SD7090 (10%) (sd7090-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7090 (10%) (sd7090-il) Reynolds number: 50,000 Max Cl/Cd: 34.21 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7090-il-50000-n5.txt Download as CSV file: xf-sd7090-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5031 0.10421 0.09672 -0.0262 1.0000 0.0552
-10.000 -0.5048 0.09954 0.09211 -0.0281 1.0000 0.0552
-9.750 -0.5087 0.09452 0.08716 -0.0306 1.0000 0.0552
-9.500 -0.5135 0.08937 0.08207 -0.0333 1.0000 0.0552
-9.250 -0.5222 0.08339 0.07615 -0.0371 1.0000 0.0551
-9.000 -0.5322 0.07804 0.07085 -0.0402 1.0000 0.0549
-8.750 -0.5465 0.07344 0.06629 -0.0417 1.0000 0.0547
-8.500 -0.5597 0.06866 0.06145 -0.0430 1.0000 0.0547
-8.250 -0.5703 0.06411 0.05677 -0.0435 1.0000 0.0547
-8.000 -0.5792 0.05953 0.05197 -0.0436 1.0000 0.0549
-7.750 -0.5833 0.05522 0.04737 -0.0430 1.0000 0.0551
-7.250 -0.5765 0.04769 0.03927 -0.0410 1.0000 0.0559
-7.000 -0.5671 0.04465 0.03597 -0.0398 1.0000 0.0568
-6.750 -0.5555 0.04186 0.03292 -0.0385 1.0000 0.0580
-6.500 -0.5416 0.03952 0.03034 -0.0372 1.0000 0.0600
-6.250 -0.5269 0.03715 0.02759 -0.0359 1.0000 0.0634
-6.000 -0.5105 0.03460 0.02448 -0.0345 1.0000 0.0666
-5.750 -0.4923 0.03246 0.02211 -0.0332 1.0000 0.0691
-5.500 -0.4730 0.03077 0.02030 -0.0320 1.0000 0.0724
-5.250 -0.4529 0.02924 0.01845 -0.0307 1.0000 0.0783
-5.000 -0.4330 0.02786 0.01701 -0.0294 1.0000 0.0848
-4.750 -0.4120 0.02662 0.01552 -0.0281 1.0000 0.0935
-4.500 -0.3922 0.02554 0.01449 -0.0269 1.0000 0.1040
-4.250 -0.3720 0.02456 0.01349 -0.0256 1.0000 0.1177
-4.000 -0.3515 0.02366 0.01254 -0.0244 1.0000 0.1344
-3.750 -0.3309 0.02281 0.01172 -0.0232 1.0000 0.1540
-3.500 -0.3097 0.02202 0.01098 -0.0223 1.0000 0.1801
-3.250 -0.2898 0.02126 0.01037 -0.0212 1.0000 0.2123
-3.000 -0.2705 0.02050 0.00986 -0.0202 1.0000 0.2613
-2.750 -0.2516 0.01979 0.00951 -0.0190 1.0000 0.3338
-2.500 -0.2343 0.01911 0.00934 -0.0174 1.0000 0.4331
-2.250 -0.2194 0.01856 0.00937 -0.0149 1.0000 0.5543
-2.000 -0.2063 0.01823 0.00951 -0.0114 1.0000 0.6817
-1.750 -0.1725 0.01814 0.00973 -0.0110 0.9933 0.8303
-1.500 -0.0877 0.01817 0.00956 -0.0212 0.9906 0.9945
-1.250 -0.0423 0.01836 0.00943 -0.0256 0.9778 1.0000
-1.000 -0.0002 0.01849 0.00930 -0.0291 0.9632 1.0000
-0.750 0.0410 0.01860 0.00918 -0.0323 0.9483 1.0000
-0.500 0.0820 0.01868 0.00907 -0.0353 0.9333 1.0000
-0.250 0.1230 0.01873 0.00895 -0.0381 0.9183 1.0000
0.000 0.1645 0.01873 0.00883 -0.0408 0.9033 1.0000
0.250 0.2060 0.01870 0.00870 -0.0434 0.8881 1.0000
0.500 0.2452 0.01866 0.00857 -0.0454 0.8721 1.0000
0.750 0.2833 0.01861 0.00845 -0.0470 0.8556 1.0000
1.000 0.3180 0.01859 0.00837 -0.0479 0.8373 1.0000
