SD7080 (9.2%) (sd7080-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7080 (9.2%) (sd7080-il) Reynolds number: 500,000 Max Cl/Cd: 84.91 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7080-il-500000-n5.txt Download as CSV file: xf-sd7080-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4420 0.08442 0.08211 -0.0314 1.0000 0.0108
-9.000 -0.4445 0.08034 0.07807 -0.0332 1.0000 0.0110
-8.750 -0.4571 0.07448 0.07225 -0.0358 1.0000 0.0105
-8.500 -0.5539 0.04470 0.04229 -0.0560 0.9959 0.0093
-8.250 -0.5480 0.03481 0.03174 -0.0641 0.9878 0.0093
-8.000 -0.5292 0.02904 0.02538 -0.0681 0.9840 0.0094
-7.750 -0.5089 0.02526 0.02117 -0.0697 0.9795 0.0096
-7.500 -0.4841 0.02291 0.01850 -0.0708 0.9755 0.0097
-7.250 -0.4563 0.02124 0.01660 -0.0719 0.9725 0.0100
-7.000 -0.4283 0.01968 0.01479 -0.0727 0.9695 0.0102
-6.750 -0.4037 0.01848 0.01339 -0.0726 0.9643 0.0105
-6.500 -0.3766 0.01732 0.01205 -0.0729 0.9601 0.0107
-6.250 -0.3484 0.01624 0.01078 -0.0732 0.9567 0.0110
-6.000 -0.3243 0.01537 0.00976 -0.0726 0.9506 0.0112
-5.750 -0.2983 0.01456 0.00881 -0.0723 0.9456 0.0115
-5.500 -0.2719 0.01389 0.00804 -0.0721 0.9410 0.0119
-5.250 -0.2468 0.01331 0.00737 -0.0715 0.9348 0.0124
-5.000 -0.2209 0.01265 0.00660 -0.0710 0.9296 0.0125
-4.750 -0.1957 0.01204 0.00592 -0.0705 0.9233 0.0127
-4.500 -0.1700 0.01151 0.00530 -0.0700 0.9169 0.0129
-4.250 -0.1441 0.01105 0.00477 -0.0695 0.9105 0.0132
-4.000 -0.1181 0.01063 0.00429 -0.0690 0.9031 0.0135
-3.750 -0.0922 0.01009 0.00368 -0.0685 0.8960 0.0141
-3.500 -0.0658 0.00973 0.00326 -0.0681 0.8880 0.0150
-3.250 -0.0390 0.00946 0.00293 -0.0678 0.8796 0.0158
-3.000 -0.0121 0.00923 0.00264 -0.0674 0.8708 0.0167
-2.750 0.0149 0.00904 0.00239 -0.0671 0.8600 0.0180
-2.500 0.0419 0.00884 0.00215 -0.0667 0.8483 0.0210
-2.250 0.0687 0.00858 0.00193 -0.0664 0.8352 0.0375
-2.000 0.0952 0.00829 0.00174 -0.0661 0.8201 0.0791
-1.750 0.1216 0.00800 0.00159 -0.0658 0.8031 0.1341
-1.500 0.1481 0.00779 0.00146 -0.0655 0.7845 0.1859
-1.250 0.1743 0.00756 0.00136 -0.0652 0.7638 0.2512
-1.000 0.1995 0.00712 0.00130 -0.0649 0.7423 0.3886
-0.750 0.2245 0.00674 0.00127 -0.0644 0.7200 0.5242
-0.500 0.2498 0.00659 0.00127 -0.0638 0.6973 0.6077
-0.250 0.2755 0.00653 0.00128 -0.0633 0.6741 0.6639
0.000 0.3008 0.00649 0.00130 -0.0626 0.6510 0.7179
0.500 0.3504 0.00649 0.00138 -0.0609 0.6036 0.8129
0.750 0.3742 0.00651 0.00142 -0.0598 0.5808 0.8575
1.000 0.3977 0.00655 0.00147 -0.0586 0.5584 0.9041
1.250 0.4274 0.00663 0.00150 -0.0587 0.5352 0.9494
1.500 0.4649 0.00678 0.00153 -0.0608 0.5099 0.9834
1.750 0.4970 0.00695 0.00158 -0.0618 0.4860 1.0000
2.000 0.5227 0.00713 0.00165 -0.0614 0.4646 1.0000
2.250 0.5485 0.00732 0.00173 -0.0610 0.4429 1.0000
2.500 0.5745 0.00751 0.00182 -0.0607 0.4220 1.0000
2.750 0.6005 0.00771 0.00193 -0.0603 0.4009 1.0000
3.000 0.6265 0.00792 0.00205 -0.0600 0.3810 1.0000
