SA7035 (sa7035-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7035 (sa7035-il) Reynolds number: 200,000 Max Cl/Cd: 71.3 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7035-il-200000.txt Download as CSV file: xf-sa7035-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: SA7035
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3953 0.08649 0.08310 -0.0306 1.0000 0.0420
-8.000 -0.3981 0.08293 0.07960 -0.0326 1.0000 0.0433
-7.000 -0.4400 0.06803 0.06472 -0.0440 1.0000 0.0460
-6.750 -0.4456 0.06526 0.06183 -0.0433 1.0000 0.0461
-6.500 -0.4558 0.05909 0.05565 -0.0427 1.0000 0.0470
-6.250 -0.4520 0.05637 0.05305 -0.0405 1.0000 0.0480
-6.000 -0.4481 0.05426 0.05097 -0.0386 1.0000 0.0493
-5.750 -0.4435 0.05178 0.04844 -0.0375 1.0000 0.0511
-5.500 -0.4369 0.04877 0.04531 -0.0371 1.0000 0.0536
-5.250 -0.4189 0.04319 0.03907 -0.0406 0.9981 0.0603
-5.000 -0.3867 0.03974 0.03567 -0.0437 0.9943 0.0635
-4.750 -0.3517 0.03580 0.03118 -0.0476 0.9887 0.0744
-4.500 -0.3101 0.02623 0.02018 -0.0483 0.9856 0.0357
-4.250 -0.2724 0.02313 0.01673 -0.0502 0.9823 0.0321
-4.000 -0.2376 0.02031 0.01343 -0.0512 0.9772 0.0300
-3.750 -0.1987 0.01832 0.01113 -0.0529 0.9733 0.0294
-3.500 -0.1574 0.01684 0.00949 -0.0552 0.9702 0.0304
-3.250 -0.1242 0.01577 0.00833 -0.0561 0.9629 0.0330
-3.000 -0.0835 0.01465 0.00720 -0.0586 0.9586 0.0407
-2.750 -0.0485 0.01301 0.00601 -0.0602 0.9524 0.1355
-2.500 -0.0130 0.01171 0.00575 -0.0625 0.9465 0.3838
-2.250 0.0253 0.01080 0.00570 -0.0646 0.9429 0.6113
-2.000 0.0521 0.01042 0.00561 -0.0637 0.9336 0.7161
-1.750 0.0867 0.01007 0.00547 -0.0640 0.9290 0.8081
-1.500 0.1133 0.00988 0.00538 -0.0625 0.9194 0.8860
-1.250 0.1657 0.00969 0.00512 -0.0664 0.9162 0.9518
-1.000 0.2255 0.00948 0.00477 -0.0724 0.9118 0.9856
-0.750 0.2733 0.00925 0.00440 -0.0764 0.9035 1.0000
-0.500 0.2958 0.00912 0.00416 -0.0751 0.8901 1.0000
-0.250 0.3183 0.00902 0.00396 -0.0738 0.8765 1.0000
0.000 0.3410 0.00894 0.00377 -0.0724 0.8626 1.0000
0.250 0.3642 0.00887 0.00361 -0.0711 0.8481 1.0000
0.500 0.3878 0.00882 0.00346 -0.0699 0.8332 1.0000
0.750 0.4120 0.00879 0.00333 -0.0687 0.8176 1.0000
1.000 0.4365 0.00879 0.00322 -0.0677 0.8011 1.0000
1.250 0.4610 0.00882 0.00317 -0.0667 0.7825 1.0000
1.500 0.4860 0.00887 0.00312 -0.0658 0.7641 1.0000
1.750 0.5114 0.00894 0.00308 -0.0650 0.7459 1.0000
2.000 0.5365 0.00904 0.00310 -0.0643 0.7255 1.0000
2.250 0.5619 0.00917 0.00314 -0.0635 0.7053 1.0000
2.500 0.5871 0.00931 0.00319 -0.0628 0.6842 1.0000
2.750 0.6124 0.00948 0.00325 -0.0621 0.6625 1.0000
3.000 0.6375 0.00966 0.00335 -0.0614 0.6399 1.0000
3.250 0.6627 0.00987 0.00347 -0.0607 0.6180 1.0000
