SD6060-104-88 (sd6060-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD6060-104-88 (sd6060-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.74 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd6060-il-1000000.txt Download as CSV file: xf-sd6060-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: SD6060-104-88
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4043 0.09575 0.09430 -0.0177 1.0000 0.0109
-10.250 -0.4054 0.09027 0.08882 -0.0200 1.0000 0.0113
-7.000 -0.5438 0.02017 0.01602 -0.0414 0.9153 0.0074
-6.750 -0.5273 0.01711 0.01252 -0.0396 0.9051 0.0069
-6.500 -0.5063 0.01531 0.01044 -0.0383 0.8965 0.0069
-6.250 -0.4835 0.01411 0.00904 -0.0374 0.8879 0.0071
-6.000 -0.4596 0.01317 0.00795 -0.0366 0.8794 0.0073
-5.750 -0.4349 0.01257 0.00723 -0.0360 0.8715 0.0077
-5.500 -0.4088 0.01217 0.00675 -0.0356 0.8630 0.0080
-5.250 -0.3866 0.01097 0.00537 -0.0346 0.8550 0.0084
-5.000 -0.3618 0.01034 0.00465 -0.0341 0.8465 0.0088
-4.750 -0.3360 0.00991 0.00415 -0.0337 0.8384 0.0093
-4.500 -0.3099 0.00956 0.00372 -0.0334 0.8303 0.0099
-4.250 -0.2831 0.00926 0.00338 -0.0331 0.8219 0.0108
-4.000 -0.2564 0.00902 0.00304 -0.0329 0.8140 0.0115
-3.750 -0.2300 0.00858 0.00255 -0.0325 0.8053 0.0145
-3.500 -0.2036 0.00820 0.00221 -0.0322 0.7972 0.0314
-3.250 -0.1772 0.00787 0.00199 -0.0320 0.7886 0.0639
-2.500 -0.0979 0.00689 0.00149 -0.0317 0.7629 0.2207
-2.250 -0.0728 0.00637 0.00134 -0.0315 0.7545 0.3340
-2.000 -0.0480 0.00585 0.00120 -0.0312 0.7456 0.4580
-1.750 -0.0225 0.00546 0.00111 -0.0309 0.7369 0.5621
-1.500 0.0033 0.00520 0.00106 -0.0305 0.7283 0.6420
-1.250 0.0299 0.00503 0.00103 -0.0302 0.7190 0.6988
-1.000 0.0569 0.00495 0.00101 -0.0300 0.7101 0.7373
-0.750 0.0840 0.00490 0.00100 -0.0297 0.7011 0.7696
-0.500 0.1113 0.00486 0.00100 -0.0295 0.6919 0.7944
-0.250 0.1387 0.00485 0.00100 -0.0293 0.6832 0.8154
0.000 0.1659 0.00484 0.00101 -0.0291 0.6741 0.8344
0.250 0.1933 0.00485 0.00102 -0.0289 0.6651 0.8523
0.500 0.2204 0.00487 0.00104 -0.0287 0.6563 0.8681
0.750 0.2475 0.00489 0.00106 -0.0284 0.6469 0.8824
1.000 0.2744 0.00492 0.00110 -0.0281 0.6377 0.8963
1.250 0.3008 0.00496 0.00113 -0.0277 0.6283 0.9093
1.500 0.3271 0.00500 0.00117 -0.0272 0.6182 0.9211
1.750 0.3534 0.00504 0.00121 -0.0268 0.6084 0.9321
2.000 0.3793 0.00511 0.00125 -0.0263 0.5979 0.9429
2.500 0.4325 0.00523 0.00135 -0.0256 0.5747 0.9609
2.750 0.4598 0.00530 0.00140 -0.0254 0.5618 0.9695
3.000 0.4919 0.00539 0.00145 -0.0263 0.5472 0.9746
3.500 0.5565 0.00563 0.00160 -0.0285 0.5106 0.9844
3.750 0.5918 0.00579 0.00169 -0.0303 0.4872 0.9867
4.000 0.6266 0.00599 0.00180 -0.0320 0.4595 0.9893
4.250 0.6598 0.00624 0.00193 -0.0334 0.4255 0.9925
4.500 0.6922 0.00665 0.00211 -0.0348 0.3714 0.9953
4.750 0.7258 0.00703 0.00231 -0.0365 0.3269 0.9980
