S2060 8% (s2060-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S2060 8% (s2060-il) Reynolds number: 50,000 Max Cl/Cd: 36.4 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2060-il-50000.txt Download as CSV file: xf-s2060-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S2060 8%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4668 0.09358 0.08679 -0.0081 1.0000 0.2927
-7.500 -0.4682 0.09083 0.08413 -0.0074 1.0000 0.3076
-7.250 -0.4694 0.08804 0.08142 -0.0063 1.0000 0.3223
-7.000 -0.4748 0.08557 0.07906 -0.0050 1.0000 0.3372
-6.750 -0.4566 0.08147 0.07495 -0.0024 1.0000 0.3645
-6.500 -0.4489 0.07834 0.07183 0.0003 1.0000 0.3927
-6.250 -0.4411 0.07496 0.06849 0.0025 1.0000 0.4149
-6.000 -0.4844 0.06148 0.05496 -0.0310 1.0000 0.2041
-5.750 -0.4731 0.05048 0.04323 -0.0406 1.0000 0.1459
-5.500 -0.4591 0.04493 0.03716 -0.0422 1.0000 0.1407
-5.250 -0.4421 0.04115 0.03301 -0.0422 1.0000 0.1447
-5.000 -0.4220 0.03697 0.02823 -0.0424 1.0000 0.1460
-4.750 -0.4016 0.03399 0.02485 -0.0420 1.0000 0.1563
-4.500 -0.3777 0.03100 0.02120 -0.0416 1.0000 0.1633
-4.250 -0.3551 0.02891 0.01876 -0.0409 1.0000 0.1782
-4.000 -0.3312 0.02681 0.01644 -0.0401 1.0000 0.1903
-3.750 -0.3074 0.02515 0.01455 -0.0392 1.0000 0.2094
-3.500 -0.2838 0.02361 0.01300 -0.0382 1.0000 0.2304
-3.250 -0.2599 0.02225 0.01164 -0.0373 1.0000 0.2611
-3.000 -0.2368 0.02092 0.01041 -0.0361 1.0000 0.3049
-2.750 -0.2136 0.01944 0.00939 -0.0349 1.0000 0.3865
-2.500 -0.1992 0.01746 0.00888 -0.0310 1.0000 0.5905
-2.250 -0.1495 0.01639 0.00852 -0.0289 1.0000 1.0000
-2.000 -0.1360 0.01621 0.00789 -0.0278 1.0000 1.0000
-1.750 -0.1170 0.01617 0.00743 -0.0272 1.0000 1.0000
-1.500 -0.0966 0.01620 0.00713 -0.0267 1.0000 1.0000
-1.250 -0.0756 0.01628 0.00692 -0.0262 1.0000 1.0000
-1.000 -0.0543 0.01639 0.00679 -0.0257 1.0000 1.0000
-0.750 -0.0329 0.01655 0.00670 -0.0252 1.0000 1.0000
-0.500 -0.0116 0.01674 0.00670 -0.0247 1.0000 1.0000
-0.250 0.0096 0.01696 0.00676 -0.0243 1.0000 1.0000
0.000 0.0307 0.01722 0.00688 -0.0239 1.0000 1.0000
0.250 0.0515 0.01752 0.00707 -0.0235 1.0000 1.0000
0.500 0.0721 0.01785 0.00729 -0.0231 1.0000 1.0000
0.750 0.0923 0.01824 0.00760 -0.0227 1.0000 1.0000
1.000 0.1122 0.01866 0.00797 -0.0224 1.0000 1.0000
1.250 0.1317 0.01915 0.00841 -0.0221 1.0000 1.0000
1.500 0.1508 0.01968 0.00892 -0.0219 1.0000 1.0000
1.750 0.1694 0.02028 0.00951 -0.0217 1.0000 1.0000
2.000 0.1874 0.02095 0.01019 -0.0216 1.0000 1.0000
2.250 0.2049 0.02170 0.01096 -0.0216 1.0000 1.0000
2.500 0.2218 0.02253 0.01184 -0.0216 1.0000 1.0000
2.750 0.2844 0.02408 0.01353 -0.0301 0.9760 1.0000
3.000 0.3465 0.02532 0.01495 -0.0378 0.9493 1.0000
3.250 0.4068 0.02621 0.01610 -0.0445 0.9211 1.0000
3.500 0.4661 0.02674 0.01690 -0.0503 0.8914 1.0000
3.750 0.5286 0.02679 0.01734 -0.0555 0.8603 1.0000
4.000 0.5999 0.02607 0.01706 -0.0607 0.8286 1.0000
4.250 0.6475 0.02532 0.01665 -0.0614 0.7920 1.0000
4.500 0.6967 0.02406 0.01578 -0.0610 0.7532 1.0000
4.750 0.7344 0.02297 0.01492 -0.0586 0.7074 1.0000
5.000 0.7656 0.02218 0.01424 -0.0553 0.6537 1.0000
5.250 0.7900 0.02197 0.01393 -0.0515 0.5898 1.0000
5.500 0.8098 0.02225 0.01394 -0.0477 0.5168 1.0000
5.750 0.8251 0.02303 0.01433 -0.0438 0.4350 1.0000
6.000 0.8372 0.02435 0.01505 -0.0401 0.3451 1.0000
6.250 0.8447 0.02620 0.01621 -0.0364 0.2485 1.0000
6.500 0.8573 0.02875 0.01810 -0.0338 0.1725 1.0000
6.750 0.8812 0.03146 0.02063 -0.0325 0.1364 1.0000
7.000 0.9073 0.03420 0.02325 -0.0318 0.1185 1.0000
7.250 0.9336 0.03712 0.02658 -0.0308 0.1102 1.0000
7.500 0.9583 0.04065 0.03026 -0.0301 0.1054 1.0000
7.750 0.9751 0.04402 0.03433 -0.0284 0.1019 1.0000
8.000 0.9898 0.04745 0.03826 -0.0268 0.0982 1.0000
8.250 1.0026 0.05120 0.04246 -0.0253 0.0963 1.0000
8.500 1.0070 0.05593 0.04781 -0.0235 0.0974 1.0000
8.750 1.0055 0.06104 0.05346 -0.0218 0.0995 1.0000
9.000 1.0000 0.06627 0.05909 -0.0205 0.1017 1.0000
9.250 0.9954 0.07145 0.06452 -0.0197 0.1038 1.0000
9.500 1.0060 0.07705 0.07015 -0.0194 0.1060 1.0000
9.750 0.9433 0.08254 0.07612 -0.0195 0.1101 1.0000
10.000 0.9069 0.08966 0.08325 -0.0229 0.1137 1.0000
10.250 0.8956 0.09644 0.09003 -0.0259 0.1175 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S2060 8% (s2060-il)