3.500 0.6878 0.01007 0.00361 -0.0601 0.5948 1.0000
3.750 0.7128 0.01031 0.00377 -0.0595 0.5724 1.0000
4.000 0.7377 0.01056 0.00394 -0.0588 0.5493 1.0000
4.250 0.7625 0.01082 0.00416 -0.0582 0.5256 1.0000
4.500 0.7870 0.01111 0.00437 -0.0576 0.5021 1.0000
4.750 0.8113 0.01141 0.00461 -0.0569 0.4779 1.0000
5.000 0.8356 0.01172 0.00487 -0.0563 0.4533 1.0000
5.250 0.8597 0.01206 0.00518 -0.0556 0.4293 1.0000
5.500 0.8835 0.01244 0.00548 -0.0549 0.4057 1.0000
5.750 0.9072 0.01281 0.00583 -0.0542 0.3810 1.0000
6.000 0.9307 0.01321 0.00620 -0.0535 0.3567 1.0000
6.250 0.9536 0.01365 0.00660 -0.0528 0.3315 1.0000
6.500 0.9761 0.01412 0.00701 -0.0520 0.3060 1.0000
6.750 0.9984 0.01462 0.00746 -0.0512 0.2806 1.0000
7.000 1.0205 0.01512 0.00795 -0.0504 0.2554 1.0000
7.250 1.0422 0.01569 0.00848 -0.0496 0.2311 1.0000
7.500 1.0632 0.01632 0.00908 -0.0486 0.2079 1.0000
7.750 1.0838 0.01697 0.00970 -0.0477 0.1838 1.0000
8.000 1.1040 0.01767 0.01038 -0.0467 0.1598 1.0000
8.250 1.1229 0.01849 0.01115 -0.0456 0.1359 1.0000
8.500 1.1403 0.01943 0.01200 -0.0443 0.1121 1.0000
8.750 1.1563 0.02052 0.01299 -0.0429 0.0903 1.0000
9.000 1.1716 0.02165 0.01411 -0.0413 0.0731 1.0000
9.250 1.1851 0.02291 0.01541 -0.0394 0.0598 1.0000
9.500 1.1963 0.02435 0.01687 -0.0373 0.0496 1.0000
9.750 1.2030 0.02612 0.01860 -0.0348 0.0417 1.0000
10.000 1.2141 0.02734 0.02000 -0.0325 0.0362 1.0000
10.250 1.2147 0.02968 0.02232 -0.0294 0.0319 1.0000
10.500 1.2254 0.03090 0.02374 -0.0273 0.0290 1.0000
10.750 1.2327 0.03243 0.02538 -0.0252 0.0262 1.0000
11.000 1.2373 0.03462 0.02762 -0.0231 0.0242 1.0000
11.250 1.2434 0.03794 0.03113 -0.0212 0.0226 1.0000
11.500 1.2481 0.03953 0.03295 -0.0193 0.0211 1.0000
11.750 1.2519 0.04160 0.03524 -0.0176 0.0197 1.0000
12.000 1.2534 0.04376 0.03756 -0.0162 0.0185 1.0000
12.250 1.2535 0.04643 0.04040 -0.0150 0.0178 1.0000
12.500 1.2520 0.04943 0.04356 -0.0140 0.0172 1.0000
12.750 1.2474 0.05313 0.04745 -0.0133 0.0168 1.0000
13.000 1.2386 0.05747 0.05203 -0.0129 0.0165 1.0000
13.250 1.2271 0.06209 0.05690 -0.0132 0.0163 1.0000
13.500 1.2130 0.06718 0.06224 -0.0142 0.0163 1.0000
13.750 1.1953 0.07302 0.06833 -0.0161 0.0162 1.0000
14.000 1.1809 0.07856 0.07408 -0.0184 0.0162 1.0000
14.250 1.1656 0.08458 0.08032 -0.0215 0.0163 1.0000
14.500 1.1499 0.09107 0.08700 -0.0253 0.0164 1.0000
14.750 1.1330 0.09827 0.09440 -0.0297 0.0164 1.0000
15.000 1.1150 0.10632 0.10265 -0.0351 0.0166 1.0000
15.250 1.0885 0.11736 0.11396 -0.0429 0.0172 1.0000
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Polar data table (+)
Polar graphs
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