SD7080 (9.2%) (sd7080-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7080 (9.2%) (sd7080-il) Reynolds number: 500,000 Max Cl/Cd: 91.53 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7080-il-500000.txt Download as CSV file: xf-sd7080-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4276 0.09601 0.09368 -0.0301 1.0000 0.0204
-9.500 -0.4352 0.09071 0.08842 -0.0309 1.0000 0.0211
-9.250 -0.4339 0.08721 0.08494 -0.0321 1.0000 0.0212
-9.000 -0.4303 0.08459 0.08234 -0.0326 1.0000 0.0216
-8.750 -0.4289 0.08163 0.07940 -0.0334 1.0000 0.0219
-8.500 -0.4291 0.07864 0.07645 -0.0343 1.0000 0.0223
-8.250 -0.4335 0.07549 0.07334 -0.0350 1.0000 0.0228
-8.000 -0.4458 0.07259 0.07050 -0.0348 1.0000 0.0230
-7.750 -0.4669 0.06975 0.06773 -0.0339 1.0000 0.0230
-7.500 -0.4843 0.06566 0.06365 -0.0351 1.0000 0.0229
-7.250 -0.4903 0.06116 0.05912 -0.0373 0.9995 0.0234
-7.000 -0.4583 0.05005 0.04755 -0.0512 0.9948 0.0269
-6.750 -0.4475 0.03950 0.03643 -0.0584 0.9890 0.0279
-6.500 -0.4201 0.03675 0.03367 -0.0611 0.9865 0.0288
-6.250 -0.3893 0.03436 0.03116 -0.0640 0.9845 0.0301
-6.000 -0.3617 0.03166 0.02822 -0.0658 0.9808 0.0322
-5.750 -0.3249 0.03207 0.02814 -0.0668 0.9771 0.0357
-5.500 -0.3031 0.01880 0.01352 -0.0678 0.9737 0.0207
-5.250 -0.2664 0.01752 0.01204 -0.0697 0.9723 0.0205
-5.000 -0.2302 0.01549 0.00978 -0.0716 0.9712 0.0207
-4.750 -0.2035 0.01414 0.00831 -0.0714 0.9659 0.0209
-4.500 -0.1704 0.01305 0.00713 -0.0724 0.9627 0.0209
-4.250 -0.1372 0.01194 0.00594 -0.0735 0.9598 0.0214
-4.000 -0.1054 0.01119 0.00514 -0.0742 0.9564 0.0222
-3.750 -0.0795 0.01068 0.00461 -0.0737 0.9497 0.0232
-3.500 -0.0496 0.01022 0.00411 -0.0739 0.9451 0.0246
-3.250 -0.0233 0.00987 0.00371 -0.0733 0.9387 0.0261
-3.000 0.0033 0.00948 0.00327 -0.0728 0.9322 0.0295
-2.750 0.0296 0.00912 0.00292 -0.0721 0.9257 0.0396
-2.500 0.0539 0.00841 0.00259 -0.0714 0.9177 0.1344
-2.250 0.0791 0.00795 0.00240 -0.0708 0.9100 0.2162
-2.000 0.1040 0.00746 0.00223 -0.0702 0.9016 0.3167
-1.750 0.1286 0.00696 0.00212 -0.0696 0.8921 0.4348
-1.500 0.1532 0.00649 0.00202 -0.0688 0.8830 0.5579
-1.250 0.1772 0.00611 0.00197 -0.0678 0.8720 0.6664
-1.000 0.2013 0.00586 0.00194 -0.0666 0.8600 0.7446
-0.750 0.2250 0.00566 0.00190 -0.0652 0.8472 0.8114
-0.500 0.2483 0.00552 0.00186 -0.0637 0.8332 0.8632
-0.250 0.2720 0.00544 0.00180 -0.0622 0.8174 0.9059
0.000 0.3004 0.00541 0.00173 -0.0618 0.8000 0.9460
0.250 0.3392 0.00541 0.00164 -0.0638 0.7798 0.9755
0.500 0.3812 0.00546 0.00155 -0.0667 0.7567 0.9948
0.750 0.4110 0.00555 0.00151 -0.0671 0.7320 1.0000
1.000 0.4348 0.00568 0.00150 -0.0661 0.7074 1.0000
1.250 0.4591 0.00584 0.00151 -0.0653 0.6823 1.0000
1.500 0.4839 0.00599 0.00154 -0.0647 0.6567 1.0000
1.750 0.5090 0.00617 0.00158 -0.0640 0.6312 1.0000
2.000 0.5342 0.00635 0.00164 -0.0634 0.6060 1.0000
2.250 0.5595 0.00655 0.00171 -0.0629 0.5800 1.0000
2.500 0.5851 0.00674 0.00180 -0.0624 0.5546 1.0000
2.750 0.6106 0.00695 0.00189 -0.0619 0.5294 1.0000
3.000 0.6362 0.00717 0.00200 -0.0615 0.5043 1.0000
3.250 0.6619 0.00739 0.00212 -0.0611 0.4795 1.0000
