S7012 8.75% (s7012-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S7012 8.75% (s7012-il) Reynolds number: 200,000 Max Cl/Cd: 67.47 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s7012-il-200000-n5.txt Download as CSV file: xf-s7012-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4720 0.08826 0.08474 -0.0190 1.0000 0.0172
-8.500 -0.4738 0.08365 0.08018 -0.0212 1.0000 0.0159
-8.250 -0.4843 0.07561 0.07221 -0.0262 1.0000 0.0132
-8.000 -0.4900 0.07111 0.06777 -0.0289 1.0000 0.0130
-7.750 -0.4941 0.06550 0.06220 -0.0347 1.0000 0.0128
-7.500 -0.4956 0.05943 0.05606 -0.0395 1.0000 0.0125
-7.250 -0.4954 0.05369 0.05019 -0.0426 1.0000 0.0123
-7.000 -0.4932 0.04800 0.04430 -0.0445 1.0000 0.0119
-6.750 -0.4881 0.04243 0.03844 -0.0455 1.0000 0.0116
-6.500 -0.4792 0.03732 0.03296 -0.0457 1.0000 0.0113
-6.250 -0.4668 0.03262 0.02780 -0.0455 1.0000 0.0111
-6.000 -0.4509 0.02875 0.02343 -0.0449 1.0000 0.0110
-5.750 -0.4324 0.02569 0.01991 -0.0441 1.0000 0.0111
-5.500 -0.4121 0.02350 0.01732 -0.0433 1.0000 0.0116
-5.250 -0.3907 0.02190 0.01538 -0.0424 1.0000 0.0126
-5.000 -0.3600 0.02020 0.01331 -0.0432 0.9970 0.0132
-4.750 -0.3248 0.01841 0.01123 -0.0448 0.9918 0.0133
-4.500 -0.2896 0.01696 0.00958 -0.0464 0.9858 0.0134
-4.250 -0.2557 0.01575 0.00822 -0.0477 0.9789 0.0136
-4.000 -0.2207 0.01452 0.00691 -0.0494 0.9723 0.0141
-3.750 -0.1870 0.01364 0.00595 -0.0508 0.9638 0.0150
-3.500 -0.1509 0.01299 0.00520 -0.0526 0.9562 0.0163
-3.250 -0.1169 0.01246 0.00453 -0.0538 0.9456 0.0188
-3.000 -0.0829 0.01184 0.00392 -0.0551 0.9344 0.0313
-2.750 -0.0496 0.01093 0.00344 -0.0566 0.9219 0.1268
-2.500 -0.0177 0.01001 0.00316 -0.0580 0.9077 0.2844
-2.250 0.0123 0.00915 0.00296 -0.0589 0.8914 0.4670
-2.000 0.0409 0.00872 0.00291 -0.0588 0.8736 0.5896
-1.750 0.0687 0.00857 0.00286 -0.0583 0.8540 0.6619
-1.500 0.0959 0.00851 0.00277 -0.0577 0.8332 0.7040
-1.250 0.1223 0.00848 0.00267 -0.0569 0.8121 0.7350
-1.000 0.1482 0.00848 0.00260 -0.0560 0.7907 0.7617
-0.750 0.1736 0.00849 0.00254 -0.0550 0.7698 0.7853
-0.500 0.1986 0.00851 0.00248 -0.0540 0.7492 0.8072
0.000 0.2478 0.00856 0.00239 -0.0519 0.7101 0.8491
0.250 0.2720 0.00859 0.00236 -0.0507 0.6913 0.8713
0.500 0.2967 0.00863 0.00232 -0.0497 0.6732 0.8946
0.750 0.3232 0.00865 0.00228 -0.0491 0.6551 0.9205
1.000 0.3548 0.00869 0.00224 -0.0496 0.6366 0.9508
1.250 0.3914 0.00875 0.00221 -0.0515 0.6179 0.9942
1.500 0.4189 0.00889 0.00224 -0.0515 0.6011 1.0000
1.750 0.4460 0.00904 0.00230 -0.0514 0.5845 1.0000
2.000 0.4731 0.00920 0.00237 -0.0513 0.5685 1.0000
2.250 0.5002 0.00936 0.00248 -0.0512 0.5525 1.0000
2.500 0.5272 0.00953 0.00258 -0.0511 0.5364 1.0000
