SD7032-099-88 (sd7032-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7032-099-88 (sd7032-il) Reynolds number: 200,000 Max Cl/Cd: 75.15 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7032-il-200000-n5.txt Download as CSV file: xf-sd7032-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD7032-099-88
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3375 0.08589 0.08257 -0.0374 1.0000 0.0174
-8.000 -0.3462 0.08403 0.08078 -0.0354 1.0000 0.0171
-7.750 -0.3414 0.08047 0.07726 -0.0379 0.9961 0.0165
-7.500 -0.3301 0.07516 0.07196 -0.0443 0.9878 0.0158
-7.000 -0.2967 0.04927 0.04579 -0.0790 0.9677 0.0132
-6.750 -0.2777 0.04057 0.03669 -0.0874 0.9598 0.0130
-6.500 -0.2588 0.03334 0.02884 -0.0923 0.9518 0.0130
-6.250 -0.2347 0.02776 0.02244 -0.0952 0.9455 0.0132
-6.000 -0.2091 0.02460 0.01879 -0.0965 0.9397 0.0136
-5.750 -0.1828 0.02296 0.01691 -0.0971 0.9333 0.0143
-5.500 -0.1524 0.02181 0.01555 -0.0981 0.9290 0.0156
-5.250 -0.1269 0.02034 0.01369 -0.0978 0.9217 0.0172
-5.000 -0.0978 0.01884 0.01179 -0.0979 0.9161 0.0180
-4.750 -0.0716 0.01739 0.01023 -0.0979 0.9096 0.0191
-4.500 -0.0445 0.01648 0.00923 -0.0977 0.9027 0.0205
-4.250 -0.0165 0.01578 0.00839 -0.0976 0.8964 0.0229
-4.000 0.0096 0.01494 0.00748 -0.0972 0.8885 0.0255
-3.750 0.0371 0.01429 0.00677 -0.0971 0.8816 0.0278
-3.500 0.0640 0.01384 0.00622 -0.0967 0.8732 0.0313
-3.250 0.0910 0.01323 0.00557 -0.0965 0.8652 0.0352
-3.000 0.1186 0.01284 0.00509 -0.0963 0.8568 0.0400
-2.750 0.1456 0.01241 0.00465 -0.0960 0.8473 0.0481
-2.500 0.1735 0.01200 0.00422 -0.0957 0.8387 0.0656
-2.250 0.2004 0.01152 0.00392 -0.0956 0.8285 0.1167
-2.000 0.2273 0.01110 0.00371 -0.0955 0.8179 0.1880
-1.750 0.2542 0.01066 0.00353 -0.0954 0.8074 0.2788
-1.500 0.2803 0.01009 0.00342 -0.0951 0.7965 0.4239
-1.250 0.3054 0.00969 0.00338 -0.0945 0.7842 0.5498
-1.000 0.3304 0.00944 0.00335 -0.0935 0.7717 0.6384
-0.750 0.3544 0.00925 0.00331 -0.0923 0.7587 0.7157
-0.500 0.3781 0.00913 0.00325 -0.0908 0.7452 0.7768
-0.250 0.4010 0.00903 0.00318 -0.0892 0.7313 0.8323
0.000 0.4251 0.00893 0.00308 -0.0878 0.7169 0.8908
0.250 0.4620 0.00884 0.00291 -0.0893 0.7014 0.9727
0.500 0.4912 0.00892 0.00284 -0.0895 0.6855 1.0000
0.750 0.5184 0.00903 0.00281 -0.0893 0.6696 1.0000
1.000 0.5454 0.00917 0.00280 -0.0890 0.6534 1.0000
1.250 0.5723 0.00931 0.00281 -0.0888 0.6373 1.0000
1.500 0.5991 0.00947 0.00283 -0.0885 0.6210 1.0000
1.750 0.6259 0.00963 0.00289 -0.0883 0.6043 1.0000
2.000 0.6525 0.00980 0.00295 -0.0880 0.5877 1.0000
2.250 0.6790 0.00999 0.00303 -0.0877 0.5706 1.0000
2.500 0.7053 0.01019 0.00314 -0.0874 0.5535 1.0000
2.750 0.7314 0.01040 0.00325 -0.0870 0.5360 1.0000
3.000 0.7573 0.01063 0.00338 -0.0867 0.5185 1.0000
3.250 0.7832 0.01086 0.00352 -0.0863 0.5007 1.0000
3.500 0.8090 0.01110 0.00370 -0.0859 0.4834 1.0000
3.750 0.8346 0.01135 0.00388 -0.0856 0.4664 1.0000
