SD7090 (10%) (sd7090-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7090 (10%) (sd7090-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.21 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7090-il-1000000-n5.txt Download as CSV file: xf-sd7090-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD7090 (10%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.9022 0.08584 0.08361 -0.0319 1.0000 0.0069
-15.000 -1.0857 0.04618 0.04343 -0.0602 1.0000 0.0064
-14.750 -1.1134 0.03806 0.03507 -0.0673 1.0000 0.0063
-14.500 -1.1155 0.03527 0.03218 -0.0685 1.0000 0.0065
-14.250 -1.1288 0.03223 0.02898 -0.0681 1.0000 0.0065
-14.000 -1.1341 0.03056 0.02720 -0.0658 1.0000 0.0066
-13.750 -1.1395 0.02921 0.02574 -0.0623 1.0000 0.0067
-13.500 -1.1348 0.02794 0.02436 -0.0600 1.0000 0.0068
-13.250 -1.1265 0.02685 0.02315 -0.0580 1.0000 0.0069
-13.000 -1.1173 0.02573 0.02192 -0.0560 1.0000 0.0070
-12.750 -1.1055 0.02477 0.02086 -0.0542 1.0000 0.0070
-12.500 -1.0948 0.02364 0.01960 -0.0522 1.0000 0.0072
-12.250 -1.0832 0.02251 0.01837 -0.0502 1.0000 0.0073
-12.000 -1.0682 0.02167 0.01744 -0.0486 1.0000 0.0076
-11.750 -1.0519 0.02091 0.01662 -0.0470 1.0000 0.0077
-11.500 -1.0342 0.02027 0.01591 -0.0456 1.0000 0.0079
-11.250 -1.0159 0.01967 0.01525 -0.0442 1.0000 0.0081
-11.000 -0.9972 0.01909 0.01460 -0.0429 1.0000 0.0083
-10.750 -0.9788 0.01845 0.01388 -0.0415 1.0000 0.0085
-10.500 -0.9595 0.01789 0.01325 -0.0402 1.0000 0.0088
-10.250 -0.9360 0.01733 0.01262 -0.0397 0.9996 0.0090
-10.000 -0.9068 0.01674 0.01196 -0.0404 0.9986 0.0093
-9.750 -0.8773 0.01625 0.01139 -0.0411 0.9974 0.0095
-9.500 -0.8471 0.01581 0.01089 -0.0419 0.9962 0.0097
-9.250 -0.8173 0.01509 0.01008 -0.0428 0.9949 0.0100
-9.000 -0.7875 0.01439 0.00930 -0.0436 0.9937 0.0104
-8.750 -0.7596 0.01386 0.00873 -0.0439 0.9918 0.0107
-8.500 -0.7301 0.01343 0.00825 -0.0445 0.9898 0.0111
-8.250 -0.6995 0.01302 0.00780 -0.0453 0.9879 0.0114
-8.000 -0.6681 0.01263 0.00737 -0.0462 0.9863 0.0119
-7.750 -0.6359 0.01222 0.00691 -0.0473 0.9848 0.0123
-7.500 -0.6027 0.01185 0.00649 -0.0485 0.9835 0.0127
-7.250 -0.5760 0.01149 0.00609 -0.0483 0.9799 0.0129
-7.000 -0.5466 0.01115 0.00571 -0.0487 0.9764 0.0131
-6.750 -0.5154 0.01064 0.00515 -0.0495 0.9735 0.0138
-6.250 -0.4575 0.00995 0.00443 -0.0500 0.9639 0.0151
-5.750 -0.3966 0.00937 0.00379 -0.0511 0.9504 0.0162
-5.500 -0.3627 0.00909 0.00347 -0.0523 0.9416 0.0168
-5.250 -0.3286 0.00881 0.00315 -0.0536 0.9285 0.0178
