SD7062 (14%) (sd7062-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7062 (14%) (sd7062-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.55 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7062-il-1000000.txt Download as CSV file: xf-sd7062-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: SD7062 (14%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4635 0.06916 0.06731 -0.0574 1.0000 0.0173
-11.000 -0.5283 0.05315 0.05120 -0.0691 1.0000 0.0166
-10.750 -0.5740 0.04265 0.04049 -0.0796 0.9995 0.0164
-10.500 -0.5872 0.03163 0.02880 -0.0962 0.9691 0.0159
-10.250 -0.5821 0.02742 0.02413 -0.0980 0.9422 0.0158
-10.000 -0.5748 0.02507 0.02145 -0.0968 0.9172 0.0157
-9.750 -0.5615 0.02352 0.01964 -0.0956 0.8973 0.0158
-9.500 -0.5462 0.02197 0.01784 -0.0945 0.8807 0.0159
-9.250 -0.5279 0.02069 0.01633 -0.0935 0.8665 0.0160
-8.750 -0.4865 0.01849 0.01375 -0.0920 0.8415 0.0162
-8.500 -0.4638 0.01760 0.01270 -0.0914 0.8309 0.0163
-8.250 -0.4403 0.01680 0.01175 -0.0909 0.8200 0.0165
-8.000 -0.4156 0.01616 0.01099 -0.0904 0.8101 0.0167
-7.500 -0.3646 0.01516 0.00976 -0.0896 0.7907 0.0172
-7.250 -0.3387 0.01472 0.00919 -0.0892 0.7814 0.0173
-7.000 -0.3150 0.01357 0.00796 -0.0887 0.7724 0.0176
-6.750 -0.2902 0.01286 0.00717 -0.0883 0.7634 0.0179
-6.500 -0.2638 0.01236 0.00664 -0.0881 0.7544 0.0182
-6.250 -0.2373 0.01198 0.00619 -0.0877 0.7456 0.0185
-6.000 -0.2102 0.01160 0.00578 -0.0875 0.7368 0.0188
-5.750 -0.1833 0.01128 0.00538 -0.0873 0.7280 0.0192
-5.500 -0.1558 0.01094 0.00500 -0.0871 0.7193 0.0196
-5.250 -0.1286 0.01067 0.00465 -0.0869 0.7103 0.0199
-5.000 -0.1007 0.01039 0.00433 -0.0867 0.7017 0.0203
-4.750 -0.0731 0.01019 0.00406 -0.0865 0.6926 0.0206
-4.500 -0.0457 0.00975 0.00358 -0.0864 0.6838 0.0214
-4.250 -0.0180 0.00954 0.00331 -0.0862 0.6747 0.0222
-4.000 0.0104 0.00935 0.00310 -0.0861 0.6657 0.0232
-3.750 0.0384 0.00922 0.00290 -0.0860 0.6567 0.0241
-3.500 0.0667 0.00899 0.00265 -0.0859 0.6474 0.0254
-3.250 0.0948 0.00885 0.00247 -0.0858 0.6383 0.0272
-3.000 0.1232 0.00869 0.00229 -0.0857 0.6287 0.0303
-2.750 0.1512 0.00848 0.00211 -0.0856 0.6197 0.0450
-2.500 0.1790 0.00818 0.00196 -0.0856 0.6100 0.0860
-2.250 0.2070 0.00796 0.00185 -0.0856 0.6010 0.1252
-2.000 0.2349 0.00776 0.00177 -0.0855 0.5911 0.1689
-1.750 0.2631 0.00757 0.00170 -0.0855 0.5820 0.2144
-1.250 0.3192 0.00724 0.00162 -0.0855 0.5628 0.3196
-1.000 0.3470 0.00712 0.00161 -0.0855 0.5532 0.3745
-0.750 0.3753 0.00700 0.00161 -0.0855 0.5436 0.4246
-0.500 0.4033 0.00694 0.00162 -0.0854 0.5340 0.4697
-0.250 0.4315 0.00689 0.00164 -0.0854 0.5240 0.5098
0.000 0.4596 0.00685 0.00167 -0.0853 0.5147 0.5530
0.250 0.4875 0.00685 0.00171 -0.0852 0.5044 0.5864
0.500 0.5158 0.00684 0.00174 -0.0851 0.4950 0.6150
0.750 0.5436 0.00688 0.00179 -0.0850 0.4850 0.6448
1.000 0.5716 0.00688 0.00184 -0.0849 0.4755 0.6766
1.250 0.5992 0.00691 0.00191 -0.0847 0.4659 0.7061
1.500 0.6269 0.00694 0.00197 -0.0845 0.4560 0.7353
1.750 0.6543 0.00697 0.00204 -0.0842 0.4469 0.7662
2.000 0.6810 0.00701 0.00212 -0.0839 0.4369 0.7985
2.250 0.7076 0.00702 0.00221 -0.0834 0.4280 0.8340
2.500 0.7325 0.00707 0.00230 -0.0826 0.4185 0.8735
2.750 0.7558 0.00705 0.00237 -0.0813 0.4099 0.9212
3.000 0.7895 0.00711 0.00243 -0.0824 0.4000 0.9839
3.250 0.8199 0.00724 0.00251 -0.0829 0.3905 1.0000
3.500 0.8474 0.00739 0.00260 -0.0828 0.3816 1.0000
