S6062 8% (s6062-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S6062 8% (s6062-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.02 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s6062-il-1000000.txt Download as CSV file: xf-s6062-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5322 0.08300 0.08144 -0.0128 1.0000 0.0086
-8.500 -0.5377 0.07765 0.07612 -0.0160 1.0000 0.0079
-8.250 -0.5410 0.07347 0.07197 -0.0189 1.0000 0.0088
-8.000 -0.5505 0.06797 0.06649 -0.0244 1.0000 0.0085
-7.750 -0.5521 0.06099 0.05946 -0.0309 1.0000 0.0087
-7.500 -0.5507 0.05416 0.05253 -0.0353 1.0000 0.0087
-7.250 -0.5455 0.04757 0.04576 -0.0379 1.0000 0.0092
-7.000 -0.5328 0.04174 0.03972 -0.0387 1.0000 0.0100
-6.750 -0.5180 0.03777 0.03549 -0.0386 1.0000 0.0103
-6.500 -0.5079 0.03413 0.03156 -0.0377 1.0000 0.0104
-6.250 -0.4983 0.02503 0.02176 -0.0394 0.9948 0.0111
-6.000 -0.4691 0.02307 0.01966 -0.0411 0.9900 0.0117
-5.750 -0.4376 0.02170 0.01816 -0.0428 0.9855 0.0126
-5.500 -0.4075 0.02001 0.01624 -0.0438 0.9789 0.0138
-5.250 -0.3746 0.02042 0.01653 -0.0443 0.9720 0.0154
-4.750 -0.3302 0.01196 0.00708 -0.0414 0.9500 0.0087
-4.500 -0.3069 0.01059 0.00550 -0.0401 0.9397 0.0080
-4.250 -0.2830 0.00979 0.00457 -0.0391 0.9296 0.0080
-4.000 -0.2579 0.00919 0.00388 -0.0384 0.9194 0.0084
-3.750 -0.2322 0.00874 0.00334 -0.0379 0.9098 0.0091
-3.500 -0.2062 0.00840 0.00290 -0.0373 0.9005 0.0099
-3.250 -0.1795 0.00811 0.00255 -0.0370 0.8904 0.0103
-3.000 -0.1528 0.00778 0.00212 -0.0366 0.8807 0.0110
-2.750 -0.1259 0.00753 0.00179 -0.0362 0.8710 0.0132
-2.500 -0.0990 0.00723 0.00150 -0.0359 0.8606 0.0305
-2.250 -0.0730 0.00665 0.00128 -0.0358 0.8501 0.1280
-2.000 -0.0465 0.00628 0.00114 -0.0357 0.8397 0.2079
-1.750 -0.0202 0.00588 0.00103 -0.0355 0.8289 0.3061
-1.500 0.0057 0.00541 0.00093 -0.0354 0.8175 0.4325
-1.250 0.0315 0.00495 0.00086 -0.0351 0.8058 0.5645
-1.000 0.0575 0.00463 0.00083 -0.0348 0.7937 0.6668
-0.750 0.0832 0.00440 0.00082 -0.0342 0.7813 0.7504
-0.500 0.1095 0.00431 0.00081 -0.0337 0.7681 0.7971
-0.250 0.1357 0.00425 0.00081 -0.0332 0.7541 0.8357
0.000 0.1615 0.00422 0.00081 -0.0325 0.7392 0.8699
0.250 0.1871 0.00421 0.00082 -0.0318 0.7239 0.8979
0.500 0.2124 0.00421 0.00082 -0.0310 0.7079 0.9226
0.750 0.2382 0.00425 0.00083 -0.0304 0.6913 0.9458
1.000 0.2677 0.00429 0.00084 -0.0305 0.6737 0.9661
1.250 0.3019 0.00436 0.00084 -0.0319 0.6540 0.9810
1.500 0.3386 0.00446 0.00086 -0.0338 0.6333 0.9905
1.750 0.3752 0.00455 0.00088 -0.0358 0.6101 0.9977
2.000 0.4047 0.00467 0.00091 -0.0362 0.5864 1.0000
2.250 0.4298 0.00482 0.00096 -0.0357 0.5612 1.0000
2.500 0.4551 0.00500 0.00103 -0.0352 0.5291 1.0000
2.750 0.4798 0.00530 0.00111 -0.0347 0.4742 1.0000
3.000 0.5054 0.00556 0.00122 -0.0344 0.4333 1.0000
3.250 0.5308 0.00589 0.00135 -0.0340 0.3832 1.0000
3.500 0.5558 0.00631 0.00152 -0.0337 0.3216 1.0000
3.750 0.5808 0.00676 0.00172 -0.0334 0.2603 1.0000
4.000 0.6052 0.00734 0.00198 -0.0331 0.1894 1.0000
4.250 0.6297 0.00791 0.00226 -0.0327 0.1255 1.0000
4.500 0.6528 0.00875 0.00270 -0.0322 0.0458 1.0000
4.750 0.6779 0.00928 0.00308 -0.0319 0.0162 1.0000
5.000 0.7043 0.00957 0.00340 -0.0316 0.0145 1.0000
5.250 0.7303 0.00993 0.00379 -0.0313 0.0130 1.0000
5.500 0.7561 0.01034 0.00427 -0.0309 0.0121 1.0000
5.750 0.7809 0.01094 0.00497 -0.0304 0.0112 1.0000
6.000 0.8047 0.01170 0.00585 -0.0298 0.0108 1.0000
6.250 0.8291 0.01229 0.00651 -0.0293 0.0107 1.0000
6.500 0.8536 0.01285 0.00712 -0.0288 0.0106 1.0000
6.750 0.8775 0.01350 0.00786 -0.0282 0.0104 1.0000
7.000 0.9011 0.01420 0.00863 -0.0276 0.0101 1.0000
7.250 0.9241 0.01501 0.00952 -0.0269 0.0098 1.0000
7.500 0.9463 0.01598 0.01058 -0.0261 0.0095 1.0000
7.750 0.9678 0.01715 0.01185 -0.0251 0.0093 1.0000
8.000 0.9896 0.01825 0.01305 -0.0243 0.0090 1.0000
8.250 1.0113 0.01935 0.01425 -0.0235 0.0086 1.0000
8.500 1.0317 0.02089 0.01595 -0.0225 0.0085 1.0000
8.750 1.0515 0.02251 0.01773 -0.0215 0.0084 1.0000
9.000 1.0699 0.02441 0.01983 -0.0204 0.0083 1.0000
9.250 1.0861 0.02664 0.02229 -0.0190 0.0083 1.0000
9.500 1.1000 0.02902 0.02493 -0.0176 0.0082 1.0000
9.750 1.0960 0.03524 0.03176 -0.0141 0.0090 1.0000
10.000 1.1007 0.03807 0.03484 -0.0121 0.0086 1.0000
10.250 1.1351 0.03475 0.03112 -0.0134 0.0074 1.0000
10.500 1.1360 0.03776 0.03436 -0.0112 0.0073 1.0000
10.750 1.0680 0.03017 0.02718 -0.0047 0.0072 1.0000
11.000 1.0494 0.03324 0.03042 -0.0021 0.0072 1.0000
11.250 1.0313 0.03666 0.03403 -0.0007 0.0073 1.0000
11.500 1.0117 0.04104 0.03857 -0.0006 0.0072 1.0000
11.750 0.9917 0.04637 0.04407 -0.0018 0.0073 1.0000
12.000 0.9696 0.05288 0.05071 -0.0041 0.0072 1.0000
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Polar data table (+)
Polar graphs
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