SD5060 (9.5%) (sd5060-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD5060 (9.5%) (sd5060-il) Reynolds number: 500,000 Max Cl/Cd: 88.78 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd5060-il-500000.txt Download as CSV file: xf-sd5060-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5892 0.05951 0.05738 -0.0349 1.0000 0.0194
-9.000 -0.6891 0.03357 0.03007 -0.0544 1.0000 0.0157
-8.750 -0.6786 0.03001 0.02613 -0.0545 1.0000 0.0157
-8.500 -0.6650 0.02686 0.02268 -0.0544 1.0000 0.0160
-8.250 -0.6477 0.02461 0.02019 -0.0539 1.0000 0.0163
-8.000 -0.6295 0.02300 0.01841 -0.0532 1.0000 0.0168
-7.750 -0.6143 0.02155 0.01681 -0.0516 1.0000 0.0171
-7.500 -0.5937 0.02032 0.01542 -0.0510 0.9984 0.0177
-7.250 -0.5583 0.01907 0.01399 -0.0531 0.9941 0.0188
-7.000 -0.5237 0.01790 0.01261 -0.0549 0.9893 0.0196
-6.750 -0.4878 0.01693 0.01144 -0.0567 0.9850 0.0201
-6.500 -0.4562 0.01474 0.00907 -0.0581 0.9790 0.0209
-6.250 -0.4236 0.01363 0.00789 -0.0594 0.9723 0.0220
-6.000 -0.3930 0.01302 0.00724 -0.0601 0.9639 0.0234
-5.750 -0.3640 0.01244 0.00657 -0.0602 0.9552 0.0246
-5.500 -0.3389 0.01192 0.00596 -0.0595 0.9443 0.0255
-5.250 -0.3141 0.01151 0.00546 -0.0587 0.9337 0.0263
-5.000 -0.2902 0.01081 0.00468 -0.0577 0.9239 0.0283
-4.750 -0.2652 0.01045 0.00425 -0.0569 0.9143 0.0312
-4.500 -0.2393 0.01014 0.00388 -0.0563 0.9045 0.0345
-4.250 -0.2140 0.00962 0.00340 -0.0556 0.8956 0.0498
-4.000 -0.1884 0.00909 0.00307 -0.0552 0.8862 0.0982
-3.750 -0.1619 0.00883 0.00288 -0.0548 0.8771 0.1266
-3.500 -0.1354 0.00865 0.00271 -0.0543 0.8687 0.1510
-3.250 -0.1081 0.00846 0.00258 -0.0541 0.8590 0.1747
-3.000 -0.0811 0.00830 0.00244 -0.0538 0.8504 0.1969
-2.750 -0.0539 0.00814 0.00231 -0.0535 0.8411 0.2213
-2.500 -0.0264 0.00796 0.00219 -0.0533 0.8318 0.2481
-2.250 0.0007 0.00780 0.00209 -0.0530 0.8231 0.2813
-2.000 0.0282 0.00760 0.00199 -0.0529 0.8130 0.3183
-1.750 0.0557 0.00743 0.00191 -0.0527 0.8035 0.3585
-1.500 0.0828 0.00725 0.00183 -0.0524 0.7941 0.4081
-1.250 0.1102 0.00704 0.00177 -0.0522 0.7833 0.4615
-1.000 0.1374 0.00685 0.00173 -0.0520 0.7728 0.5197
-0.750 0.1643 0.00667 0.00170 -0.0516 0.7623 0.5811
-0.500 0.1909 0.00646 0.00167 -0.0511 0.7508 0.6493
-0.250 0.2169 0.00627 0.00167 -0.0505 0.7386 0.7195
0.000 0.2418 0.00607 0.00168 -0.0495 0.7262 0.7947
0.250 0.2648 0.00589 0.00169 -0.0479 0.7137 0.8707
0.500 0.2942 0.00579 0.00166 -0.0476 0.7007 0.9493
0.750 0.3377 0.00578 0.00159 -0.0508 0.6863 1.0000
1.000 0.3648 0.00586 0.00158 -0.0505 0.6722 1.0000
1.250 0.3920 0.00594 0.00158 -0.0502 0.6571 1.0000
1.500 0.4193 0.00603 0.00159 -0.0500 0.6411 1.0000
1.750 0.4466 0.00613 0.00162 -0.0497 0.6242 1.0000
2.000 0.4740 0.00624 0.00165 -0.0495 0.6063 1.0000
2.250 0.5012 0.00637 0.00169 -0.0493 0.5877 1.0000
2.500 0.5286 0.00650 0.00174 -0.0491 0.5677 1.0000
2.750 0.5557 0.00666 0.00182 -0.0488 0.5456 1.0000
3.000 0.5829 0.00683 0.00190 -0.0486 0.5232 1.0000
