SD7090 (10%) (sd7090-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7090 (10%) (sd7090-il) Reynolds number: 100,000 Max Cl/Cd: 47.11 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7090-il-100000.txt Download as CSV file: xf-sd7090-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4567 0.10006 0.09492 -0.0195 1.0000 0.1235
-9.000 -0.4724 0.09690 0.09186 -0.0233 1.0000 0.1293
-8.750 -0.5058 0.09343 0.08855 -0.0296 1.0000 0.1304
-8.500 -0.4626 0.08959 0.08462 -0.0227 1.0000 0.1357
-8.250 -0.4643 0.08649 0.08158 -0.0233 1.0000 0.1406
-8.000 -0.5170 0.08256 0.07782 -0.0316 1.0000 0.1449
-7.750 -0.4992 0.07865 0.07398 -0.0278 1.0000 0.1478
-7.500 -0.4882 0.07603 0.07137 -0.0255 1.0000 0.1519
-7.250 -0.5284 0.07100 0.06628 -0.0331 1.0000 0.1608
-7.000 -0.5070 0.06790 0.06329 -0.0292 1.0000 0.1635
-6.750 -0.5478 0.04850 0.04280 -0.0384 1.0000 0.0900
-6.500 -0.5474 0.04131 0.03453 -0.0364 1.0000 0.0742
-6.250 -0.5357 0.03732 0.03032 -0.0350 1.0000 0.0732
-6.000 -0.5225 0.03442 0.02693 -0.0332 1.0000 0.0738
-5.750 -0.5080 0.03146 0.02354 -0.0316 1.0000 0.0751
-5.500 -0.4907 0.02881 0.02066 -0.0302 1.0000 0.0766
-5.250 -0.4716 0.02679 0.01841 -0.0288 1.0000 0.0783
-5.000 -0.4514 0.02511 0.01652 -0.0274 1.0000 0.0812
-4.750 -0.4307 0.02387 0.01492 -0.0259 1.0000 0.0867
-4.500 -0.4099 0.02224 0.01327 -0.0247 1.0000 0.0926
-4.250 -0.3883 0.02111 0.01195 -0.0234 1.0000 0.1004
-4.000 -0.3677 0.02002 0.01091 -0.0222 1.0000 0.1127
-3.750 -0.3469 0.01909 0.00998 -0.0210 1.0000 0.1287
-3.500 -0.3266 0.01825 0.00928 -0.0198 1.0000 0.1489
-3.250 -0.3066 0.01765 0.00875 -0.0187 1.0000 0.1754
-3.000 -0.2873 0.01693 0.00828 -0.0175 1.0000 0.2070
-2.750 -0.2687 0.01618 0.00789 -0.0163 1.0000 0.2591
-2.500 -0.2514 0.01523 0.00764 -0.0149 1.0000 0.3679
-2.250 -0.2366 0.01440 0.00772 -0.0127 1.0000 0.5435
-2.000 -0.2246 0.01407 0.00802 -0.0092 1.0000 0.7046
-1.750 -0.2089 0.01400 0.00832 -0.0058 0.9998 0.8426
-1.500 -0.1205 0.01424 0.00843 -0.0171 0.9964 1.0000
-1.250 -0.0649 0.01461 0.00851 -0.0234 0.9852 1.0000
-1.000 -0.0118 0.01486 0.00854 -0.0290 0.9732 1.0000
-0.750 0.0396 0.01500 0.00850 -0.0340 0.9606 1.0000
-0.500 0.0895 0.01506 0.00842 -0.0386 0.9475 1.0000
-0.250 0.1393 0.01503 0.00828 -0.0430 0.9344 1.0000
0.000 0.1906 0.01492 0.00808 -0.0475 0.9217 1.0000
0.250 0.2472 0.01467 0.00777 -0.0527 0.9108 1.0000
0.500 0.3023 0.01430 0.00736 -0.0574 0.8991 1.0000
0.750 0.3449 0.01402 0.00704 -0.0597 0.8825 1.0000
1.000 0.3820 0.01380 0.00678 -0.0608 0.8634 1.0000
1.250 0.4175 0.01359 0.00653 -0.0615 0.8435 1.0000
1.500 0.4512 0.01343 0.00630 -0.0617 0.8234 1.0000
1.750 0.4755 0.01345 0.00626 -0.0603 0.7988 1.0000
