SD7080 (9.2%) (sd7080-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7080 (9.2%) (sd7080-il) Reynolds number: 50,000 Max Cl/Cd: 33.63 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7080-il-50000.txt Download as CSV file: xf-sd7080-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SD7080 (9.2%)
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3953 0.09732 0.09057 -0.0155 1.0000 0.2632
-7.750 -0.4147 0.09677 0.09018 -0.0158 1.0000 0.2739
-7.500 -0.4095 0.09370 0.08718 -0.0144 1.0000 0.2885
-7.250 -0.4053 0.09074 0.08428 -0.0128 1.0000 0.3030
-7.000 -0.4033 0.08795 0.08158 -0.0110 1.0000 0.3176
-6.750 -0.4011 0.08523 0.07894 -0.0091 1.0000 0.3321
-6.500 -0.4016 0.08271 0.07652 -0.0069 1.0000 0.3466
-6.250 -0.4119 0.08091 0.07485 -0.0047 1.0000 0.3626
-5.750 -0.3975 0.07470 0.06875 0.0005 1.0000 0.3970
-5.500 -0.3952 0.07226 0.06638 0.0032 1.0000 0.4152
-5.000 -0.4051 0.04984 0.04284 -0.0382 1.0000 0.1523
-4.750 -0.3837 0.04333 0.03537 -0.0414 1.0000 0.1288
-4.500 -0.3639 0.03989 0.03165 -0.0411 1.0000 0.1237
-4.250 -0.3419 0.03637 0.02762 -0.0411 1.0000 0.1194
-4.000 -0.3180 0.03338 0.02405 -0.0409 1.0000 0.1173
-3.750 -0.2950 0.03126 0.02160 -0.0403 1.0000 0.1211
-3.500 -0.2700 0.02926 0.01906 -0.0397 1.0000 0.1258
-3.250 -0.2453 0.02731 0.01685 -0.0389 1.0000 0.1305
-3.000 -0.2206 0.02574 0.01509 -0.0379 1.0000 0.1395
-2.750 -0.1965 0.02430 0.01365 -0.0370 1.0000 0.1595
-2.500 -0.1719 0.02281 0.01226 -0.0359 1.0000 0.2011
-2.250 -0.1476 0.01999 0.01100 -0.0351 1.0000 0.4133
-2.000 -0.1266 0.01760 0.01067 -0.0285 1.0000 1.0000
-1.750 -0.1047 0.01767 0.01010 -0.0286 1.0000 1.0000
-1.500 -0.0836 0.01782 0.00978 -0.0283 1.0000 1.0000
-1.250 -0.0629 0.01803 0.00960 -0.0280 1.0000 1.0000
-1.000 -0.0424 0.01829 0.00954 -0.0276 1.0000 1.0000
-0.750 -0.0223 0.01861 0.00958 -0.0273 1.0000 1.0000
-0.500 -0.0025 0.01897 0.00971 -0.0269 1.0000 1.0000
-0.250 0.0168 0.01940 0.00991 -0.0266 1.0000 1.0000
0.000 0.0358 0.01988 0.01020 -0.0264 1.0000 1.0000
0.250 0.0542 0.02042 0.01059 -0.0262 1.0000 1.0000
0.500 0.0723 0.02103 0.01107 -0.0260 1.0000 1.0000
0.750 0.0898 0.02171 0.01161 -0.0259 1.0000 1.0000
1.000 0.1108 0.02253 0.01233 -0.0267 0.9980 1.0000
1.250 0.1712 0.02401 0.01369 -0.0344 0.9768 1.0000
1.500 0.2295 0.02528 0.01487 -0.0414 0.9553 1.0000
1.750 0.2811 0.02624 0.01580 -0.0468 0.9326 1.0000
2.000 0.3320 0.02704 0.01659 -0.0517 0.9100 1.0000
2.250 0.3829 0.02761 0.01719 -0.0561 0.8872 1.0000
2.500 0.4269 0.02803 0.01766 -0.0591 0.8638 1.0000
2.750 0.4825 0.02810 0.01784 -0.0633 0.8423 1.0000
3.000 0.5241 0.02818 0.01800 -0.0651 0.8180 1.0000
3.250 0.5817 0.02760 0.01759 -0.0683 0.7980 1.0000
3.500 0.6169 0.02744 0.01753 -0.0683 0.7732 1.0000
3.750 0.6584 0.02693 0.01713 -0.0686 0.7501 1.0000
4.000 0.7001 0.02624 0.01657 -0.0685 0.7268 1.0000
4.250 0.7322 0.02598 0.01639 -0.0673 0.7005 1.0000
4.500 0.7641 0.02573 0.01620 -0.0660 0.6737 1.0000
4.750 0.7944 0.02562 0.01615 -0.0646 0.6461 1.0000
5.000 0.8226 0.02568 0.01622 -0.0629 0.6176 1.0000
5.250 0.8490 0.02592 0.01645 -0.0612 0.5884 1.0000
5.500 0.8743 0.02630 0.01682 -0.0596 0.5592 1.0000
5.750 0.8987 0.02681 0.01735 -0.0579 0.5299 1.0000
6.000 0.9224 0.02743 0.01794 -0.0562 0.5009 1.0000
6.250 0.9457 0.02812 0.01862 -0.0546 0.4723 1.0000
6.500 0.9688 0.02891 0.01938 -0.0531 0.4444 1.0000
6.750 0.9919 0.02974 0.02019 -0.0515 0.4169 1.0000
7.000 1.0133 0.03074 0.02120 -0.0500 0.3898 1.0000
7.250 1.0330 0.03192 0.02248 -0.0484 0.3634 1.0000
7.500 1.0529 0.03315 0.02376 -0.0468 0.3379 1.0000
7.750 1.0745 0.03437 0.02497 -0.0453 0.3137 1.0000
8.000 1.0935 0.03572 0.02640 -0.0437 0.2895 1.0000
8.250 1.1105 0.03737 0.02817 -0.0420 0.2670 1.0000
8.500 1.1316 0.03875 0.02946 -0.0406 0.2448 1.0000
8.750 1.1443 0.04079 0.03178 -0.0386 0.2247 1.0000
9.000 1.1599 0.04284 0.03400 -0.0368 0.2059 1.0000
9.250 1.1789 0.04471 0.03576 -0.0354 0.1867 1.0000
9.500 1.1882 0.04746 0.03880 -0.0332 0.1716 1.0000
9.750 1.1956 0.05019 0.04178 -0.0310 0.1570 1.0000
10.000 1.2018 0.05297 0.04475 -0.0288 0.1433 1.0000
10.250 1.2074 0.05572 0.04763 -0.0267 0.1304 1.0000
10.500 1.2138 0.05836 0.05031 -0.0248 0.1180 1.0000
10.750 1.1952 0.06287 0.05540 -0.0218 0.1159 1.0000
11.000 1.1742 0.06748 0.06040 -0.0194 0.1146 1.0000
11.250 1.1492 0.07201 0.06519 -0.0172 0.1147 1.0000
11.500 1.1227 0.07717 0.07053 -0.0164 0.1158 1.0000
11.750 1.0970 0.08308 0.07657 -0.0172 0.1170 1.0000
12.000 1.0722 0.08986 0.08344 -0.0194 0.1180 1.0000
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Polar data table (+)
Polar graphs
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