S7012 8.75% (s7012-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S7012 8.75% (s7012-il) Reynolds number: 500,000 Max Cl/Cd: 85.68 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s7012-il-500000-n5.txt Download as CSV file: xf-s7012-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S7012 8.75%
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4490 0.04735 0.04541 -0.0350 1.0000 0.0072
-7.250 -0.5216 0.03996 0.03730 -0.0456 1.0000 0.0059
-7.000 -0.5193 0.03399 0.03095 -0.0459 1.0000 0.0057
-6.750 -0.5116 0.02872 0.02522 -0.0454 1.0000 0.0057
-6.500 -0.4836 0.02386 0.01976 -0.0479 0.9960 0.0057
-6.250 -0.4536 0.02068 0.01607 -0.0496 0.9912 0.0057
-6.000 -0.4219 0.01860 0.01361 -0.0510 0.9859 0.0059
-5.750 -0.3913 0.01667 0.01132 -0.0521 0.9800 0.0061
-5.500 -0.3601 0.01475 0.00913 -0.0532 0.9743 0.0064
-5.250 -0.3275 0.01366 0.00790 -0.0545 0.9684 0.0067
-5.000 -0.2949 0.01280 0.00694 -0.0557 0.9608 0.0069
-4.750 -0.2617 0.01212 0.00618 -0.0570 0.9522 0.0074
-4.500 -0.2281 0.01154 0.00552 -0.0583 0.9417 0.0081
-4.250 -0.1959 0.01092 0.00480 -0.0592 0.9277 0.0084
-4.000 -0.1656 0.01036 0.00413 -0.0597 0.9106 0.0085
-3.750 -0.1369 0.00993 0.00358 -0.0598 0.8908 0.0087
-3.500 -0.1093 0.00960 0.00312 -0.0595 0.8696 0.0090
-3.250 -0.0823 0.00936 0.00272 -0.0592 0.8475 0.0093
-3.000 -0.0555 0.00913 0.00235 -0.0588 0.8251 0.0102
-2.750 -0.0287 0.00897 0.00207 -0.0584 0.8027 0.0125
-2.500 -0.0021 0.00869 0.00181 -0.0581 0.7803 0.0387
-2.250 0.0241 0.00828 0.00159 -0.0580 0.7585 0.1153
-2.000 0.0505 0.00787 0.00144 -0.0579 0.7371 0.2092
-1.750 0.0770 0.00753 0.00133 -0.0579 0.7166 0.3047
-1.500 0.1032 0.00704 0.00123 -0.0579 0.6973 0.4486
-1.250 0.1297 0.00676 0.00118 -0.0578 0.6785 0.5449
-1.000 0.1563 0.00664 0.00119 -0.0575 0.6602 0.6185
-0.750 0.1834 0.00664 0.00119 -0.0572 0.6428 0.6581
-0.500 0.2106 0.00666 0.00119 -0.0570 0.6252 0.6856
-0.250 0.2377 0.00669 0.00119 -0.0567 0.6079 0.7077
0.000 0.2649 0.00674 0.00120 -0.0565 0.5909 0.7275
0.500 0.3192 0.00685 0.00124 -0.0560 0.5587 0.7625
0.750 0.3463 0.00690 0.00128 -0.0557 0.5441 0.7784
1.000 0.3733 0.00695 0.00132 -0.0554 0.5299 0.7948
1.750 0.4529 0.00713 0.00149 -0.0543 0.4873 0.8479
2.250 0.5031 0.00720 0.00164 -0.0528 0.4607 0.8951
2.750 0.5594 0.00728 0.00174 -0.0526 0.4321 0.9838
3.000 0.5880 0.00743 0.00183 -0.0529 0.4156 1.0000
3.250 0.6156 0.00760 0.00195 -0.0529 0.3977 1.0000
3.500 0.6430 0.00777 0.00208 -0.0529 0.3797 1.0000
3.750 0.6703 0.00796 0.00222 -0.0528 0.3622 1.0000
4.000 0.6974 0.00819 0.00237 -0.0528 0.3408 1.0000
4.250 0.7240 0.00847 0.00257 -0.0527 0.3140 1.0000
