S6061 9% (s6061-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S6061 9% (s6061-il) Reynolds number: 50,000 Max Cl/Cd: 35.89 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s6061-il-50000-n5.txt Download as CSV file: xf-s6061-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4950 0.09452 0.08767 -0.0199 1.0000 0.0405
-8.750 -0.4950 0.09010 0.08334 -0.0222 1.0000 0.0398
-8.500 -0.4965 0.08550 0.07880 -0.0250 1.0000 0.0391
-8.250 -0.4999 0.08060 0.07398 -0.0285 1.0000 0.0385
-8.000 -0.5055 0.07560 0.06905 -0.0322 1.0000 0.0377
-7.750 -0.5098 0.07047 0.06391 -0.0353 1.0000 0.0370
-7.500 -0.5135 0.06548 0.05884 -0.0377 1.0000 0.0363
-7.250 -0.5154 0.06062 0.05384 -0.0393 1.0000 0.0357
-7.000 -0.5147 0.05591 0.04890 -0.0402 1.0000 0.0352
-6.750 -0.5109 0.05149 0.04418 -0.0404 1.0000 0.0349
-6.500 -0.5041 0.04742 0.03975 -0.0400 1.0000 0.0347
-6.250 -0.4947 0.04376 0.03569 -0.0392 1.0000 0.0347
-6.000 -0.4828 0.04064 0.03219 -0.0380 1.0000 0.0354
-5.750 -0.4690 0.03795 0.02914 -0.0367 1.0000 0.0368
-5.500 -0.4535 0.03540 0.02616 -0.0353 1.0000 0.0392
-5.250 -0.4361 0.03296 0.02322 -0.0338 1.0000 0.0414
-5.000 -0.4169 0.03074 0.02052 -0.0322 1.0000 0.0430
-4.750 -0.3977 0.02860 0.01817 -0.0307 1.0000 0.0448
-4.500 -0.3788 0.02695 0.01635 -0.0291 1.0000 0.0479
-4.250 -0.3591 0.02561 0.01476 -0.0275 1.0000 0.0547
-4.000 -0.3405 0.02438 0.01350 -0.0260 1.0000 0.0647
-3.750 -0.3211 0.02316 0.01217 -0.0245 1.0000 0.0809
-3.500 -0.3012 0.02180 0.01100 -0.0235 1.0000 0.1180
-3.250 -0.2828 0.02036 0.01002 -0.0226 1.0000 0.1947
-2.750 -0.2527 0.01786 0.00916 -0.0188 1.0000 0.5201
-2.500 -0.2425 0.01737 0.00931 -0.0141 1.0000 0.6965
-2.250 -0.2252 0.01728 0.00936 -0.0104 1.0000 0.8326
-2.000 -0.1556 0.01731 0.00903 -0.0171 0.9995 0.9682
-1.750 -0.1009 0.01737 0.00859 -0.0233 0.9920 1.0000
-1.500 -0.0616 0.01752 0.00838 -0.0266 0.9807 1.0000
-1.250 -0.0213 0.01770 0.00825 -0.0300 0.9702 1.0000
-1.000 0.0164 0.01786 0.00811 -0.0327 0.9587 1.0000
-0.750 0.0538 0.01803 0.00806 -0.0352 0.9474 1.0000
-0.500 0.0917 0.01820 0.00805 -0.0378 0.9363 1.0000
-0.250 0.1316 0.01836 0.00804 -0.0406 0.9261 1.0000
0.000 0.1706 0.01851 0.00807 -0.0431 0.9155 1.0000
0.250 0.2038 0.01867 0.00813 -0.0445 0.9030 1.0000
0.500 0.2361 0.01883 0.00821 -0.0455 0.8904 1.0000
0.750 0.2675 0.01898 0.00831 -0.0464 0.8775 1.0000
1.000 0.2980 0.01913 0.00842 -0.0469 0.8643 1.0000
1.250 0.3276 0.01926 0.00854 -0.0472 0.8508 1.0000