2.000 0.5019 0.01346 0.00617 -0.0593 0.7760 1.0000
2.250 0.5250 0.01356 0.00620 -0.0577 0.7509 1.0000
2.500 0.5480 0.01369 0.00623 -0.0561 0.7261 1.0000
2.750 0.5718 0.01383 0.00625 -0.0546 0.7020 1.0000
3.000 0.5936 0.01402 0.00636 -0.0529 0.6757 1.0000
3.250 0.6160 0.01422 0.00648 -0.0513 0.6499 1.0000
3.500 0.6390 0.01444 0.00657 -0.0499 0.6248 1.0000
3.750 0.6609 0.01469 0.00674 -0.0483 0.5978 1.0000
4.000 0.6830 0.01497 0.00695 -0.0468 0.5711 1.0000
4.250 0.7053 0.01528 0.00715 -0.0454 0.5448 1.0000
4.500 0.7277 0.01562 0.00735 -0.0440 0.5190 1.0000
4.750 0.7494 0.01599 0.00765 -0.0426 0.4917 1.0000
5.000 0.7711 0.01639 0.00799 -0.0412 0.4649 1.0000
5.250 0.7929 0.01683 0.00833 -0.0398 0.4391 1.0000
5.500 0.8147 0.01730 0.00867 -0.0385 0.4139 1.0000
5.750 0.8358 0.01780 0.00913 -0.0372 0.3879 1.0000
6.000 0.8571 0.01834 0.00961 -0.0359 0.3632 1.0000
6.250 0.8784 0.01893 0.01009 -0.0346 0.3397 1.0000
6.500 0.8990 0.01954 0.01068 -0.0333 0.3158 1.0000
6.750 0.9201 0.02021 0.01123 -0.0321 0.2944 1.0000
7.000 0.9403 0.02090 0.01195 -0.0308 0.2724 1.0000
7.250 0.9608 0.02163 0.01262 -0.0295 0.2524 1.0000
7.500 0.9812 0.02247 0.01335 -0.0284 0.2338 1.0000
7.750 1.0007 0.02330 0.01425 -0.0270 0.2152 1.0000
8.000 1.0201 0.02419 0.01517 -0.0257 0.1980 1.0000
8.250 1.0394 0.02515 0.01612 -0.0244 0.1821 1.0000
8.500 1.0584 0.02618 0.01716 -0.0231 0.1674 1.0000
8.750 1.0772 0.02732 0.01834 -0.0218 0.1540 1.0000
9.000 1.0957 0.02855 0.01964 -0.0206 0.1417 1.0000
9.250 1.1147 0.02994 0.02102 -0.0194 0.1309 1.0000
9.500 1.1351 0.03141 0.02237 -0.0186 0.1208 1.0000
9.750 1.1492 0.03276 0.02407 -0.0166 0.1121 1.0000
10.000 1.1678 0.03463 0.02597 -0.0156 0.1048 1.0000
10.250 1.1821 0.03609 0.02766 -0.0139 0.0977 1.0000
10.500 1.1984 0.03838 0.03005 -0.0128 0.0922 1.0000
10.750 1.2082 0.04033 0.03236 -0.0106 0.0870 1.0000
11.000 1.2278 0.04277 0.03461 -0.0104 0.0815 1.0000
11.250 1.2266 0.04514 0.03756 -0.0071 0.0789 1.0000
11.500 1.2263 0.04772 0.04054 -0.0044 0.0759 1.0000
11.750 1.2328 0.04966 0.04258 -0.0025 0.0724 1.0000
12.000 1.2413 0.05309 0.04600 -0.0016 0.0692 1.0000
12.250 1.2238 0.05589 0.04921 0.0023 0.0685 1.0000
12.500 1.2028 0.05910 0.05275 0.0056 0.0680 1.0000
12.750 1.1801 0.06286 0.05680 0.0076 0.0677 1.0000
13.000 1.1548 0.06730 0.06150 0.0081 0.0676 1.0000
13.250 1.1281 0.07265 0.06708 0.0072 0.0678 1.0000
13.500 1.0999 0.07898 0.07361 0.0047 0.0682 1.0000
13.750 1.0719 0.08627 0.08105 0.0011 0.0688 1.0000
14.000 1.0432 0.09469 0.08959 -0.0036 0.0694 1.0000
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Polar data table (+)
Polar graphs
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