S6061 9% (s6061-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S6061 9% (s6061-il) Reynolds number: 500,000 Max Cl/Cd: 88.8 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s6061-il-500000.txt Download as CSV file: xf-s6061-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4999 0.09110 0.08890 -0.0154 1.0000 0.0173
-9.000 -0.4997 0.08657 0.08440 -0.0183 1.0000 0.0184
-7.500 -0.5179 0.05377 0.05128 -0.0421 1.0000 0.0200
-7.250 -0.5161 0.04968 0.04697 -0.0424 1.0000 0.0201
-7.000 -0.5360 0.04080 0.03784 -0.0418 1.0000 0.0211
-6.750 -0.5326 0.03884 0.03584 -0.0393 1.0000 0.0216
-6.500 -0.5118 0.03624 0.03311 -0.0406 0.9968 0.0223
-6.250 -0.4823 0.03310 0.02973 -0.0433 0.9921 0.0237
-6.000 -0.4511 0.02991 0.02619 -0.0454 0.9873 0.0260
-5.750 -0.4205 0.02014 0.01503 -0.0455 0.9828 0.0142
-5.500 -0.3904 0.01740 0.01205 -0.0462 0.9768 0.0129
-5.250 -0.3581 0.01516 0.00952 -0.0471 0.9719 0.0126
-5.000 -0.3285 0.01379 0.00798 -0.0473 0.9646 0.0129
-4.750 -0.2993 0.01282 0.00686 -0.0475 0.9575 0.0134
-4.500 -0.2745 0.01197 0.00590 -0.0467 0.9476 0.0140
-4.250 -0.2513 0.01097 0.00481 -0.0457 0.9381 0.0154
-4.000 -0.2269 0.01058 0.00437 -0.0449 0.9291 0.0175
-3.750 -0.2024 0.01014 0.00384 -0.0440 0.9191 0.0192
-3.500 -0.1777 0.00958 0.00319 -0.0431 0.9098 0.0253
-3.250 -0.1542 0.00883 0.00271 -0.0422 0.9009 0.0940
-2.750 -0.1049 0.00784 0.00229 -0.0413 0.8817 0.2573
-2.500 -0.0811 0.00721 0.00212 -0.0407 0.8727 0.3893
-2.250 -0.0569 0.00667 0.00198 -0.0402 0.8625 0.5123
-2.000 -0.0326 0.00628 0.00190 -0.0394 0.8528 0.6160
-1.750 -0.0082 0.00603 0.00185 -0.0385 0.8434 0.6977
-1.500 0.0169 0.00588 0.00182 -0.0376 0.8326 0.7545
-1.250 0.0423 0.00579 0.00179 -0.0367 0.8218 0.7958
-1.000 0.0678 0.00574 0.00176 -0.0359 0.8112 0.8287
-0.750 0.0929 0.00571 0.00173 -0.0350 0.8007 0.8566
-0.500 0.1180 0.00569 0.00170 -0.0340 0.7892 0.8803
-0.250 0.1431 0.00568 0.00168 -0.0331 0.7775 0.9022
0.000 0.1682 0.00568 0.00166 -0.0321 0.7658 0.9228
0.250 0.1945 0.00569 0.00164 -0.0314 0.7539 0.9424
0.500 0.2251 0.00572 0.00161 -0.0318 0.7415 0.9584
0.750 0.2596 0.00576 0.00159 -0.0330 0.7286 0.9715
1.000 0.2974 0.00580 0.00157 -0.0351 0.7152 0.9820
1.250 0.3388 0.00585 0.00156 -0.0380 0.7011 0.9886
1.500 0.3788 0.00590 0.00155 -0.0406 0.6860 0.9957
1.750 0.4132 0.00594 0.00154 -0.0422 0.6700 1.0000
2.000 0.4360 0.00601 0.00155 -0.0412 0.6542 1.0000
2.250 0.4594 0.00610 0.00159 -0.0404 0.6380 1.0000
2.500 0.4834 0.00620 0.00163 -0.0397 0.6215 1.0000