3.750 0.8747 0.00755 0.00270 -0.0827 0.3721 1.0000
4.000 0.9021 0.00770 0.00281 -0.0826 0.3635 1.0000
4.250 0.9290 0.00788 0.00293 -0.0824 0.3539 1.0000
4.500 0.9564 0.00803 0.00305 -0.0823 0.3459 1.0000
5.000 1.0101 0.00839 0.00331 -0.0819 0.3280 1.0000
5.250 1.0364 0.00861 0.00347 -0.0817 0.3190 1.0000
5.500 1.0633 0.00878 0.00361 -0.0815 0.3107 1.0000
5.750 1.0893 0.00900 0.00379 -0.0812 0.3023 1.0000
6.000 1.1158 0.00918 0.00394 -0.0810 0.2943 1.0000
6.250 1.1415 0.00942 0.00413 -0.0806 0.2860 1.0000
6.500 1.1676 0.00961 0.00431 -0.0804 0.2786 1.0000
6.750 1.1928 0.00987 0.00452 -0.0800 0.2705 1.0000
7.000 1.2185 0.01008 0.00471 -0.0797 0.2629 1.0000
7.250 1.2432 0.01035 0.00494 -0.0792 0.2552 1.0000
7.500 1.2686 0.01056 0.00514 -0.0789 0.2484 1.0000
7.750 1.2925 0.01087 0.00540 -0.0783 0.2402 1.0000
8.000 1.3175 0.01109 0.00562 -0.0779 0.2341 1.0000
8.250 1.3407 0.01141 0.00590 -0.0772 0.2263 1.0000
8.500 1.3650 0.01165 0.00614 -0.0767 0.2200 1.0000
8.750 1.3876 0.01198 0.00643 -0.0760 0.2128 1.0000
9.000 1.4107 0.01226 0.00671 -0.0753 0.2067 1.0000
9.250 1.4327 0.01259 0.00702 -0.0745 0.1999 1.0000
9.500 1.4543 0.01293 0.00734 -0.0736 0.1936 1.0000
9.750 1.4757 0.01325 0.00766 -0.0726 0.1876 1.0000
10.000 1.4947 0.01367 0.00804 -0.0714 0.1809 1.0000
10.250 1.5148 0.01397 0.00836 -0.0702 0.1757 1.0000
10.500 1.5302 0.01439 0.00876 -0.0683 0.1697 1.0000
10.750 1.5464 0.01477 0.00915 -0.0665 0.1646 1.0000
11.000 1.5618 0.01520 0.00958 -0.0647 0.1591 1.0000
11.250 1.5747 0.01576 0.01012 -0.0626 0.1531 1.0000
11.500 1.5909 0.01619 0.01057 -0.0611 0.1488 1.0000
11.750 1.6037 0.01678 0.01116 -0.0591 0.1436 1.0000
12.000 1.6166 0.01741 0.01180 -0.0573 0.1387 1.0000
12.250 1.6303 0.01802 0.01243 -0.0557 0.1344 1.0000
12.500 1.6405 0.01884 0.01324 -0.0538 0.1293 1.0000
12.750 1.6528 0.01959 0.01401 -0.0522 0.1252 1.0000
13.000 1.6643 0.02042 0.01486 -0.0507 0.1211 1.0000
13.250 1.6723 0.02150 0.01594 -0.0489 0.1164 1.0000
13.500 1.6834 0.02243 0.01692 -0.0476 0.1130 1.0000
13.750 1.6931 0.02350 0.01801 -0.0462 0.1093 1.0000
14.000 1.6995 0.02485 0.01937 -0.0447 0.1052 1.0000
14.250 1.7081 0.02611 0.02067 -0.0435 0.1021 1.0000
14.500 1.7168 0.02740 0.02200 -0.0425 0.0991 1.0000
14.750 1.7221 0.02900 0.02363 -0.0413 0.0958 1.0000
15.000 1.7252 0.03085 0.02551 -0.0402 0.0922 1.0000
15.250 1.7331 0.03236 0.02707 -0.0395 0.0898 1.0000
15.500 1.7375 0.03422 0.02898 -0.0387 0.0870 1.0000
15.750 1.7377 0.03652 0.03130 -0.0379 0.0836 1.0000
16.000 1.7405 0.03867 0.03352 -0.0374 0.0813 1.0000
16.250 1.7442 0.04080 0.03571 -0.0370 0.0787 1.0000
16.500 1.7437 0.04343 0.03838 -0.0367 0.0758 1.0000
16.750 1.7391 0.04661 0.04159 -0.0366 0.0727 1.0000
17.000 1.7417 0.04910 0.04415 -0.0366 0.0709 1.0000
17.250 1.7406 0.05206 0.04718 -0.0367 0.0686 1.0000
17.500 1.7358 0.05555 0.05071 -0.0371 0.0662 1.0000
17.750 1.7286 0.05946 0.05469 -0.0376 0.0637 1.0000
18.000 1.7279 0.06265 0.05797 -0.0382 0.0622 1.0000
18.250 1.7232 0.06641 0.06180 -0.0390 0.0604 1.0000
18.500 1.7150 0.07075 0.06620 -0.0401 0.0583 1.0000
18.750 1.7040 0.07560 0.07111 -0.0414 0.0564 1.0000
19.000 1.6984 0.07976 0.07537 -0.0427 0.0548 1.0000
19.250 1.6913 0.08423 0.07992 -0.0441 0.0532 1.0000
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Polar data table (+)
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