5.000 0.7571 0.00742 0.00254 -0.0377 0.2862 1.0000
5.250 0.7760 0.00778 0.00275 -0.0362 0.2518 1.0000
5.500 0.7951 0.00818 0.00299 -0.0348 0.2170 1.0000
5.750 0.8154 0.00855 0.00323 -0.0336 0.1882 1.0000
6.000 0.8364 0.00893 0.00351 -0.0325 0.1620 1.0000
6.250 0.8577 0.00936 0.00380 -0.0315 0.1337 1.0000
6.500 0.8793 0.00982 0.00413 -0.0306 0.1061 1.0000
6.750 0.9010 0.01032 0.00449 -0.0298 0.0790 1.0000
7.000 0.9213 0.01099 0.00497 -0.0288 0.0475 1.0000
7.250 0.9408 0.01176 0.00557 -0.0276 0.0216 1.0000
7.500 0.9638 0.01220 0.00603 -0.0269 0.0177 1.0000
7.750 0.9861 0.01269 0.00653 -0.0262 0.0154 1.0000
8.000 1.0071 0.01333 0.00725 -0.0252 0.0138 1.0000
8.250 1.0299 0.01374 0.00772 -0.0245 0.0133 1.0000
8.500 1.0524 0.01416 0.00819 -0.0238 0.0125 1.0000
8.750 1.0737 0.01469 0.00876 -0.0230 0.0116 1.0000
9.000 1.0942 0.01525 0.00938 -0.0221 0.0110 1.0000
9.250 1.1114 0.01609 0.01029 -0.0206 0.0101 1.0000
9.500 1.1209 0.01750 0.01185 -0.0181 0.0094 1.0000
9.750 1.1427 0.01784 0.01223 -0.0174 0.0091 1.0000
10.000 1.1613 0.01840 0.01284 -0.0162 0.0086 1.0000
10.250 1.1796 0.01892 0.01341 -0.0151 0.0080 1.0000
10.500 1.1945 0.01958 0.01413 -0.0134 0.0076 1.0000
10.750 1.2069 0.02022 0.01481 -0.0113 0.0072 1.0000
11.000 1.2157 0.02108 0.01572 -0.0089 0.0068 1.0000
11.250 1.2108 0.02290 0.01767 -0.0050 0.0064 1.0000
11.500 1.2139 0.02437 0.01926 -0.0025 0.0061 1.0000
11.750 1.2261 0.02520 0.02017 -0.0011 0.0060 1.0000
12.000 1.2343 0.02639 0.02145 0.0005 0.0058 1.0000
12.250 1.2429 0.02758 0.02273 0.0019 0.0055 1.0000
12.500 1.2479 0.02913 0.02439 0.0035 0.0054 1.0000
12.750 1.2549 0.03058 0.02592 0.0046 0.0052 1.0000
13.000 1.2662 0.03164 0.02704 0.0053 0.0048 1.0000
13.250 1.2660 0.03388 0.02941 0.0065 0.0048 1.0000
13.500 1.2712 0.03566 0.03127 0.0071 0.0046 1.0000
13.750 1.2702 0.03819 0.03391 0.0077 0.0046 1.0000
14.000 1.2755 0.04009 0.03587 0.0079 0.0044 1.0000
14.250 1.2721 0.04307 0.03896 0.0080 0.0042 1.0000
14.500 1.2666 0.04645 0.04247 0.0078 0.0042 1.0000
14.750 1.2454 0.05196 0.04818 0.0071 0.0040 1.0000
15.000 1.2381 0.05603 0.05238 0.0061 0.0041 1.0000
15.250 1.2108 0.06317 0.05976 0.0039 0.0039 1.0000
15.500 1.2018 0.06814 0.06488 0.0018 0.0039 1.0000
15.750 1.1917 0.07357 0.07045 -0.0007 0.0039 1.0000
16.000 1.1844 0.07884 0.07584 -0.0035 0.0039 1.0000
16.250 1.1687 0.08577 0.08292 -0.0071 0.0039 1.0000
16.500 1.1628 0.09132 0.08858 -0.0103 0.0038 1.0000
16.750 1.1514 0.09814 0.09553 -0.0142 0.0038 1.0000
17.000 1.1265 0.10780 0.10536 -0.0196 0.0038 1.0000
17.250 1.1083 0.11650 0.11419 -0.0246 0.0039 1.0000
17.500 1.0772 0.12830 0.12615 -0.0313 0.0039 1.0000
17.750 1.0681 0.13577 0.13373 -0.0358 0.0039 1.0000
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Polar data table (+)
Polar graphs
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