SD5060 (9.5%) (sd5060-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD5060 (9.5%) (sd5060-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.89 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd5060-il-1000000.txt Download as CSV file: xf-sd5060-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.7993 0.05714 0.05517 -0.0343 1.0000 0.0081
-11.500 -0.8290 0.04539 0.04324 -0.0453 1.0000 0.0080
-11.250 -0.8591 0.03791 0.03555 -0.0527 1.0000 0.0079
-11.000 -0.8625 0.03440 0.03181 -0.0539 1.0000 0.0080
-10.750 -0.8581 0.03142 0.02858 -0.0543 1.0000 0.0081
-10.500 -0.8435 0.02973 0.02670 -0.0544 1.0000 0.0083
-10.250 -0.8432 0.02497 0.02146 -0.0544 1.0000 0.0086
-10.000 -0.8255 0.02325 0.01961 -0.0542 1.0000 0.0089
-9.750 -0.8029 0.02248 0.01879 -0.0541 1.0000 0.0092
-9.500 -0.7797 0.02173 0.01796 -0.0540 1.0000 0.0095
-9.250 -0.7564 0.02096 0.01711 -0.0538 1.0000 0.0098
-9.000 -0.7332 0.02008 0.01612 -0.0536 1.0000 0.0102
-8.750 -0.7108 0.01896 0.01486 -0.0533 1.0000 0.0105
-8.500 -0.6881 0.01811 0.01389 -0.0528 1.0000 0.0109
-8.250 -0.6562 0.01729 0.01293 -0.0541 0.9935 0.0112
-8.000 -0.6247 0.01585 0.01129 -0.0555 0.9852 0.0116
-7.750 -0.5954 0.01429 0.00962 -0.0566 0.9754 0.0123
-7.500 -0.5669 0.01370 0.00897 -0.0570 0.9644 0.0128
-7.250 -0.5420 0.01321 0.00841 -0.0565 0.9521 0.0133
-7.000 -0.5180 0.01282 0.00794 -0.0556 0.9405 0.0139
-6.750 -0.4935 0.01240 0.00743 -0.0549 0.9294 0.0145
-6.500 -0.4681 0.01200 0.00695 -0.0543 0.9193 0.0149
-6.250 -0.4424 0.01168 0.00654 -0.0537 0.9099 0.0152
-6.000 -0.4183 0.01062 0.00533 -0.0531 0.9001 0.0161
-5.750 -0.3921 0.01012 0.00476 -0.0528 0.8910 0.0170
-5.500 -0.3656 0.00980 0.00436 -0.0524 0.8824 0.0179
-5.250 -0.3383 0.00948 0.00399 -0.0522 0.8733 0.0188
-5.000 -0.3111 0.00920 0.00363 -0.0519 0.8649 0.0195
-4.750 -0.2836 0.00895 0.00332 -0.0517 0.8561 0.0201
-4.500 -0.2561 0.00858 0.00286 -0.0515 0.8476 0.0220
-4.250 -0.2286 0.00833 0.00256 -0.0513 0.8391 0.0243
-4.000 -0.2006 0.00808 0.00229 -0.0511 0.8302 0.0300
-3.750 -0.1735 0.00764 0.00200 -0.0510 0.8218 0.0659
-3.500 -0.1458 0.00735 0.00182 -0.0509 0.8127 0.0967
-3.250 -0.1178 0.00716 0.00168 -0.0509 0.8041 0.1205
-3.000 -0.0900 0.00699 0.00156 -0.0508 0.7951 0.1429
-2.750 -0.0617 0.00686 0.00146 -0.0508 0.7857 0.1633
-2.500 -0.0337 0.00671 0.00136 -0.0507 0.7766 0.1888
-2.000 0.0227 0.00649 0.00120 -0.0506 0.7567 0.2302
-1.750 0.0508 0.00637 0.00113 -0.0506 0.7467 0.2595
-1.500 0.0789 0.00624 0.00107 -0.0505 0.7358 0.2949
-1.250 0.1070 0.00610 0.00102 -0.0505 0.7245 0.3315
-1.000 0.1350 0.00596 0.00098 -0.0505 0.7128 0.3769
-0.750 0.1631 0.00585 0.00095 -0.0504 0.7004 0.4185
-0.500 0.1910 0.00574 0.00093 -0.0504 0.6875 0.4657
-0.250 0.2190 0.00563 0.00092 -0.0503 0.6743 0.5139
0.000 0.2468 0.00552 0.00092 -0.0502 0.6609 0.5701
0.250 0.2745 0.00541 0.00093 -0.0501 0.6470 0.6270
0.500 0.3019 0.00528 0.00095 -0.0499 0.6325 0.6902
0.750 0.3287 0.00517 0.00098 -0.0495 0.6171 0.7554
1.000 0.3546 0.00505 0.00103 -0.0489 0.6006 0.8249
1.250 0.3783 0.00494 0.00107 -0.0476 0.5839 0.8970
1.500 0.4083 0.00490 0.00109 -0.0477 0.5649 0.9701
1.750 0.4448 0.00501 0.00111 -0.0495 0.5439 1.0000
2.000 0.4724 0.00514 0.00115 -0.0494 0.5226 1.0000
