SA7036 (sa7036-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7036 (sa7036-il) Reynolds number: 200,000 Max Cl/Cd: 73 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7036-il-200000.txt Download as CSV file: xf-sa7036-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: SA7036
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3915 0.09435 0.09091 -0.0360 1.0000 0.0401
-8.500 -0.3942 0.09088 0.08751 -0.0386 1.0000 0.0402
-8.250 -0.3984 0.08748 0.08417 -0.0402 1.0000 0.0403
-8.000 -0.3894 0.08307 0.07978 -0.0348 1.0000 0.0427
-7.750 -0.3925 0.08040 0.07717 -0.0346 1.0000 0.0432
-7.500 -0.3963 0.07841 0.07524 -0.0331 1.0000 0.0447
-7.250 -0.4072 0.07608 0.07300 -0.0322 1.0000 0.0458
-7.000 -0.4168 0.07340 0.07037 -0.0326 1.0000 0.0479
-6.750 -0.4260 0.07019 0.06719 -0.0334 1.0000 0.0483
-6.500 -0.4333 0.06623 0.06321 -0.0358 1.0000 0.0502
-6.250 -0.4382 0.06170 0.05835 -0.0405 1.0000 0.0522
-6.000 -0.4398 0.05801 0.05438 -0.0409 1.0000 0.0528
-5.750 -0.4379 0.05312 0.04975 -0.0392 1.0000 0.0546
-5.500 -0.4233 0.05067 0.04732 -0.0393 0.9987 0.0566
-5.000 -0.3041 0.02569 0.02201 -0.0555 0.9773 0.0720
-4.750 -0.2718 0.02112 0.01700 -0.0597 0.9726 0.0824
-4.500 -0.2804 0.02794 0.02247 -0.0563 0.9799 0.0440
-4.250 -0.2428 0.02235 0.01577 -0.0568 0.9760 0.0312
-4.000 -0.2038 0.02022 0.01331 -0.0589 0.9724 0.0323
-3.750 -0.1665 0.01903 0.01195 -0.0608 0.9677 0.0355
-3.500 -0.1306 0.01751 0.01023 -0.0620 0.9622 0.0364
-3.250 -0.0899 0.01629 0.00889 -0.0642 0.9585 0.0389
-3.000 -0.0545 0.01515 0.00775 -0.0657 0.9527 0.0456
-2.750 -0.0163 0.01421 0.00679 -0.0676 0.9468 0.0573
-2.500 0.0249 0.01246 0.00594 -0.0708 0.9435 0.2497
-2.250 0.0554 0.01162 0.00577 -0.0717 0.9354 0.4317
-2.000 0.0879 0.01074 0.00573 -0.0722 0.9303 0.6574
-1.750 0.1134 0.01035 0.00566 -0.0708 0.9217 0.7689
-1.500 0.1443 0.01001 0.00551 -0.0699 0.9159 0.8698
-1.250 0.1954 0.00978 0.00524 -0.0736 0.9117 0.9567
-1.000 0.2618 0.00951 0.00482 -0.0811 0.9077 0.9996
-0.750 0.2889 0.00935 0.00453 -0.0807 0.8969 1.0000
-0.500 0.3146 0.00920 0.00424 -0.0799 0.8859 1.0000
-0.250 0.3374 0.00911 0.00405 -0.0786 0.8726 1.0000
0.000 0.3610 0.00904 0.00387 -0.0773 0.8592 1.0000
0.250 0.3851 0.00897 0.00370 -0.0762 0.8453 1.0000
0.500 0.4097 0.00893 0.00355 -0.0751 0.8310 1.0000
0.750 0.4347 0.00890 0.00342 -0.0742 0.8161 1.0000
1.000 0.4600 0.00889 0.00332 -0.0733 0.8004 1.0000
1.250 0.4850 0.00892 0.00327 -0.0724 0.7825 1.0000
1.500 0.5105 0.00896 0.00321 -0.0716 0.7642 1.0000
1.750 0.5362 0.00903 0.00317 -0.0709 0.7461 1.0000
2.000 0.5618 0.00913 0.00318 -0.0701 0.7267 1.0000
2.250 0.5873 0.00924 0.00321 -0.0694 0.7066 1.0000
2.500 0.6130 0.00939 0.00324 -0.0688 0.6867 1.0000
2.750 0.6383 0.00955 0.00332 -0.0681 0.6646 1.0000
3.000 0.6637 0.00974 0.00342 -0.0674 0.6432 1.0000
3.250 0.6889 0.00993 0.00353 -0.0668 0.6205 1.0000