3.500 0.6875 0.00762 0.00226 -0.0607 0.4550 1.0000
3.750 0.7131 0.00787 0.00241 -0.0603 0.4311 1.0000
4.000 0.7388 0.00811 0.00256 -0.0599 0.4076 1.0000
4.250 0.7644 0.00837 0.00273 -0.0595 0.3848 1.0000
4.500 0.7899 0.00864 0.00293 -0.0591 0.3625 1.0000
4.750 0.8155 0.00891 0.00312 -0.0587 0.3405 1.0000
5.000 0.8409 0.00919 0.00333 -0.0584 0.3197 1.0000
5.250 0.8662 0.00949 0.00356 -0.0580 0.2993 1.0000
5.500 0.8915 0.00979 0.00381 -0.0576 0.2788 1.0000
5.750 0.9163 0.01014 0.00407 -0.0572 0.2578 1.0000
6.000 0.9412 0.01047 0.00434 -0.0567 0.2360 1.0000
6.250 0.9658 0.01085 0.00465 -0.0563 0.2163 1.0000
6.500 0.9904 0.01120 0.00496 -0.0558 0.1979 1.0000
6.750 1.0148 0.01159 0.00529 -0.0553 0.1789 1.0000
7.000 1.0384 0.01205 0.00565 -0.0548 0.1594 1.0000
7.250 1.0623 0.01247 0.00603 -0.0543 0.1402 1.0000
7.500 1.0854 0.01297 0.00644 -0.0537 0.1211 1.0000
8.000 1.1314 0.01396 0.00733 -0.0524 0.0903 1.0000
8.250 1.1540 0.01449 0.00781 -0.0517 0.0767 1.0000
8.500 1.1760 0.01505 0.00835 -0.0510 0.0635 1.0000
8.750 1.1970 0.01571 0.00893 -0.0501 0.0494 1.0000
9.000 1.2164 0.01651 0.00965 -0.0490 0.0335 1.0000
9.250 1.2325 0.01766 0.01069 -0.0474 0.0183 1.0000
9.500 1.2497 0.01865 0.01172 -0.0459 0.0143 1.0000
9.750 1.2678 0.01947 0.01262 -0.0445 0.0127 1.0000
10.000 1.2826 0.02055 0.01378 -0.0427 0.0116 1.0000
10.250 1.2957 0.02167 0.01502 -0.0407 0.0111 1.0000
10.500 1.3097 0.02262 0.01609 -0.0389 0.0105 1.0000
10.750 1.3201 0.02364 0.01722 -0.0365 0.0102 1.0000
11.000 1.3271 0.02474 0.01843 -0.0336 0.0100 1.0000
11.250 1.3333 0.02593 0.01971 -0.0309 0.0096 1.0000
11.500 1.3387 0.02719 0.02107 -0.0283 0.0094 1.0000
11.750 1.3434 0.02855 0.02253 -0.0260 0.0090 1.0000
12.000 1.3438 0.03031 0.02441 -0.0234 0.0088 1.0000
12.250 1.3428 0.03231 0.02651 -0.0212 0.0085 1.0000
12.500 1.3373 0.03489 0.02922 -0.0191 0.0084 1.0000
12.750 1.3303 0.03785 0.03233 -0.0173 0.0082 1.0000
13.000 1.3267 0.04070 0.03532 -0.0162 0.0082 1.0000
13.250 1.3251 0.04349 0.03826 -0.0156 0.0081 1.0000
13.500 1.3227 0.04652 0.04144 -0.0153 0.0081 1.0000
13.750 1.3197 0.04981 0.04488 -0.0155 0.0080 1.0000
14.000 1.3162 0.05332 0.04855 -0.0160 0.0080 1.0000
14.250 1.3087 0.05759 0.05297 -0.0169 0.0080 1.0000
14.500 1.3031 0.06178 0.05733 -0.0183 0.0079 1.0000
14.750 1.2948 0.06658 0.06228 -0.0200 0.0079 1.0000
15.000 1.2861 0.07168 0.06755 -0.0223 0.0079 1.0000
15.250 1.2761 0.07721 0.07324 -0.0248 0.0079 1.0000
15.500 1.2641 0.08335 0.07954 -0.0279 0.0079 1.0000
15.750 1.2516 0.08982 0.08617 -0.0313 0.0079 1.0000
16.000 1.2379 0.09677 0.09328 -0.0351 0.0079 1.0000
16.250 1.2232 0.10418 0.10085 -0.0392 0.0079 1.0000
16.500 1.2094 0.11178 0.10860 -0.0437 0.0079 1.0000
16.750 1.1938 0.11989 0.11686 -0.0485 0.0079 1.0000
17.000 1.1767 0.12863 0.12575 -0.0538 0.0080 1.0000
17.250 1.1623 0.13724 0.13450 -0.0592 0.0080 1.0000
17.500 1.1449 0.14669 0.14408 -0.0651 0.0081 1.0000
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Polar data table (+)
Polar graphs
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