-5.000 -0.2971 0.00856 0.00285 -0.0542 0.9084 0.0194
-4.750 -0.2688 0.00841 0.00260 -0.0542 0.8843 0.0213
-4.500 -0.2427 0.00826 0.00240 -0.0537 0.8592 0.0256
-4.250 -0.2171 0.00813 0.00221 -0.0531 0.8355 0.0333
-4.000 -0.1914 0.00802 0.00206 -0.0525 0.8130 0.0416
-3.750 -0.1655 0.00795 0.00192 -0.0520 0.7922 0.0477
-3.500 -0.1393 0.00787 0.00179 -0.0515 0.7724 0.0541
-3.250 -0.1131 0.00780 0.00168 -0.0511 0.7533 0.0613
-3.000 -0.0868 0.00774 0.00156 -0.0506 0.7349 0.0696
-2.750 -0.0605 0.00764 0.00146 -0.0502 0.7167 0.0839
-2.500 -0.0343 0.00752 0.00136 -0.0498 0.6985 0.1052
-2.250 -0.0079 0.00743 0.00128 -0.0495 0.6805 0.1254
-2.000 0.0184 0.00733 0.00120 -0.0491 0.6622 0.1515
-1.500 0.0707 0.00710 0.00107 -0.0484 0.6254 0.2229
-1.250 0.0972 0.00702 0.00102 -0.0480 0.6066 0.2554
-1.000 0.1236 0.00696 0.00099 -0.0477 0.5871 0.2872
-0.750 0.1500 0.00690 0.00096 -0.0473 0.5680 0.3211
-0.500 0.1760 0.00679 0.00094 -0.0470 0.5477 0.3751
-0.250 0.2016 0.00663 0.00093 -0.0466 0.5275 0.4458
0.250 0.2532 0.00644 0.00096 -0.0457 0.4886 0.5657
0.500 0.2788 0.00637 0.00099 -0.0452 0.4682 0.6231
0.750 0.3046 0.00635 0.00103 -0.0447 0.4489 0.6713
1.000 0.3307 0.00636 0.00108 -0.0443 0.4304 0.7092
1.250 0.3568 0.00639 0.00113 -0.0438 0.4115 0.7424
1.500 0.3827 0.00644 0.00120 -0.0433 0.3921 0.7729
2.000 0.4338 0.00654 0.00134 -0.0421 0.3563 0.8337
2.250 0.4589 0.00659 0.00143 -0.0414 0.3390 0.8645
2.500 0.4837 0.00666 0.00152 -0.0406 0.3222 0.8965
2.750 0.5096 0.00675 0.00163 -0.0400 0.3052 0.9317
3.000 0.5426 0.00691 0.00175 -0.0410 0.2867 0.9607
3.250 0.5774 0.00710 0.00186 -0.0425 0.2688 0.9767
3.500 0.6113 0.00729 0.00198 -0.0439 0.2517 0.9859
3.750 0.6456 0.00749 0.00210 -0.0453 0.2341 0.9922
4.000 0.6794 0.00770 0.00223 -0.0467 0.2166 0.9972
4.250 0.7107 0.00791 0.00237 -0.0475 0.2012 1.0000
4.500 0.7340 0.00811 0.00251 -0.0466 0.1883 1.0000
4.750 0.7574 0.00833 0.00267 -0.0457 0.1745 1.0000
5.000 0.7808 0.00855 0.00283 -0.0448 0.1618 1.0000
5.250 0.8044 0.00877 0.00300 -0.0439 0.1499 1.0000
5.500 0.8281 0.00901 0.00318 -0.0431 0.1394 1.0000
5.750 0.8518 0.00927 0.00339 -0.0423 0.1268 1.0000
6.000 0.8758 0.00952 0.00360 -0.0415 0.1156 1.0000
6.250 0.9000 0.00976 0.00381 -0.0408 0.1067 1.0000
6.500 0.9240 0.01004 0.00404 -0.0401 0.0972 1.0000
6.750 0.9480 0.01033 0.00429 -0.0394 0.0881 1.0000
7.000 0.9724 0.01057 0.00453 -0.0388 0.0815 1.0000
7.250 0.9962 0.01089 0.00480 -0.0381 0.0733 1.0000
7.500 1.0201 0.01120 0.00508 -0.0374 0.0662 1.0000
