SD7062 (14%) (sd7062-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7062 (14%) (sd7062-il) Reynolds number: 200,000 Max Cl/Cd: 70.27 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7062-il-200000-n5.txt Download as CSV file: xf-sd7062-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3202 0.08750 0.08385 -0.0473 1.0000 0.0237
-9.750 -0.3292 0.08267 0.07908 -0.0489 1.0000 0.0235
-9.500 -0.4546 0.04741 0.04346 -0.0816 0.9724 0.0216
-9.250 -0.4679 0.03865 0.03396 -0.0911 0.9447 0.0214
-9.000 -0.4560 0.03495 0.02985 -0.0935 0.9289 0.0216
-8.750 -0.4401 0.03221 0.02674 -0.0946 0.9146 0.0217
-8.500 -0.4223 0.02992 0.02410 -0.0949 0.9016 0.0219
-8.250 -0.4027 0.02800 0.02186 -0.0949 0.8895 0.0222
-8.000 -0.3832 0.02636 0.01994 -0.0944 0.8768 0.0225
-7.750 -0.3622 0.02489 0.01818 -0.0939 0.8655 0.0228
-7.500 -0.3401 0.02358 0.01661 -0.0933 0.8548 0.0232
-7.250 -0.3175 0.02248 0.01525 -0.0927 0.8437 0.0238
-7.000 -0.2938 0.02149 0.01403 -0.0921 0.8339 0.0244
-6.750 -0.2702 0.02069 0.01319 -0.0916 0.8233 0.0250
-6.500 -0.2457 0.01997 0.01237 -0.0910 0.8137 0.0256
-6.250 -0.2211 0.01923 0.01152 -0.0905 0.8037 0.0262
-6.000 -0.1963 0.01852 0.01069 -0.0899 0.7943 0.0268
-5.750 -0.1713 0.01786 0.00992 -0.0894 0.7847 0.0274
-5.500 -0.1459 0.01727 0.00921 -0.0888 0.7753 0.0281
-5.250 -0.1208 0.01669 0.00858 -0.0884 0.7660 0.0289
-5.000 -0.0951 0.01620 0.00804 -0.0880 0.7566 0.0298
-4.750 -0.0691 0.01577 0.00753 -0.0876 0.7475 0.0312
-4.500 -0.0428 0.01537 0.00706 -0.0872 0.7381 0.0332
-4.250 -0.0164 0.01501 0.00663 -0.0869 0.7292 0.0354
-4.000 0.0103 0.01465 0.00621 -0.0865 0.7196 0.0381
-3.750 0.0370 0.01430 0.00580 -0.0862 0.7109 0.0420
-3.500 0.0639 0.01396 0.00544 -0.0859 0.7011 0.0490
-3.250 0.0907 0.01361 0.00510 -0.0856 0.6925 0.0650
-3.000 0.1174 0.01324 0.00485 -0.0854 0.6825 0.0933
-2.750 0.1443 0.01295 0.00462 -0.0852 0.6737 0.1272
-2.500 0.1711 0.01264 0.00444 -0.0851 0.6637 0.1693
-2.250 0.1975 0.01227 0.00431 -0.0849 0.6548 0.2416
-2.000 0.2237 0.01191 0.00423 -0.0847 0.6449 0.3224
-1.750 0.2505 0.01171 0.00416 -0.0844 0.6355 0.3807
-1.500 0.2774 0.01158 0.00411 -0.0841 0.6259 0.4288
-1.250 0.3043 0.01147 0.00408 -0.0837 0.6161 0.4754
-1.000 0.3310 0.01140 0.00405 -0.0833 0.6068 0.5178
-0.750 0.3578 0.01134 0.00406 -0.0829 0.5966 0.5561
-0.500 0.3844 0.01131 0.00405 -0.0823 0.5873 0.5924
-0.250 0.4108 0.01128 0.00407 -0.0818 0.5771 0.6280
0.000 0.4371 0.01127 0.00408 -0.0812 0.5676 0.6618
0.250 0.4631 0.01126 0.00411 -0.0805 0.5577 0.6938
0.500 0.4888 0.01126 0.00415 -0.0798 0.5481 0.7257
0.750 0.5138 0.01128 0.00418 -0.0789 0.5385 0.7584
1.000 0.5386 0.01129 0.00423 -0.0779 0.5287 0.7928
1.250 0.5624 0.01132 0.00426 -0.0767 0.5194 0.8299
1.500 0.5870 0.01133 0.00431 -0.0756 0.5095 0.8714
1.750 0.6156 0.01136 0.00433 -0.0754 0.4998 0.9190
2.000 0.6550 0.01143 0.00433 -0.0776 0.4887 0.9801
2.250 0.6839 0.01158 0.00439 -0.0779 0.4786 1.0000
2.750 0.7366 0.01194 0.00457 -0.0773 0.4590 1.0000
3.000 0.7627 0.01214 0.00468 -0.0770 0.4497 1.0000
3.250 0.7888 0.01234 0.00481 -0.0767 0.4398 1.0000
3.500 0.8149 0.01255 0.00495 -0.0764 0.4305 1.0000
3.750 0.8406 0.01277 0.00511 -0.0760 0.4209 1.0000