1.250 0.3497 0.01860 0.00832 -0.0483 0.8175 1.0000
1.500 0.3821 0.01860 0.00826 -0.0486 0.7978 1.0000
1.750 0.4134 0.01861 0.00822 -0.0486 0.7779 1.0000
2.000 0.4401 0.01871 0.00827 -0.0479 0.7555 1.0000
2.250 0.4688 0.01877 0.00827 -0.0474 0.7344 1.0000
2.500 0.4935 0.01893 0.00840 -0.0463 0.7110 1.0000
2.750 0.5203 0.01907 0.00846 -0.0455 0.6888 1.0000
3.000 0.5442 0.01928 0.00864 -0.0443 0.6645 1.0000
3.250 0.5692 0.01948 0.00877 -0.0432 0.6410 1.0000
3.500 0.5931 0.01972 0.00900 -0.0420 0.6163 1.0000
3.750 0.6167 0.02000 0.00923 -0.0408 0.5917 1.0000
4.000 0.6408 0.02028 0.00943 -0.0397 0.5678 1.0000
4.250 0.6634 0.02062 0.00978 -0.0384 0.5423 1.0000
4.500 0.6863 0.02098 0.01010 -0.0372 0.5175 1.0000
4.750 0.7093 0.02137 0.01042 -0.0360 0.4935 1.0000
5.000 0.7313 0.02181 0.01085 -0.0347 0.4682 1.0000
5.250 0.7535 0.02228 0.01130 -0.0335 0.4442 1.0000
5.500 0.7753 0.02278 0.01178 -0.0323 0.4202 1.0000
5.750 0.7967 0.02333 0.01233 -0.0311 0.3964 1.0000
6.000 0.8180 0.02391 0.01286 -0.0299 0.3741 1.0000
6.250 0.8387 0.02455 0.01355 -0.0286 0.3513 1.0000
6.500 0.8591 0.02521 0.01418 -0.0274 0.3298 1.0000
6.750 0.8792 0.02594 0.01494 -0.0261 0.3088 1.0000
7.000 0.8988 0.02670 0.01572 -0.0249 0.2884 1.0000
7.250 0.9183 0.02751 0.01654 -0.0236 0.2700 1.0000
7.500 0.9370 0.02838 0.01748 -0.0223 0.2510 1.0000
7.750 0.9555 0.02932 0.01847 -0.0210 0.2335 1.0000
8.000 0.9733 0.03029 0.01950 -0.0197 0.2169 1.0000
8.250 0.9907 0.03134 0.02060 -0.0183 0.2016 1.0000
8.500 1.0074 0.03245 0.02180 -0.0170 0.1871 1.0000
8.750 1.0234 0.03364 0.02307 -0.0156 0.1735 1.0000
9.000 1.0389 0.03492 0.02444 -0.0141 0.1612 1.0000
9.250 1.0534 0.03624 0.02584 -0.0127 0.1498 1.0000
9.500 1.0681 0.03758 0.02715 -0.0113 0.1401 1.0000
9.750 1.0801 0.03917 0.02904 -0.0097 0.1299 1.0000
10.000 1.0922 0.04086 0.03088 -0.0081 0.1215 1.0000
10.250 1.1037 0.04242 0.03248 -0.0066 0.1141 1.0000
10.500 1.1113 0.04447 0.03481 -0.0048 0.1070 1.0000
10.750 1.1202 0.04618 0.03658 -0.0032 0.1013 1.0000
11.000 1.1244 0.04850 0.03914 -0.0013 0.0965 1.0000
11.250 1.1244 0.05088 0.04179 0.0007 0.0920 1.0000
11.500 1.1302 0.05263 0.04356 0.0022 0.0877 1.0000
11.750 1.1256 0.05568 0.04688 0.0038 0.0848 1.0000
12.000 1.1144 0.05936 0.05091 0.0049 0.0826 1.0000
12.250 1.1017 0.06331 0.05514 0.0053 0.0807 1.0000
12.500 1.0880 0.06759 0.05963 0.0049 0.0789 1.0000
12.750 1.0746 0.07212 0.06433 0.0038 0.0774 1.0000
13.000 1.0830 0.07412 0.06623 0.0042 0.0743 1.0000
13.250 1.0559 0.08105 0.07341 0.0010 0.0741 1.0000
13.500 1.0270 0.08922 0.08177 -0.0035 0.0743 1.0000
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Polar data table (+)
Polar graphs
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