2.750 0.5542 0.00971 0.00270 -0.0509 0.5203 1.0000
3.000 0.5811 0.00990 0.00283 -0.0508 0.5046 1.0000
3.250 0.6080 0.01009 0.00301 -0.0506 0.4890 1.0000
3.500 0.6348 0.01029 0.00318 -0.0505 0.4730 1.0000
3.750 0.6617 0.01049 0.00336 -0.0503 0.4557 1.0000
4.000 0.6883 0.01071 0.00356 -0.0501 0.4372 1.0000
4.250 0.7147 0.01095 0.00380 -0.0499 0.4181 1.0000
4.500 0.7412 0.01119 0.00404 -0.0497 0.3984 1.0000
4.750 0.7673 0.01146 0.00430 -0.0494 0.3764 1.0000
5.000 0.7930 0.01177 0.00457 -0.0491 0.3499 1.0000
5.250 0.8184 0.01213 0.00490 -0.0488 0.3218 1.0000
5.500 0.8435 0.01253 0.00526 -0.0484 0.2933 1.0000
5.750 0.8681 0.01300 0.00565 -0.0480 0.2617 1.0000
6.000 0.8917 0.01360 0.00611 -0.0476 0.2214 1.0000
6.250 0.9135 0.01447 0.00668 -0.0470 0.1643 1.0000
6.500 0.9350 0.01540 0.00736 -0.0465 0.1141 1.0000
6.750 0.9562 0.01639 0.00810 -0.0458 0.0713 1.0000
7.000 0.9774 0.01736 0.00892 -0.0452 0.0416 1.0000
7.250 0.9978 0.01847 0.00993 -0.0443 0.0215 1.0000
7.500 1.0187 0.01954 0.01106 -0.0434 0.0152 1.0000
7.750 1.0396 0.02053 0.01223 -0.0425 0.0133 1.0000
8.000 1.0601 0.02153 0.01339 -0.0415 0.0121 1.0000
8.250 1.0798 0.02255 0.01454 -0.0406 0.0109 1.0000
8.500 1.0963 0.02392 0.01601 -0.0394 0.0099 1.0000
8.750 1.1144 0.02502 0.01728 -0.0383 0.0092 1.0000
9.000 1.1301 0.02638 0.01880 -0.0370 0.0088 1.0000
9.250 1.1446 0.02784 0.02042 -0.0355 0.0085 1.0000
9.500 1.1578 0.02941 0.02215 -0.0339 0.0082 1.0000
9.750 1.1699 0.03107 0.02401 -0.0323 0.0080 1.0000
10.000 1.1806 0.03284 0.02594 -0.0307 0.0078 1.0000
10.250 1.1891 0.03470 0.02797 -0.0288 0.0076 1.0000
10.500 1.1948 0.03661 0.03007 -0.0267 0.0075 1.0000
10.750 1.1983 0.03872 0.03236 -0.0246 0.0074 1.0000
11.000 1.1996 0.04103 0.03488 -0.0227 0.0073 1.0000
11.250 1.1990 0.04359 0.03764 -0.0212 0.0073 1.0000
11.500 1.1963 0.04646 0.04074 -0.0201 0.0072 1.0000
11.750 1.1916 0.04971 0.04422 -0.0196 0.0072 1.0000
12.000 1.1849 0.05338 0.04812 -0.0197 0.0072 1.0000
12.250 1.1762 0.05755 0.05251 -0.0205 0.0071 1.0000
12.500 1.1657 0.06229 0.05749 -0.0221 0.0071 1.0000
12.750 1.1534 0.06762 0.06305 -0.0244 0.0072 1.0000
13.000 1.1393 0.07366 0.06932 -0.0276 0.0072 1.0000
13.250 1.1233 0.08045 0.07633 -0.0315 0.0072 1.0000
13.500 1.1059 0.08799 0.08408 -0.0361 0.0073 1.0000
13.750 1.0860 0.09658 0.09288 -0.0415 0.0073 1.0000
14.000 1.0648 0.10622 0.10271 -0.0477 0.0074 1.0000
14.250 1.0414 0.11736 0.11402 -0.0549 0.0075 1.0000
14.500 1.0107 0.13191 0.12875 -0.0639 0.0078 1.0000
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Polar data table (+)
Polar graphs
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