SD7090 (10%) (sd7090-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7090 (10%) (sd7090-il) Reynolds number: 50,000 Max Cl/Cd: 30.73 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7090-il-50000.txt Download as CSV file: xf-sd7090-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4520 0.11141 0.10418 -0.0082 1.0000 0.2646
-9.000 -0.4344 0.10663 0.09939 -0.0074 1.0000 0.2735
-8.750 -0.4428 0.10432 0.09718 -0.0080 1.0000 0.2828
-8.500 -0.4454 0.10206 0.09499 -0.0078 1.0000 0.2953
-8.250 -0.4273 0.09766 0.09059 -0.0067 1.0000 0.3073
-8.000 -0.4226 0.09456 0.08754 -0.0059 1.0000 0.3218
-7.750 -0.4204 0.09172 0.08476 -0.0050 1.0000 0.3380
-7.500 -0.4155 0.08865 0.08175 -0.0040 1.0000 0.3522
-7.250 -0.4119 0.08559 0.07876 -0.0030 1.0000 0.3656
-7.000 -0.4108 0.08268 0.07591 -0.0019 1.0000 0.3790
-6.250 -0.5186 0.05253 0.04499 -0.0351 1.0000 0.1443
-6.000 -0.5087 0.04853 0.04075 -0.0344 1.0000 0.1433
-5.750 -0.4973 0.04462 0.03652 -0.0336 1.0000 0.1422
-5.500 -0.4838 0.04089 0.03235 -0.0327 1.0000 0.1411
-5.250 -0.4680 0.03746 0.02842 -0.0316 1.0000 0.1414
-5.000 -0.4506 0.03460 0.02489 -0.0304 1.0000 0.1457
-4.750 -0.4313 0.03246 0.02279 -0.0292 1.0000 0.1540
-4.500 -0.4106 0.03008 0.01993 -0.0279 1.0000 0.1620
-4.250 -0.3897 0.02831 0.01798 -0.0267 1.0000 0.1765
-4.000 -0.3688 0.02670 0.01635 -0.0254 1.0000 0.1945
-3.750 -0.3473 0.02529 0.01485 -0.0241 1.0000 0.2184
-3.500 -0.3258 0.02393 0.01359 -0.0227 1.0000 0.2474
-3.250 -0.3041 0.02266 0.01250 -0.0214 1.0000 0.2865
-3.000 -0.2826 0.02139 0.01151 -0.0200 1.0000 0.3453
-2.750 -0.2638 0.01988 0.01076 -0.0179 1.0000 0.4550
-2.500 -0.2561 0.01851 0.01069 -0.0122 1.0000 0.6502
-2.250 -0.0962 0.01867 0.01069 -0.0283 1.0000 1.0000
-2.000 -0.1124 0.01823 0.01016 -0.0233 1.0000 1.0000
-1.750 -0.1162 0.01807 0.00979 -0.0197 1.0000 1.0000
-1.500 -0.1112 0.01809 0.00958 -0.0171 1.0000 1.0000
-1.250 -0.1014 0.01822 0.00947 -0.0153 1.0000 1.0000
-1.000 -0.0890 0.01843 0.00947 -0.0138 1.0000 1.0000
-0.750 -0.0753 0.01872 0.00955 -0.0126 1.0000 1.0000
-0.500 -0.0608 0.01906 0.00973 -0.0116 1.0000 1.0000
-0.250 -0.0460 0.01947 0.00996 -0.0107 1.0000 1.0000
0.000 -0.0309 0.01994 0.01030 -0.0100 1.0000 1.0000
0.250 -0.0158 0.02047 0.01071 -0.0094 1.0000 1.0000
0.500 -0.0008 0.02108 0.01120 -0.0089 1.0000 1.0000
0.750 0.0381 0.02209 0.01210 -0.0130 0.9898 1.0000
1.000 0.1001 0.02332 0.01323 -0.0209 0.9687 1.0000
1.250 0.1571 0.02423 0.01408 -0.0275 0.9464 1.0000
1.500 0.2113 0.02494 0.01476 -0.0332 0.9239 1.0000
1.750 0.2682 0.02546 0.01530 -0.0389 0.9015 1.0000
2.000 0.3176 0.02582 0.01569 -0.0430 0.8782 1.0000
2.250 0.3772 0.02589 0.01585 -0.0482 0.8560 1.0000
2.500 0.4285 0.02588 0.01592 -0.0516 0.8325 1.0000
2.750 0.4848 0.02552 0.01568 -0.0551 0.8102 1.0000
3.000 0.5240 0.02544 0.01567 -0.0558 0.7852 1.0000
3.250 0.5734 0.02489 0.01520 -0.0572 0.7624 1.0000
3.500 0.6022 0.02496 0.01533 -0.0560 0.7353 1.0000
3.750 0.6320 0.02497 0.01537 -0.0548 0.7086 1.0000
4.000 0.6623 0.02492 0.01533 -0.0534 0.6823 1.0000
4.250 0.6926 0.02486 0.01526 -0.0519 0.6559 1.0000
4.500 0.7159 0.02514 0.01554 -0.0499 0.6275 1.0000
4.750 0.7394 0.02546 0.01585 -0.0479 0.5992 1.0000
5.000 0.7629 0.02582 0.01619 -0.0460 0.5711 1.0000
5.250 0.7864 0.02623 0.01659 -0.0441 0.5430 1.0000
5.500 0.8101 0.02668 0.01697 -0.0423 0.5154 1.0000
5.750 0.8344 0.02716 0.01735 -0.0406 0.4882 1.0000
6.000 0.8558 0.02785 0.01804 -0.0388 0.4605 1.0000
6.250 0.8761 0.02869 0.01890 -0.0370 0.4336 1.0000
6.500 0.8974 0.02956 0.01974 -0.0353 0.4080 1.0000
6.750 0.9215 0.03030 0.02033 -0.0339 0.3833 1.0000
7.000 0.9388 0.03152 0.02171 -0.0320 0.3589 1.0000
7.250 0.9606 0.03255 0.02267 -0.0306 0.3362 1.0000
7.500 0.9783 0.03392 0.02416 -0.0288 0.3144 1.0000
7.750 1.0019 0.03499 0.02505 -0.0276 0.2936 1.0000
8.000 1.0162 0.03676 0.02707 -0.0257 0.2748 1.0000
8.250 1.0325 0.03841 0.02888 -0.0239 0.2566 1.0000
8.500 1.0489 0.04027 0.03087 -0.0223 0.2405 1.0000
8.750 1.0642 0.04216 0.03288 -0.0206 0.2252 1.0000
9.000 1.0758 0.04462 0.03557 -0.0187 0.2128 1.0000
9.250 1.0878 0.04698 0.03810 -0.0169 0.2008 1.0000
9.500 1.1041 0.04923 0.04041 -0.0156 0.1894 1.0000
9.750 1.0963 0.05319 0.04492 -0.0128 0.1834 1.0000
10.000 1.1083 0.05575 0.04754 -0.0114 0.1742 1.0000
10.250 1.0892 0.06045 0.05270 -0.0087 0.1714 1.0000
10.500 1.0653 0.06552 0.05807 -0.0066 0.1703 1.0000
10.750 1.0280 0.07129 0.06402 -0.0048 0.1718 1.0000
11.000 0.9895 0.07812 0.07090 -0.0053 0.1742 1.0000
11.250 0.9576 0.08608 0.07887 -0.0081 0.1759 1.0000
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Polar data table (+)
Polar graphs
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