2.250 0.4999 0.00529 0.00120 -0.0493 0.5003 1.0000
2.500 0.5276 0.00545 0.00127 -0.0492 0.4784 1.0000
2.750 0.5549 0.00564 0.00135 -0.0490 0.4521 1.0000
3.000 0.5822 0.00585 0.00145 -0.0489 0.4249 1.0000
3.250 0.6095 0.00606 0.00155 -0.0488 0.3983 1.0000
3.500 0.6366 0.00631 0.00168 -0.0487 0.3686 1.0000
3.750 0.6635 0.00659 0.00182 -0.0485 0.3369 1.0000
4.250 0.7172 0.00714 0.00213 -0.0482 0.2818 1.0000
4.500 0.7439 0.00744 0.00232 -0.0481 0.2546 1.0000
4.750 0.7707 0.00773 0.00250 -0.0479 0.2318 1.0000
5.000 0.7973 0.00802 0.00269 -0.0478 0.2109 1.0000
5.250 0.8239 0.00832 0.00291 -0.0476 0.1917 1.0000
5.500 0.8506 0.00858 0.00311 -0.0474 0.1763 1.0000
5.750 0.8772 0.00886 0.00333 -0.0472 0.1613 1.0000
6.000 0.9036 0.00915 0.00356 -0.0470 0.1479 1.0000
6.250 0.9299 0.00945 0.00381 -0.0468 0.1356 1.0000
6.500 0.9563 0.00973 0.00405 -0.0466 0.1253 1.0000
6.750 0.9827 0.00999 0.00430 -0.0464 0.1170 1.0000
7.000 1.0087 0.01030 0.00458 -0.0462 0.1081 1.0000
7.250 1.0349 0.01058 0.00484 -0.0460 0.1010 1.0000
7.500 1.0608 0.01088 0.00514 -0.0457 0.0937 1.0000
7.750 1.0862 0.01123 0.00544 -0.0454 0.0848 1.0000
8.000 1.1119 0.01153 0.00574 -0.0451 0.0775 1.0000
8.250 1.1369 0.01191 0.00608 -0.0448 0.0691 1.0000
8.500 1.1616 0.01232 0.00645 -0.0444 0.0609 1.0000
8.750 1.1864 0.01269 0.00681 -0.0440 0.0542 1.0000
9.000 1.2104 0.01315 0.00723 -0.0436 0.0468 1.0000
9.250 1.2339 0.01365 0.00770 -0.0431 0.0402 1.0000
9.500 1.2577 0.01409 0.00815 -0.0426 0.0353 1.0000
9.750 1.2803 0.01465 0.00868 -0.0420 0.0298 1.0000
10.000 1.3033 0.01514 0.00918 -0.0414 0.0260 1.0000
10.250 1.3253 0.01571 0.00976 -0.0407 0.0219 1.0000
10.500 1.3461 0.01639 0.01042 -0.0399 0.0174 1.0000
10.750 1.3664 0.01709 0.01112 -0.0390 0.0137 1.0000
11.000 1.3855 0.01788 0.01192 -0.0380 0.0106 1.0000
11.250 1.4042 0.01864 0.01274 -0.0369 0.0088 1.0000
11.500 1.4220 0.01945 0.01358 -0.0357 0.0077 1.0000
11.750 1.4375 0.02040 0.01461 -0.0342 0.0068 1.0000
12.000 1.4543 0.02114 0.01543 -0.0329 0.0064 1.0000
12.250 1.4692 0.02197 0.01632 -0.0314 0.0061 1.0000
12.500 1.4804 0.02283 0.01728 -0.0293 0.0059 1.0000
12.750 1.4863 0.02386 0.01837 -0.0266 0.0055 1.0000
13.000 1.4916 0.02497 0.01958 -0.0241 0.0054 1.0000
13.250 1.4898 0.02667 0.02140 -0.0213 0.0051 1.0000
13.500 1.4867 0.02864 0.02351 -0.0190 0.0049 1.0000
13.750 1.4924 0.03009 0.02504 -0.0176 0.0049 1.0000
14.000 1.4954 0.03185 0.02691 -0.0163 0.0048 1.0000
14.250 1.4956 0.03400 0.02918 -0.0152 0.0047 1.0000
14.500 1.4940 0.03648 0.03177 -0.0145 0.0047 1.0000
14.750 1.4929 0.03908 0.03449 -0.0142 0.0046 1.0000
15.000 1.4898 0.04209 0.03762 -0.0142 0.0045 1.0000
15.250 1.4858 0.04541 0.04106 -0.0146 0.0045 1.0000
15.500 1.4794 0.04924 0.04502 -0.0155 0.0044 1.0000
15.750 1.4671 0.05414 0.05006 -0.0171 0.0044 1.0000
16.000 1.4579 0.05891 0.05497 -0.0190 0.0044 1.0000
16.250 1.4409 0.06520 0.06141 -0.0218 0.0044 1.0000
16.500 1.4280 0.07123 0.06757 -0.0248 0.0043 1.0000
16.750 1.4077 0.07889 0.07539 -0.0289 0.0043 1.0000
17.000 1.3874 0.08694 0.08359 -0.0332 0.0043 1.0000
17.250 1.3652 0.09565 0.09245 -0.0380 0.0044 1.0000
17.500 1.3394 0.10538 0.10233 -0.0435 0.0044 1.0000
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