3.250 0.6098 0.00703 0.00200 -0.0484 0.4984 1.0000
3.500 0.6366 0.00725 0.00212 -0.0482 0.4703 1.0000
3.750 0.6633 0.00750 0.00225 -0.0479 0.4418 1.0000
4.000 0.6898 0.00777 0.00241 -0.0477 0.4116 1.0000
4.250 0.7160 0.00809 0.00259 -0.0474 0.3774 1.0000
4.500 0.7420 0.00844 0.00280 -0.0472 0.3433 1.0000
4.750 0.7679 0.00880 0.00303 -0.0469 0.3116 1.0000
5.000 0.7936 0.00920 0.00328 -0.0466 0.2802 1.0000
5.250 0.8193 0.00959 0.00356 -0.0464 0.2517 1.0000
5.500 0.8450 0.00997 0.00384 -0.0461 0.2276 1.0000
5.750 0.8705 0.01038 0.00414 -0.0458 0.2058 1.0000
6.000 0.8962 0.01074 0.00445 -0.0455 0.1878 1.0000
6.250 0.9217 0.01112 0.00478 -0.0452 0.1716 1.0000
6.500 0.9471 0.01151 0.00511 -0.0449 0.1576 1.0000
6.750 0.9725 0.01189 0.00546 -0.0446 0.1454 1.0000
7.000 0.9975 0.01230 0.00583 -0.0442 0.1346 1.0000
7.250 1.0226 0.01269 0.00621 -0.0438 0.1247 1.0000
7.500 1.0478 0.01305 0.00659 -0.0435 0.1164 1.0000
7.750 1.0720 0.01351 0.00702 -0.0430 0.1078 1.0000
8.000 1.0970 0.01387 0.00740 -0.0426 0.1002 1.0000
8.250 1.1212 0.01431 0.00787 -0.0422 0.0926 1.0000
8.500 1.1447 0.01481 0.00833 -0.0417 0.0837 1.0000
8.750 1.1692 0.01517 0.00871 -0.0413 0.0754 1.0000
9.000 1.1926 0.01565 0.00918 -0.0408 0.0669 1.0000
9.250 1.2148 0.01625 0.00974 -0.0401 0.0586 1.0000
9.500 1.2376 0.01674 0.01027 -0.0395 0.0520 1.0000
9.750 1.2593 0.01736 0.01090 -0.0388 0.0456 1.0000
10.000 1.2793 0.01811 0.01163 -0.0379 0.0390 1.0000
10.250 1.3005 0.01868 0.01225 -0.0371 0.0342 1.0000
10.500 1.3191 0.01951 0.01308 -0.0361 0.0290 1.0000
10.750 1.3370 0.02036 0.01395 -0.0350 0.0243 1.0000
11.000 1.3535 0.02128 0.01493 -0.0337 0.0201 1.0000
11.250 1.3658 0.02251 0.01620 -0.0319 0.0166 1.0000
11.500 1.3792 0.02352 0.01728 -0.0303 0.0145 1.0000
11.750 1.3815 0.02503 0.01887 -0.0272 0.0129 1.0000
12.000 1.3889 0.02611 0.02006 -0.0249 0.0121 1.0000
12.250 1.3943 0.02738 0.02144 -0.0227 0.0115 1.0000
12.500 1.3985 0.02884 0.02300 -0.0207 0.0109 1.0000
12.750 1.3993 0.03066 0.02491 -0.0189 0.0103 1.0000
13.000 1.3963 0.03294 0.02730 -0.0173 0.0100 1.0000
13.250 1.3898 0.03576 0.03026 -0.0160 0.0096 1.0000
13.500 1.3899 0.03816 0.03280 -0.0153 0.0094 1.0000
13.750 1.3921 0.04049 0.03526 -0.0150 0.0090 1.0000
14.000 1.3902 0.04342 0.03832 -0.0150 0.0088 1.0000
14.250 1.3850 0.04692 0.04196 -0.0154 0.0086 1.0000
14.500 1.3786 0.05078 0.04596 -0.0163 0.0085 1.0000
14.750 1.3725 0.05485 0.05016 -0.0175 0.0083 1.0000
15.000 1.3643 0.05943 0.05487 -0.0192 0.0082 1.0000
15.250 1.3553 0.06436 0.05994 -0.0213 0.0081 1.0000
15.500 1.3446 0.06982 0.06554 -0.0238 0.0080 1.0000
15.750 1.3314 0.07595 0.07182 -0.0268 0.0080 1.0000
16.000 1.3196 0.08217 0.07817 -0.0300 0.0080 1.0000
16.250 1.3051 0.08904 0.08519 -0.0336 0.0079 1.0000
16.500 1.2922 0.09590 0.09217 -0.0373 0.0078 1.0000
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Polar data table (+)
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