SD5060 (9.5%) (sd5060-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD5060 (9.5%) (sd5060-il) Reynolds number: 50,000 Max Cl/Cd: 33.57 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd5060-il-50000.txt Download as CSV file: xf-sd5060-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SD5060 (9.5%)
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4324 0.09984 0.09313 -0.0052 1.0000 0.2650
-8.000 -0.4201 0.09565 0.08896 -0.0050 1.0000 0.2728
-7.500 -0.4262 0.09081 0.08431 -0.0062 1.0000 0.2956
-7.250 -0.4101 0.08666 0.08015 -0.0054 1.0000 0.3075
-7.000 -0.4078 0.08344 0.07701 -0.0055 1.0000 0.3164
-6.500 -0.4678 0.05690 0.05015 -0.0436 1.0000 0.1335
-6.250 -0.4595 0.05242 0.04553 -0.0443 1.0000 0.1318
-6.000 -0.4519 0.04776 0.04058 -0.0452 1.0000 0.1312
-5.750 -0.4417 0.04338 0.03580 -0.0456 1.0000 0.1311
-5.500 -0.4288 0.03925 0.03117 -0.0456 1.0000 0.1316
-5.250 -0.4129 0.03550 0.02679 -0.0452 1.0000 0.1334
-5.000 -0.3955 0.03298 0.02410 -0.0442 1.0000 0.1392
-4.750 -0.3766 0.03067 0.02135 -0.0433 1.0000 0.1507
-4.500 -0.3568 0.02867 0.01913 -0.0421 1.0000 0.1653
-4.250 -0.3374 0.02715 0.01753 -0.0408 1.0000 0.1912
-4.000 -0.3194 0.02604 0.01660 -0.0393 1.0000 0.2285
-3.750 -0.3013 0.02511 0.01577 -0.0378 1.0000 0.2719
-3.500 -0.2813 0.02407 0.01469 -0.0365 1.0000 0.3126
-3.250 -0.2619 0.02323 0.01394 -0.0350 1.0000 0.3501
-3.000 -0.2417 0.02246 0.01319 -0.0338 1.0000 0.3894
-2.750 -0.2218 0.02181 0.01258 -0.0325 1.0000 0.4310
-2.500 -0.2021 0.02121 0.01210 -0.0311 1.0000 0.4757
-2.250 -0.1817 0.02065 0.01172 -0.0297 1.0000 0.5268
-2.000 -0.1629 0.02008 0.01138 -0.0278 1.0000 0.5905
-1.750 -0.1478 0.01945 0.01116 -0.0249 1.0000 0.6751
-1.500 -0.1413 0.01866 0.01100 -0.0193 1.0000 0.8043
-1.250 -0.0909 0.01810 0.01008 -0.0255 1.0000 1.0000
-1.000 -0.0684 0.01839 0.00996 -0.0262 1.0000 1.0000
-0.750 -0.0474 0.01874 0.01000 -0.0264 1.0000 1.0000
-0.500 -0.0272 0.01915 0.01015 -0.0264 1.0000 1.0000
-0.250 -0.0076 0.01960 0.01038 -0.0264 1.0000 1.0000
0.000 0.0118 0.02011 0.01070 -0.0264 1.0000 1.0000
0.250 0.0309 0.02067 0.01109 -0.0264 1.0000 1.0000
0.500 0.0497 0.02128 0.01155 -0.0264 1.0000 1.0000
0.750 0.1017 0.02251 0.01262 -0.0326 0.9848 1.0000
1.000 0.1534 0.02369 0.01368 -0.0384 0.9686 1.0000
1.250 0.1998 0.02470 0.01462 -0.0430 0.9509 1.0000
1.500 0.2468 0.02568 0.01555 -0.0476 0.9327 1.0000
1.750 0.2974 0.02661 0.01646 -0.0523 0.9142 1.0000
2.000 0.3396 0.02738 0.01725 -0.0555 0.8944 1.0000
2.250 0.3828 0.02805 0.01796 -0.0584 0.8736 1.0000
2.500 0.4393 0.02849 0.01849 -0.0629 0.8537 1.0000
2.750 0.4743 0.02895 0.01902 -0.0640 0.8306 1.0000
3.000 0.5285 0.02891 0.01910 -0.0669 0.8098 1.0000
3.250 0.5609 0.02909 0.01939 -0.0666 0.7857 1.0000
3.500 0.6077 0.02855 0.01898 -0.0671 0.7646 1.0000
3.750 0.6360 0.02850 0.01905 -0.0655 0.7391 1.0000
4.000 0.6684 0.02809 0.01873 -0.0638 0.7142 1.0000
4.250 0.7043 0.02718 0.01790 -0.0616 0.6905 1.0000
4.500 0.7317 0.02669 0.01747 -0.0590 0.6621 1.0000
4.750 0.7593 0.02613 0.01696 -0.0562 0.6323 1.0000
5.000 0.7846 0.02577 0.01660 -0.0534 0.5990 1.0000
5.250 0.8093 0.02554 0.01633 -0.0507 0.5630 1.0000
5.500 0.8347 0.02540 0.01607 -0.0481 0.5265 1.0000
5.750 0.8577 0.02571 0.01626 -0.0459 0.4879 1.0000
6.000 0.8810 0.02624 0.01663 -0.0440 0.4515 1.0000
6.250 0.9035 0.02707 0.01736 -0.0424 0.4174 1.0000
6.500 0.9263 0.02805 0.01826 -0.0409 0.3869 1.0000
6.750 0.9491 0.02926 0.01941 -0.0397 0.3604 1.0000
7.000 0.9732 0.03044 0.02044 -0.0386 0.3367 1.0000
7.250 0.9941 0.03205 0.02220 -0.0376 0.3151 1.0000
7.500 1.0172 0.03351 0.02365 -0.0366 0.2957 1.0000
7.750 1.0395 0.03521 0.02538 -0.0357 0.2782 1.0000
8.000 1.0589 0.03720 0.02759 -0.0347 0.2621 1.0000
8.250 1.0774 0.03924 0.02981 -0.0336 0.2465 1.0000
8.500 1.0962 0.04152 0.03226 -0.0326 0.2330 1.0000
8.750 1.1135 0.04376 0.03470 -0.0315 0.2191 1.0000
9.000 1.1332 0.04617 0.03716 -0.0305 0.2066 1.0000
9.250 1.1363 0.04956 0.04116 -0.0288 0.1967 1.0000
9.500 1.1427 0.05297 0.04488 -0.0274 0.1874 1.0000
9.750 1.1607 0.05574 0.04766 -0.0264 0.1773 1.0000
10.000 1.1439 0.06090 0.05344 -0.0247 0.1740 1.0000
10.250 1.1253 0.06608 0.05899 -0.0235 0.1712 1.0000
10.500 1.1125 0.07066 0.06376 -0.0226 0.1676 1.0000
10.750 1.0939 0.07569 0.06893 -0.0220 0.1660 1.0000
11.000 1.0793 0.08096 0.07427 -0.0219 0.1646 1.0000
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Polar data table (+)
Polar graphs
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