4.500 0.7506 0.00876 0.00278 -0.0525 0.2896 1.0000
4.750 0.7767 0.00911 0.00302 -0.0524 0.2583 1.0000
5.000 0.8017 0.00962 0.00332 -0.0521 0.2130 1.0000
5.250 0.8253 0.01036 0.00374 -0.0517 0.1522 1.0000
5.500 0.8497 0.01097 0.00414 -0.0514 0.1105 1.0000
5.750 0.8746 0.01149 0.00454 -0.0511 0.0825 1.0000
6.000 0.8992 0.01205 0.00498 -0.0508 0.0569 1.0000
6.250 0.9231 0.01272 0.00552 -0.0504 0.0312 1.0000
6.500 0.9468 0.01341 0.00612 -0.0499 0.0132 1.0000
6.750 0.9711 0.01399 0.00669 -0.0494 0.0080 1.0000
7.000 0.9956 0.01453 0.00727 -0.0490 0.0065 1.0000
7.250 1.0202 0.01503 0.00785 -0.0486 0.0061 1.0000
7.500 1.0444 0.01559 0.00849 -0.0481 0.0056 1.0000
7.750 1.0681 0.01618 0.00920 -0.0476 0.0054 1.0000
8.000 1.0912 0.01686 0.00996 -0.0470 0.0051 1.0000
8.250 1.1133 0.01762 0.01082 -0.0463 0.0048 1.0000
8.500 1.1344 0.01851 0.01180 -0.0455 0.0046 1.0000
8.750 1.1535 0.01960 0.01301 -0.0444 0.0044 1.0000
9.000 1.1701 0.02094 0.01449 -0.0431 0.0042 1.0000
9.250 1.1865 0.02225 0.01594 -0.0417 0.0041 1.0000
9.500 1.2035 0.02340 0.01722 -0.0405 0.0041 1.0000
9.750 1.2191 0.02466 0.01861 -0.0391 0.0040 1.0000
10.000 1.2334 0.02601 0.02010 -0.0376 0.0040 1.0000
10.250 1.2458 0.02749 0.02173 -0.0359 0.0039 1.0000
10.500 1.2565 0.02903 0.02343 -0.0341 0.0039 1.0000
10.750 1.2635 0.03069 0.02524 -0.0319 0.0039 1.0000
11.000 1.2664 0.03241 0.02713 -0.0292 0.0039 1.0000
11.250 1.2673 0.03429 0.02919 -0.0267 0.0039 1.0000
11.500 1.2666 0.03641 0.03148 -0.0246 0.0038 1.0000
11.750 1.2654 0.03867 0.03392 -0.0231 0.0038 1.0000
12.000 1.2625 0.04132 0.03675 -0.0221 0.0038 1.0000
12.250 1.2579 0.04438 0.04003 -0.0217 0.0037 1.0000
12.500 1.2530 0.04775 0.04358 -0.0219 0.0037 1.0000
12.750 1.2450 0.05184 0.04785 -0.0228 0.0037 1.0000
13.000 1.2375 0.05616 0.05235 -0.0244 0.0036 1.0000
13.250 1.2263 0.06137 0.05775 -0.0266 0.0036 1.0000
13.500 1.2147 0.06701 0.06356 -0.0295 0.0036 1.0000
13.750 1.2032 0.07292 0.06965 -0.0328 0.0035 1.0000
14.000 1.1900 0.07951 0.07639 -0.0365 0.0035 1.0000
14.250 1.1707 0.08760 0.08466 -0.0413 0.0036 1.0000
14.500 1.1561 0.09528 0.09249 -0.0459 0.0035 1.0000
14.750 1.1382 0.10414 0.10150 -0.0513 0.0036 1.0000
15.000 1.1188 0.11388 0.11139 -0.0572 0.0036 1.0000
15.250 1.1009 0.12382 0.12147 -0.0632 0.0036 1.0000
15.500 1.0800 0.13508 0.13282 -0.0699 0.0037 1.0000
15.750 1.0589 0.14700 0.14486 -0.0768 0.0038 1.0000
16.000 1.0333 0.16118 0.15914 -0.0847 0.0039 1.0000
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Polar data table (+)
Polar graphs
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