1.500 0.3562 0.01940 0.00868 -0.0472 0.8370 1.0000
1.750 0.3841 0.01953 0.00881 -0.0469 0.8228 1.0000
2.000 0.4112 0.01965 0.00895 -0.0465 0.8083 1.0000
2.250 0.4380 0.01976 0.00910 -0.0460 0.7935 1.0000
2.500 0.4646 0.01987 0.00928 -0.0453 0.7783 1.0000
2.750 0.4910 0.01996 0.00942 -0.0446 0.7628 1.0000
3.000 0.5174 0.02002 0.00955 -0.0437 0.7469 1.0000
3.250 0.5417 0.02015 0.00979 -0.0426 0.7290 1.0000
3.500 0.5661 0.02027 0.01000 -0.0415 0.7104 1.0000
3.750 0.5916 0.02033 0.01014 -0.0404 0.6921 1.0000
4.000 0.6158 0.02045 0.01037 -0.0391 0.6717 1.0000
4.250 0.6404 0.02054 0.01061 -0.0379 0.6504 1.0000
4.500 0.6641 0.02069 0.01086 -0.0365 0.6268 1.0000
4.750 0.6880 0.02082 0.01108 -0.0351 0.6019 1.0000
5.000 0.7114 0.02098 0.01135 -0.0337 0.5747 1.0000
5.250 0.7342 0.02121 0.01167 -0.0322 0.5447 1.0000
5.500 0.7566 0.02148 0.01208 -0.0307 0.5121 1.0000
5.750 0.7781 0.02182 0.01247 -0.0291 0.4764 1.0000
6.000 0.7988 0.02226 0.01291 -0.0274 0.4377 1.0000
6.250 0.8181 0.02283 0.01347 -0.0257 0.3952 1.0000
6.500 0.8357 0.02357 0.01415 -0.0240 0.3484 1.0000
6.750 0.8511 0.02452 0.01494 -0.0222 0.2977 1.0000
7.000 0.8645 0.02571 0.01593 -0.0204 0.2430 1.0000
7.250 0.8747 0.02726 0.01721 -0.0187 0.1773 1.0000
7.500 0.8839 0.02920 0.01869 -0.0172 0.1207 1.0000
7.750 0.8945 0.03132 0.02065 -0.0155 0.0893 1.0000
8.000 0.9059 0.03337 0.02264 -0.0139 0.0724 1.0000
8.250 0.9189 0.03526 0.02460 -0.0124 0.0618 1.0000
8.500 0.9321 0.03724 0.02663 -0.0109 0.0557 1.0000
8.750 0.9505 0.03928 0.02895 -0.0096 0.0515 1.0000
9.000 0.9688 0.04146 0.03131 -0.0085 0.0483 1.0000
9.250 0.9881 0.04406 0.03398 -0.0076 0.0460 1.0000
9.500 1.0068 0.04705 0.03742 -0.0066 0.0444 1.0000
9.750 1.0182 0.05010 0.04096 -0.0053 0.0425 1.0000
10.000 1.0237 0.05315 0.04442 -0.0040 0.0404 1.0000
10.250 1.0256 0.05620 0.04778 -0.0026 0.0387 1.0000
10.500 1.0222 0.05930 0.05116 -0.0010 0.0377 1.0000
10.750 1.0148 0.06286 0.05499 0.0003 0.0373 1.0000
11.000 1.0036 0.06676 0.05916 0.0009 0.0371 1.0000
11.250 0.9887 0.07119 0.06384 0.0005 0.0371 1.0000
11.500 0.9701 0.07642 0.06931 -0.0011 0.0372 1.0000
11.750 0.9479 0.08271 0.07581 -0.0042 0.0375 1.0000
12.000 0.9205 0.09083 0.08411 -0.0095 0.0382 1.0000
12.250 0.8904 0.10125 0.09464 -0.0168 0.0395 1.0000
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Polar data table (+)
Polar graphs
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