 1.0000
11.500 1.1159 0.04671 0.04119 -0.0010 0.0108 1.0000
11.750 1.1093 0.04968 0.04443 0.0000 0.0105 1.0000
12.000 1.1001 0.05321 0.04821 0.0004 0.0104 1.0000
12.250 1.0882 0.05732 0.05257 0.0000 0.0102 1.0000
12.500 1.0741 0.06205 0.05754 -0.0013 0.0102 1.0000
12.750 1.0585 0.06744 0.06315 -0.0036 0.0101 1.0000
13.000 1.0413 0.07362 0.06954 -0.0068 0.0102 1.0000
13.250 1.0232 0.08055 0.07667 -0.0110 0.0101 1.0000
13.500 1.0041 0.08838 0.08467 -0.0161 0.0102 1.0000
13.750 0.9835 0.09736 0.09380 -0.0221 0.0104 1.0000
14.000 0.9612 0.10773 0.10431 -0.0289 0.0105 1.0000
14.250 0.9384 0.11914 0.11578 -0.0360 0.0108 1.0000
14.500 0.9130 0.13198 0.12867 -0.0433 0.0112 1.0000
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Polar data table (+)
Polar graphs
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