3.500 0.7141 0.01015 0.00366 -0.0661 0.5986 1.0000
3.750 0.7392 0.01038 0.00381 -0.0655 0.5761 1.0000
4.000 0.7641 0.01063 0.00401 -0.0649 0.5534 1.0000
4.250 0.7889 0.01091 0.00420 -0.0642 0.5310 1.0000
4.500 0.8136 0.01118 0.00442 -0.0636 0.5074 1.0000
4.750 0.8380 0.01148 0.00465 -0.0629 0.4838 1.0000
5.000 0.8620 0.01182 0.00492 -0.0622 0.4599 1.0000
5.250 0.8861 0.01214 0.00521 -0.0616 0.4353 1.0000
5.500 0.9100 0.01250 0.00551 -0.0609 0.4117 1.0000
5.750 0.9333 0.01291 0.00584 -0.0601 0.3885 1.0000
6.000 0.9569 0.01329 0.00623 -0.0594 0.3645 1.0000
6.250 0.9800 0.01372 0.00662 -0.0587 0.3413 1.0000
6.500 1.0024 0.01420 0.00702 -0.0579 0.3176 1.0000
6.750 1.0250 0.01466 0.00747 -0.0571 0.2933 1.0000
7.000 1.0470 0.01518 0.00795 -0.0563 0.2697 1.0000
7.250 1.0682 0.01576 0.00848 -0.0553 0.2471 1.0000
7.500 1.0898 0.01630 0.00903 -0.0545 0.2237 1.0000
7.750 1.1104 0.01693 0.00962 -0.0535 0.2013 1.0000
8.000 1.1303 0.01762 0.01026 -0.0525 0.1793 1.0000
8.250 1.1500 0.01832 0.01096 -0.0514 0.1575 1.0000
8.500 1.1676 0.01920 0.01177 -0.0501 0.1374 1.0000
8.750 1.1859 0.02003 0.01262 -0.0489 0.1167 1.0000
9.000 1.2009 0.02111 0.01361 -0.0473 0.0987 1.0000
9.250 1.2150 0.02228 0.01476 -0.0455 0.0830 1.0000
9.500 1.2278 0.02352 0.01601 -0.0436 0.0703 1.0000
9.750 1.2370 0.02502 0.01748 -0.0413 0.0607 1.0000
10.000 1.2506 0.02593 0.01853 -0.0394 0.0523 1.0000
10.250 1.2573 0.02736 0.02001 -0.0368 0.0459 1.0000
10.500 1.2631 0.02872 0.02141 -0.0343 0.0397 1.0000
10.750 1.2698 0.03024 0.02310 -0.0320 0.0347 1.0000
11.000 1.2731 0.03195 0.02485 -0.0297 0.0305 1.0000
11.250 1.2737 0.03430 0.02735 -0.0272 0.0269 1.0000
11.500 1.2783 0.03601 0.02919 -0.0254 0.0239 1.0000
11.750 1.2773 0.03837 0.03157 -0.0237 0.0215 1.0000
12.000 1.2770 0.04142 0.03481 -0.0219 0.0200 1.0000
12.250 1.2794 0.04392 0.03752 -0.0206 0.0188 1.0000
12.500 1.2803 0.04672 0.04052 -0.0195 0.0179 1.0000
12.750 1.2795 0.04973 0.04373 -0.0186 0.0172 1.0000
13.000 1.2770 0.05295 0.04713 -0.0181 0.0165 1.0000
13.250 1.2733 0.05647 0.05084 -0.0180 0.0162 1.0000
13.500 1.2674 0.06037 0.05492 -0.0183 0.0158 1.0000
13.750 1.2593 0.06472 0.05945 -0.0189 0.0155 1.0000
14.000 1.2497 0.06948 0.06443 -0.0201 0.0154 1.0000
14.250 1.2373 0.07487 0.07004 -0.0219 0.0153 1.0000
14.500 1.2231 0.08079 0.07617 -0.0244 0.0152 1.0000
14.750 1.2074 0.08726 0.08288 -0.0276 0.0153 1.0000
15.000 1.1905 0.09435 0.09019 -0.0316 0.0154 1.0000
15.250 1.1707 0.10257 0.09864 -0.0365 0.0155 1.0000
15.500 1.1455 0.11267 0.10902 -0.0430 0.0159 1.0000
15.750 1.1169 0.12445 0.12105 -0.0508 0.0164 1.0000
16.000 1.0733 0.14177 0.13862 -0.0624 0.0176 1.0000
16.250 1.0286 0.16161 0.15856 -0.0746 0.0193 1.0000
16.500 1.0047 0.17594 0.17284 -0.0822 0.0203 1.0000
16.750 0.9960 0.18538 0.18226 -0.0868 0.0207 1.0000
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