SD7084 (9.6%) (sd7084-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7084 (9.6%) (sd7084-il) Reynolds number: 200,000 Max Cl/Cd: 65.69 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7084-il-200000.txt Download as CSV file: xf-sd7084-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: SD7084 (9.6%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4351 0.10218 0.09866 -0.0304 1.0000 0.0469
-9.500 -0.4378 0.09825 0.09477 -0.0339 1.0000 0.0471
-9.250 -0.4410 0.09402 0.09059 -0.0374 1.0000 0.0472
-9.000 -0.4415 0.08818 0.08479 -0.0361 1.0000 0.0484
-8.750 -0.4310 0.08589 0.08251 -0.0338 1.0000 0.0497
-8.500 -0.4275 0.08307 0.07972 -0.0338 1.0000 0.0509
-8.250 -0.4286 0.07996 0.07666 -0.0345 1.0000 0.0523
-8.000 -0.4363 0.07669 0.07346 -0.0354 1.0000 0.0538
-7.750 -0.4514 0.07353 0.07038 -0.0360 1.0000 0.0538
-7.500 -0.4639 0.06998 0.06686 -0.0369 1.0000 0.0546
-7.250 -0.4770 0.06641 0.06329 -0.0370 1.0000 0.0558
-7.000 -0.4887 0.06263 0.05943 -0.0370 1.0000 0.0574
-6.500 -0.5131 0.05357 0.04980 -0.0358 1.0000 0.0611
-6.250 -0.5024 0.05180 0.04827 -0.0337 1.0000 0.0634
-6.000 -0.4959 0.04986 0.04628 -0.0319 1.0000 0.0662
-5.000 -0.4356 0.03004 0.02436 -0.0301 0.9954 0.0458
-4.750 -0.4045 0.02568 0.01948 -0.0314 0.9917 0.0423
-4.500 -0.3692 0.02347 0.01683 -0.0329 0.9872 0.0435
-4.250 -0.3313 0.02115 0.01407 -0.0346 0.9839 0.0429
-4.000 -0.2966 0.01953 0.01217 -0.0357 0.9788 0.0432
-3.750 -0.2589 0.01828 0.01071 -0.0374 0.9742 0.0448
-3.500 -0.2174 0.01731 0.00960 -0.0399 0.9707 0.0481
-3.250 -0.1867 0.01616 0.00850 -0.0406 0.9637 0.0521
-3.000 -0.1468 0.01541 0.00771 -0.0429 0.9591 0.0581
-2.750 -0.1126 0.01455 0.00688 -0.0441 0.9527 0.0747
-2.500 -0.0797 0.01301 0.00624 -0.0457 0.9467 0.2465
-2.250 -0.0436 0.01192 0.00609 -0.0478 0.9424 0.4840
-2.000 -0.0209 0.01113 0.00611 -0.0462 0.9334 0.6854
-1.750 0.0192 0.01065 0.00612 -0.0472 0.9303 0.8498
-1.500 0.0871 0.01054 0.00600 -0.0543 0.9301 0.9332
-1.250 0.1594 0.01047 0.00579 -0.0625 0.9299 0.9718
-1.000 0.2253 0.01028 0.00545 -0.0699 0.9269 0.9906
-0.750 0.2760 0.00999 0.00506 -0.0744 0.9190 1.0000
-0.500 0.3000 0.00978 0.00476 -0.0735 0.9059 1.0000
-0.250 0.3220 0.00958 0.00449 -0.0720 0.8921 1.0000
0.000 0.3430 0.00940 0.00423 -0.0703 0.8776 1.0000
0.250 0.3639 0.00925 0.00400 -0.0685 0.8626 1.0000
0.500 0.3852 0.00911 0.00379 -0.0667 0.8468 1.0000
0.750 0.4073 0.00900 0.00360 -0.0651 0.8303 1.0000
1.000 0.4293 0.00893 0.00345 -0.0636 0.8114 1.0000
1.250 0.4519 0.00889 0.00332 -0.0621 0.7911 1.0000
1.500 0.4751 0.00888 0.00320 -0.0608 0.7701 1.0000
1.750 0.4983 0.00892 0.00314 -0.0595 0.7469 1.0000
2.000 0.5216 0.00900 0.00311 -0.0582 0.7225 1.0000
2.250 0.5449 0.00913 0.00310 -0.0570 0.6976 1.0000
2.500 0.5680 0.00929 0.00313 -0.0559 0.6717 1.0000
2.750 0.5910 0.00948 0.00321 -0.0547 0.6451 1.0000