7.750 1.0439 0.01151 0.00538 -0.0367 0.0596 1.0000
8.000 1.0671 0.01187 0.00571 -0.0360 0.0528 1.0000
8.250 1.0910 0.01216 0.00601 -0.0353 0.0488 1.0000
8.500 1.1141 0.01254 0.00636 -0.0346 0.0437 1.0000
8.750 1.1374 0.01288 0.00671 -0.0338 0.0398 1.0000
9.000 1.1600 0.01327 0.00709 -0.0330 0.0357 1.0000
9.250 1.1827 0.01365 0.00747 -0.0322 0.0321 1.0000
9.500 1.2048 0.01406 0.00788 -0.0314 0.0287 1.0000
9.750 1.2267 0.01449 0.00831 -0.0305 0.0259 1.0000
10.000 1.2486 0.01489 0.00874 -0.0296 0.0238 1.0000
10.250 1.2693 0.01538 0.00922 -0.0286 0.0211 1.0000
10.500 1.2907 0.01580 0.00968 -0.0276 0.0199 1.0000
10.750 1.3114 0.01624 0.01015 -0.0266 0.0183 1.0000
11.000 1.3312 0.01674 0.01066 -0.0255 0.0169 1.0000
11.250 1.3505 0.01725 0.01121 -0.0242 0.0156 1.0000
11.500 1.3698 0.01772 0.01173 -0.0230 0.0147 1.0000
11.750 1.3880 0.01825 0.01230 -0.0217 0.0136 1.0000
12.000 1.4046 0.01885 0.01292 -0.0201 0.0125 1.0000
12.250 1.4202 0.01941 0.01352 -0.0184 0.0117 1.0000
12.500 1.4336 0.01997 0.01413 -0.0163 0.0109 1.0000
12.750 1.4452 0.02062 0.01482 -0.0139 0.0099 1.0000
13.000 1.4554 0.02136 0.01561 -0.0115 0.0090 1.0000
13.250 1.4667 0.02205 0.01636 -0.0094 0.0085 1.0000
13.500 1.4764 0.02285 0.01722 -0.0072 0.0077 1.0000
13.750 1.4843 0.02378 0.01820 -0.0049 0.0070 1.0000
14.000 1.4917 0.02478 0.01927 -0.0028 0.0065 1.0000
14.250 1.4986 0.02587 0.02043 -0.0009 0.0061 1.0000
14.500 1.5040 0.02711 0.02175 0.0010 0.0056 1.0000
14.750 1.5072 0.02860 0.02331 0.0027 0.0051 1.0000
15.000 1.5110 0.03016 0.02494 0.0042 0.0050 1.0000
15.250 1.5121 0.03205 0.02694 0.0054 0.0046 1.0000
15.500 1.5137 0.03403 0.02901 0.0062 0.0044 1.0000
15.750 1.5143 0.03627 0.03134 0.0068 0.0043 1.0000
16.000 1.5123 0.03891 0.03409 0.0070 0.0042 1.0000
16.250 1.5093 0.04186 0.03715 0.0069 0.0040 1.0000
16.500 1.5044 0.04522 0.04062 0.0064 0.0039 1.0000
16.750 1.4975 0.04902 0.04452 0.0054 0.0038 1.0000
17.000 1.4887 0.05329 0.04892 0.0040 0.0037 1.0000
17.250 1.4785 0.05797 0.05373 0.0022 0.0037 1.0000
17.500 1.4658 0.06325 0.05913 -0.0001 0.0037 1.0000
17.750 1.4479 0.06962 0.06564 -0.0031 0.0036 1.0000
18.000 1.4292 0.07637 0.07253 -0.0065 0.0036 1.0000
18.250 1.4090 0.08366 0.07996 -0.0103 0.0036 1.0000
18.500 1.3842 0.09197 0.08843 -0.0147 0.0035 1.0000
18.750 1.3578 0.10090 0.09751 -0.0196 0.0035 1.0000
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Polar data table (+)
Polar graphs
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