4.000 0.8601 0.01162 0.00407 -0.0852 0.4499 1.0000
4.250 0.8855 0.01189 0.00430 -0.0848 0.4336 1.0000
4.500 0.9106 0.01218 0.00453 -0.0844 0.4176 1.0000
4.750 0.9356 0.01248 0.00478 -0.0839 0.4021 1.0000
5.000 0.9605 0.01279 0.00505 -0.0835 0.3869 1.0000
5.250 0.9852 0.01311 0.00535 -0.0830 0.3716 1.0000
5.500 1.0097 0.01344 0.00565 -0.0825 0.3567 1.0000
5.750 1.0341 0.01378 0.00597 -0.0820 0.3420 1.0000
6.000 1.0581 0.01414 0.00631 -0.0815 0.3270 1.0000
6.250 1.0819 0.01452 0.00669 -0.0809 0.3121 1.0000
6.500 1.1053 0.01492 0.00707 -0.0803 0.2966 1.0000
6.750 1.1284 0.01533 0.00747 -0.0796 0.2813 1.0000
7.000 1.1511 0.01577 0.00790 -0.0789 0.2662 1.0000
7.250 1.1734 0.01622 0.00837 -0.0782 0.2508 1.0000
7.500 1.1953 0.01671 0.00884 -0.0774 0.2353 1.0000
7.750 1.2166 0.01722 0.00934 -0.0765 0.2198 1.0000
8.000 1.2374 0.01776 0.00987 -0.0756 0.2044 1.0000
8.250 1.2577 0.01832 0.01046 -0.0746 0.1902 1.0000
8.500 1.2776 0.01891 0.01105 -0.0736 0.1770 1.0000
8.750 1.2967 0.01953 0.01168 -0.0725 0.1639 1.0000
9.000 1.3150 0.02018 0.01236 -0.0713 0.1507 1.0000
9.250 1.3324 0.02088 0.01307 -0.0700 0.1377 1.0000
9.500 1.3487 0.02162 0.01385 -0.0685 0.1251 1.0000
9.750 1.3630 0.02241 0.01464 -0.0667 0.1126 1.0000
10.000 1.3755 0.02325 0.01550 -0.0648 0.1010 1.0000
10.250 1.3866 0.02418 0.01644 -0.0627 0.0905 1.0000
10.750 1.4064 0.02626 0.01858 -0.0585 0.0726 1.0000
11.000 1.4149 0.02743 0.01980 -0.0565 0.0661 1.0000
11.250 1.4224 0.02871 0.02115 -0.0545 0.0599 1.0000
11.500 1.4293 0.03006 0.02259 -0.0526 0.0551 1.0000
11.750 1.4359 0.03150 0.02413 -0.0509 0.0506 1.0000
12.000 1.4383 0.03333 0.02599 -0.0490 0.0469 1.0000
12.250 1.4450 0.03487 0.02770 -0.0476 0.0437 1.0000
12.500 1.4486 0.03675 0.02968 -0.0463 0.0402 1.0000
12.750 1.4482 0.03909 0.03207 -0.0450 0.0371 1.0000
13.000 1.4535 0.04100 0.03414 -0.0441 0.0336 1.0000
13.250 1.4542 0.04344 0.03665 -0.0434 0.0305 1.0000
13.500 1.4530 0.04621 0.03951 -0.0429 0.0280 1.0000
13.750 1.4548 0.04879 0.04227 -0.0426 0.0254 1.0000
14.000 1.4527 0.05193 0.04552 -0.0427 0.0233 1.0000
14.250 1.4464 0.05574 0.04944 -0.0431 0.0219 1.0000
14.500 1.4438 0.05926 0.05313 -0.0435 0.0205 1.0000
14.750 1.4391 0.06320 0.05724 -0.0444 0.0192 1.0000
15.000 1.4326 0.06759 0.06177 -0.0456 0.0179 1.0000
15.250 1.4234 0.07258 0.06689 -0.0472 0.0170 1.0000
15.500 1.4121 0.07812 0.07256 -0.0493 0.0162 1.0000
15.750 1.4035 0.08341 0.07803 -0.0513 0.0153 1.0000
16.000 1.3937 0.08908 0.08388 -0.0537 0.0143 1.0000
16.250 1.3824 0.09517 0.09012 -0.0564 0.0137 1.0000
16.500 1.3704 0.10158 0.09668 -0.0594 0.0132 1.0000
16.750 1.3567 0.10850 0.10373 -0.0629 0.0127 1.0000
17.000 1.3426 0.11567 0.11104 -0.0665 0.0123 1.0000
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Polar data table (+)
Polar graphs
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