3.250 0.6526 0.00813 0.00217 -0.0597 0.3608 1.0000
3.500 0.6785 0.00836 0.00232 -0.0594 0.3412 1.0000
3.750 0.7045 0.00859 0.00247 -0.0591 0.3224 1.0000
4.000 0.7305 0.00882 0.00263 -0.0588 0.3039 1.0000
4.250 0.7564 0.00907 0.00280 -0.0585 0.2857 1.0000
4.750 0.8080 0.00958 0.00320 -0.0579 0.2524 1.0000
5.000 0.8337 0.00985 0.00341 -0.0575 0.2352 1.0000
5.250 0.8593 0.01012 0.00364 -0.0572 0.2203 1.0000
5.500 0.8847 0.01042 0.00389 -0.0569 0.2039 1.0000
5.750 0.9096 0.01077 0.00416 -0.0565 0.1855 1.0000
6.000 0.9344 0.01112 0.00445 -0.0560 0.1671 1.0000
6.250 0.9594 0.01146 0.00474 -0.0556 0.1529 1.0000
6.500 0.9837 0.01185 0.00507 -0.0552 0.1350 1.0000
6.750 1.0072 0.01233 0.00545 -0.0546 0.1139 1.0000
7.000 1.0309 0.01279 0.00583 -0.0541 0.0962 1.0000
7.250 1.0546 0.01324 0.00623 -0.0535 0.0826 1.0000
7.500 1.0781 0.01368 0.00664 -0.0530 0.0711 1.0000
7.750 1.1008 0.01422 0.00711 -0.0523 0.0571 1.0000
8.000 1.1232 0.01476 0.00762 -0.0516 0.0456 1.0000
8.250 1.1451 0.01534 0.00816 -0.0508 0.0353 1.0000
8.500 1.1661 0.01600 0.00877 -0.0500 0.0250 1.0000
8.750 1.1864 0.01671 0.00944 -0.0490 0.0150 1.0000
9.000 1.2057 0.01751 0.01021 -0.0478 0.0092 1.0000
9.250 1.2263 0.01813 0.01088 -0.0469 0.0080 1.0000
9.500 1.2456 0.01885 0.01169 -0.0457 0.0069 1.0000
9.750 1.2646 0.01957 0.01249 -0.0445 0.0064 1.0000
10.000 1.2833 0.02027 0.01329 -0.0433 0.0061 1.0000
10.250 1.3012 0.02099 0.01411 -0.0420 0.0058 1.0000
10.500 1.3177 0.02179 0.01501 -0.0405 0.0056 1.0000
10.750 1.3327 0.02264 0.01596 -0.0389 0.0054 1.0000
11.000 1.3448 0.02352 0.01695 -0.0367 0.0052 1.0000
11.250 1.3541 0.02449 0.01803 -0.0343 0.0050 1.0000
11.500 1.3622 0.02553 0.01918 -0.0318 0.0049 1.0000
11.750 1.3698 0.02664 0.02039 -0.0295 0.0047 1.0000
12.000 1.3747 0.02796 0.02182 -0.0271 0.0046 1.0000
12.250 1.3767 0.02954 0.02352 -0.0247 0.0044 1.0000
12.500 1.3781 0.03125 0.02535 -0.0225 0.0043 1.0000
12.750 1.3749 0.03345 0.02768 -0.0204 0.0042 1.0000
13.000 1.3688 0.03608 0.03046 -0.0187 0.0040 1.0000
13.250 1.3671 0.03854 0.03306 -0.0177 0.0040 1.0000
13.500 1.3652 0.04121 0.03586 -0.0171 0.0040 1.0000
13.750 1.3620 0.04426 0.03905 -0.0170 0.0039 1.0000
14.000 1.3565 0.04783 0.04276 -0.0174 0.0039 1.0000
14.250 1.3510 0.05167 0.04674 -0.0183 0.0039 1.0000
14.500 1.3458 0.05574 0.05099 -0.0196 0.0038 1.0000
14.750 1.3342 0.06099 0.05639 -0.0216 0.0039 1.0000
15.000 1.3248 0.06622 0.06177 -0.0239 0.0038 1.0000
15.250 1.3136 0.07197 0.06767 -0.0266 0.0038 1.0000
15.500 1.3008 0.07824 0.07409 -0.0297 0.0038 1.0000
15.750 1.2874 0.08485 0.08083 -0.0331 0.0038 1.0000
16.000 1.2741 0.09163 0.08776 -0.0367 0.0038 1.0000
16.250 1.2606 0.09866 0.09493 -0.0404 0.0038 1.0000
16.500 1.2462 0.10600 0.10239 -0.0443 0.0038 1.0000
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Polar data table (+)
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