3.000 0.6139 0.00970 0.00331 -0.0535 0.6181 1.0000
3.250 0.6368 0.00994 0.00343 -0.0524 0.5911 1.0000
3.500 0.6596 0.01020 0.00357 -0.0513 0.5642 1.0000
3.750 0.6823 0.01048 0.00376 -0.0502 0.5376 1.0000
4.000 0.7050 0.01078 0.00394 -0.0492 0.5115 1.0000
4.250 0.7276 0.01111 0.00415 -0.0481 0.4861 1.0000
4.500 0.7504 0.01143 0.00439 -0.0472 0.4608 1.0000
4.750 0.7732 0.01177 0.00467 -0.0462 0.4370 1.0000
5.000 0.7957 0.01215 0.00495 -0.0452 0.4149 1.0000
5.250 0.8186 0.01250 0.00527 -0.0443 0.3930 1.0000
5.500 0.8413 0.01290 0.00559 -0.0434 0.3733 1.0000
5.750 0.8641 0.01330 0.00596 -0.0426 0.3544 1.0000
6.000 0.8870 0.01369 0.00634 -0.0417 0.3363 1.0000
6.250 0.9096 0.01411 0.00673 -0.0409 0.3191 1.0000
6.500 0.9321 0.01454 0.00714 -0.0400 0.3029 1.0000
6.750 0.9543 0.01499 0.00757 -0.0391 0.2872 1.0000
7.000 0.9763 0.01545 0.00804 -0.0382 0.2716 1.0000
7.250 0.9983 0.01587 0.00850 -0.0373 0.2557 1.0000
7.500 1.0199 0.01630 0.00898 -0.0363 0.2395 1.0000
7.750 1.0411 0.01672 0.00945 -0.0353 0.2228 1.0000
8.000 1.0611 0.01714 0.00986 -0.0342 0.2035 1.0000
8.250 1.0812 0.01753 0.01030 -0.0331 0.1794 1.0000
8.500 1.1006 0.01805 0.01079 -0.0320 0.1555 1.0000
8.750 1.1190 0.01869 0.01138 -0.0308 0.1291 1.0000
9.000 1.1338 0.01972 0.01223 -0.0291 0.0904 1.0000
9.250 1.1354 0.02202 0.01412 -0.0256 0.0430 1.0000
9.500 1.1411 0.02372 0.01582 -0.0226 0.0322 1.0000
9.750 1.1420 0.02546 0.01760 -0.0190 0.0273 1.0000
10.000 1.1482 0.02673 0.01900 -0.0160 0.0254 1.0000
10.250 1.1530 0.02814 0.02055 -0.0131 0.0238 1.0000
10.500 1.1573 0.02968 0.02218 -0.0104 0.0224 1.0000
10.750 1.1609 0.03139 0.02398 -0.0080 0.0215 1.0000
11.000 1.1632 0.03349 0.02615 -0.0056 0.0207 1.0000
11.250 1.1675 0.03608 0.02882 -0.0036 0.0200 1.0000
11.500 1.1766 0.03889 0.03176 -0.0020 0.0196 1.0000
11.750 1.1839 0.04110 0.03417 -0.0004 0.0193 1.0000
12.000 1.1887 0.04341 0.03670 0.0011 0.0191 1.0000
12.250 1.1903 0.04583 0.03934 0.0026 0.0186 1.0000
12.500 1.1894 0.04840 0.04214 0.0037 0.0182 1.0000
12.750 1.1865 0.05162 0.04560 0.0047 0.0182 1.0000
13.000 1.1802 0.05497 0.04918 0.0052 0.0179 1.0000
13.250 1.1733 0.05829 0.05270 0.0052 0.0173 1.0000
13.500 1.1633 0.06242 0.05709 0.0046 0.0172 1.0000
13.750 1.1506 0.06719 0.06209 0.0034 0.0172 1.0000
14.000 1.1361 0.07252 0.06765 0.0014 0.0174 1.0000
14.250 1.1193 0.07850 0.07385 -0.0013 0.0175 1.0000
14.500 1.1011 0.08511 0.08067 -0.0048 0.0176 1.0000
14.750 1.0814 0.09250 0.08823 -0.0092 0.0176 1.0000
15.000 1.0615 0.10043 0.09634 -0.0140 0.0180 1.0000
15.250 1.0412 0.10902 0.10510 -0.0195 0.0181 1.0000
15.500 1.0187 0.11870 0.11494 -0.0258 0.0183 1.0000
15.750 0.9945 0.12938 0.12573 -0.0324 0.0189 1.0000
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Polar data table (+)
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