2.750 0.5077 0.00632 0.00169 -0.0390 0.6045 1.0000
3.000 0.5326 0.00644 0.00176 -0.0384 0.5860 1.0000
3.250 0.5578 0.00658 0.00186 -0.0379 0.5658 1.0000
3.500 0.5832 0.00674 0.00196 -0.0375 0.5439 1.0000
3.750 0.6087 0.00692 0.00208 -0.0370 0.5208 1.0000
4.000 0.6340 0.00714 0.00221 -0.0366 0.4917 1.0000
4.250 0.6584 0.00747 0.00238 -0.0361 0.4426 1.0000
4.500 0.6821 0.00792 0.00258 -0.0355 0.3850 1.0000
4.750 0.7063 0.00836 0.00282 -0.0351 0.3376 1.0000
5.000 0.7309 0.00877 0.00309 -0.0347 0.2979 1.0000
5.250 0.7550 0.00927 0.00340 -0.0343 0.2525 1.0000
5.500 0.7789 0.00979 0.00374 -0.0338 0.2083 1.0000
5.750 0.8023 0.01039 0.00412 -0.0334 0.1603 1.0000
6.000 0.8242 0.01118 0.00461 -0.0327 0.1037 1.0000
6.250 0.8432 0.01242 0.00540 -0.0317 0.0337 1.0000
6.500 0.8663 0.01311 0.00608 -0.0310 0.0237 1.0000
6.750 0.8898 0.01372 0.00678 -0.0303 0.0214 1.0000
7.000 0.9132 0.01432 0.00748 -0.0296 0.0201 1.0000
7.250 0.9358 0.01500 0.00823 -0.0289 0.0189 1.0000
7.500 0.9575 0.01574 0.00904 -0.0281 0.0175 1.0000
7.750 0.9766 0.01681 0.01019 -0.0269 0.0163 1.0000
8.000 0.9926 0.01829 0.01182 -0.0253 0.0156 1.0000
8.250 1.0087 0.01993 0.01358 -0.0237 0.0152 1.0000
8.500 1.0288 0.02098 0.01475 -0.0226 0.0149 1.0000
8.750 1.0494 0.02193 0.01581 -0.0217 0.0143 1.0000
9.000 1.0689 0.02302 0.01702 -0.0207 0.0136 1.0000
9.250 1.0874 0.02437 0.01849 -0.0195 0.0130 1.0000
9.500 1.1049 0.02590 0.02016 -0.0183 0.0125 1.0000
9.750 1.1213 0.02762 0.02206 -0.0171 0.0121 1.0000
10.000 1.1360 0.02943 0.02404 -0.0157 0.0117 1.0000
10.250 1.1484 0.03146 0.02626 -0.0141 0.0114 1.0000
10.500 1.1576 0.03378 0.02875 -0.0125 0.0110 1.0000
10.750 1.1613 0.03689 0.03209 -0.0104 0.0107 1.0000
11.000 1.1556 0.04054 0.03603 -0.0075 0.0105 1.0000
11.250 1.1465 0.04349 0.03921 -0.0043 0.0104 1.0000
11.500 1.1220 0.04828 0.04432 -0.0013 0.0103 1.0000
11.750 1.1013 0.05255 0.04884 0.0002 0.0102 1.0000
12.000 1.0836 0.05671 0.05321 0.0006 0.0102 1.0000
12.250 1.0649 0.06140 0.05810 -0.0002 0.0102 1.0000
12.500 1.0567 0.06506 0.06189 -0.0014 0.0102 1.0000
12.750 1.0358 0.07111 0.06812 -0.0043 0.0102 1.0000
13.000 1.0331 0.07468 0.07179 -0.0064 0.0103 1.0000
13.250 1.0152 0.08140 0.07867 -0.0106 0.0103 1.0000
13.500 1.0025 0.08778 0.08517 -0.0150 0.0104 1.0000
13.750 0.9955 0.09362 0.09113 -0.0192 0.0106 1.0000
14.000 0.9726 0.10369 0.10133 -0.0262 0.0105 1.0000
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Polar data table (+)
Polar graphs
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