4.000 0.8665 0.01299 0.00528 -0.0757 0.4116 1.0000
4.250 0.8916 0.01325 0.00545 -0.0752 0.4025 1.0000
4.500 0.9174 0.01347 0.00566 -0.0749 0.3931 1.0000
4.750 0.9422 0.01375 0.00586 -0.0744 0.3844 1.0000
5.000 0.9675 0.01400 0.00609 -0.0740 0.3751 1.0000
5.250 0.9920 0.01429 0.00633 -0.0735 0.3664 1.0000
5.500 1.0167 0.01456 0.00658 -0.0730 0.3574 1.0000
5.750 1.0408 0.01487 0.00685 -0.0725 0.3489 1.0000
6.000 1.0648 0.01517 0.00713 -0.0719 0.3400 1.0000
6.250 1.0885 0.01549 0.00743 -0.0713 0.3319 1.0000
6.500 1.1117 0.01582 0.00774 -0.0706 0.3232 1.0000
6.750 1.1347 0.01617 0.00807 -0.0699 0.3152 1.0000
7.000 1.1571 0.01653 0.00842 -0.0692 0.3069 1.0000
7.250 1.1793 0.01690 0.00878 -0.0684 0.2991 1.0000
7.500 1.2008 0.01729 0.00916 -0.0675 0.2910 1.0000
7.750 1.2220 0.01769 0.00957 -0.0666 0.2836 1.0000
8.000 1.2425 0.01811 0.00999 -0.0656 0.2758 1.0000
8.250 1.2622 0.01856 0.01043 -0.0645 0.2689 1.0000
8.500 1.2817 0.01900 0.01090 -0.0634 0.2614 1.0000
8.750 1.2989 0.01951 0.01139 -0.0619 0.2548 1.0000
9.000 1.3164 0.01995 0.01188 -0.0605 0.2478 1.0000
9.250 1.3304 0.02052 0.01244 -0.0586 0.2415 1.0000
9.500 1.3466 0.02104 0.01301 -0.0571 0.2350 1.0000
9.750 1.3605 0.02165 0.01364 -0.0553 0.2287 1.0000
10.000 1.3741 0.02232 0.01432 -0.0536 0.2230 1.0000
10.250 1.3882 0.02298 0.01504 -0.0521 0.2165 1.0000
10.500 1.3991 0.02382 0.01587 -0.0503 0.2111 1.0000
10.750 1.4130 0.02456 0.01669 -0.0490 0.2054 1.0000
11.000 1.4243 0.02545 0.01761 -0.0474 0.1997 1.0000
11.250 1.4339 0.02648 0.01866 -0.0459 0.1946 1.0000
11.500 1.4459 0.02742 0.01968 -0.0446 0.1890 1.0000
11.750 1.4545 0.02860 0.02089 -0.0432 0.1837 1.0000
12.000 1.4635 0.02981 0.02215 -0.0420 0.1789 1.0000
12.250 1.4733 0.03103 0.02345 -0.0409 0.1737 1.0000
12.500 1.4794 0.03253 0.02498 -0.0398 0.1689 1.0000
12.750 1.4872 0.03399 0.02650 -0.0388 0.1644 1.0000
13.000 1.4946 0.03552 0.02812 -0.0379 0.1594 1.0000
13.250 1.4989 0.03735 0.02998 -0.0371 0.1552 1.0000
13.500 1.5044 0.03915 0.03186 -0.0363 0.1511 1.0000
13.750 1.5100 0.04100 0.03381 -0.0358 0.1466 1.0000
14.000 1.5122 0.04321 0.03606 -0.0353 0.1424 1.0000
14.250 1.5145 0.04548 0.03838 -0.0349 0.1388 1.0000
14.500 1.5188 0.04764 0.04067 -0.0346 0.1347 1.0000
14.750 1.5198 0.05020 0.04330 -0.0345 0.1308 1.0000
15.000 1.5179 0.05312 0.04625 -0.0345 0.1275 1.0000
15.250 1.5211 0.05563 0.04889 -0.0346 0.1239 1.0000
15.500 1.5215 0.05853 0.05189 -0.0349 0.1202 1.0000
15.750 1.5193 0.06179 0.05520 -0.0353 0.1171 1.0000
16.000 1.5171 0.06512 0.05860 -0.0359 0.1142 1.0000
16.250 1.5174 0.06828 0.06190 -0.0365 0.1108 1.0000
16.500 1.5148 0.07188 0.06560 -0.0374 0.1076 1.0000
16.750 1.5100 0.07583 0.06960 -0.0384 0.1048 1.0000
17.000 1.5065 0.07967 0.07353 -0.0395 0.1022 1.0000
17.250 1.5041 0.08350 0.07750 -0.0407 0.0992 1.0000
17.500 1.4993 0.08772 0.08182 -0.0421 0.0963 1.0000
17.750 1.4929 0.09221 0.08637 -0.0438 0.0938 1.0000
18.000 1.4880 0.09653 0.09077 -0.0454 0.0914 1.0000
18.250 1.4839 0.10087 0.09526 -0.0471 0.0888 1.0000
18.500 1.4778 0.10558 0.10008 -0.0490 0.0862 1.0000
18.750 1.4710 0.11038 0.10495 -0.0511 0.0839 1.0000
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