SD7032-099-88 (sd7032-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7032-099-88 (sd7032-il) Reynolds number: 200,000 Max Cl/Cd: 77.87 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7032-il-200000.txt Download as CSV file: xf-sd7032-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2585 0.09769 0.09447 -0.0394 1.0000 0.0407
-9.250 -0.2669 0.09516 0.09201 -0.0400 1.0000 0.0409
-9.000 -0.2754 0.09273 0.08964 -0.0395 1.0000 0.0410
-8.750 -0.2707 0.08793 0.08488 -0.0362 1.0000 0.0423
-8.500 -0.2656 0.08626 0.08324 -0.0329 1.0000 0.0441
-8.250 -0.2719 0.08433 0.08135 -0.0310 1.0000 0.0449
-8.000 -0.2804 0.08243 0.07950 -0.0290 1.0000 0.0459
-7.750 -0.2906 0.08053 0.07766 -0.0272 1.0000 0.0467
-7.500 -0.3027 0.07864 0.07584 -0.0253 1.0000 0.0475
-7.250 -0.3805 0.08449 0.08152 -0.0263 1.0000 0.0441
-7.000 -0.3980 0.08316 0.08027 -0.0236 1.0000 0.0442
-6.750 -0.4039 0.08084 0.07799 -0.0237 0.9994 0.0448
-6.500 -0.3750 0.07508 0.07220 -0.0340 0.9936 0.0483
-6.250 -0.3258 0.06369 0.06028 -0.0632 0.9832 0.0524
-6.000 -0.3146 0.05790 0.05470 -0.0634 0.9782 0.0542
-5.750 -0.2875 0.05513 0.05192 -0.0658 0.9738 0.0565
-5.250 -0.2227 0.04381 0.03997 -0.0803 0.9612 0.0677
-5.000 -0.1870 0.04081 0.03691 -0.0840 0.9581 0.0721
-4.750 -0.1574 0.03666 0.03233 -0.0877 0.9505 0.0818
-4.500 -0.1135 0.02580 0.01995 -0.0905 0.9467 0.0390
-4.250 -0.0709 0.02331 0.01692 -0.0933 0.9440 0.0401
-4.000 -0.0377 0.02090 0.01411 -0.0943 0.9382 0.0398
-3.750 0.0006 0.01934 0.01221 -0.0958 0.9335 0.0408
-3.500 0.0403 0.01744 0.01027 -0.0982 0.9304 0.0457
-3.250 0.0757 0.01644 0.00918 -0.0993 0.9252 0.0498
-3.000 0.1075 0.01538 0.00810 -0.0998 0.9182 0.0558
-2.750 0.1455 0.01462 0.00730 -0.1014 0.9142 0.0651
-2.500 0.1724 0.01379 0.00659 -0.1010 0.9049 0.0849
-2.250 0.2049 0.01229 0.00591 -0.1022 0.8996 0.2794
-2.000 0.2292 0.01154 0.00578 -0.1015 0.8898 0.4551
-1.750 0.2573 0.01087 0.00563 -0.1009 0.8840 0.6181
-1.500 0.2763 0.01050 0.00563 -0.0981 0.8730 0.7441
-1.250 0.2960 0.01022 0.00550 -0.0953 0.8635 0.8273
-1.000 0.3188 0.00990 0.00522 -0.0929 0.8555 0.8971
-0.750 0.3651 0.00957 0.00484 -0.0959 0.8456 0.9915
-0.500 0.3938 0.00949 0.00459 -0.0959 0.8349 1.0000
-0.250 0.4217 0.00941 0.00435 -0.0955 0.8243 1.0000
0.000 0.4487 0.00937 0.00417 -0.0951 0.8120 1.0000
0.250 0.4756 0.00935 0.00403 -0.0947 0.7988 1.0000
0.500 0.5026 0.00936 0.00391 -0.0942 0.7852 1.0000
0.750 0.5297 0.00937 0.00381 -0.0938 0.7713 1.0000
1.000 0.5569 0.00941 0.00372 -0.0934 0.7567 1.0000
1.250 0.5839 0.00947 0.00367 -0.0930 0.7416 1.0000
1.500 0.6110 0.00954 0.00363 -0.0926 0.7262 1.0000
1.750 0.6379 0.00964 0.00361 -0.0922 0.7102 1.0000
2.000 0.6647 0.00976 0.00362 -0.0918 0.6939 1.0000
2.250 0.6912 0.00990 0.00367 -0.0913 0.6761 1.0000
2.500 0.7176 0.01005 0.00373 -0.0909 0.6581 1.0000
2.750 0.7439 0.01023 0.00381 -0.0904 0.6401 1.0000
3.000 0.7700 0.01042 0.00389 -0.0900 0.6221 1.0000
3.250 0.7960 0.01063 0.00401 -0.0895 0.6033 1.0000
3.500 0.8218 0.01084 0.00417 -0.0890 0.5844 1.0000
3.750 0.8474 0.01108 0.00432 -0.0885 0.5659 1.0000
4.000 0.8730 0.01135 0.00449 -0.0881 0.5480 1.0000
4.250 0.8983 0.01160 0.00469 -0.0876 0.5291 1.0000
4.500 0.9235 0.01188 0.00493 -0.0871 0.5105 1.0000
4.750 0.9485 0.01218 0.00516 -0.0865 0.4925 1.0000
5.000 0.9734 0.01251 0.00541 -0.0860 0.4750 1.0000
5.250 0.9980 0.01283 0.00569 -0.0854 0.4570 1.0000
5.500 1.0225 0.01316 0.00602 -0.0849 0.4391 1.0000
5.750 1.0467 0.01351 0.00634 -0.0843 0.4215 1.0000
6.000 1.0705 0.01389 0.00667 -0.0836 0.4042 1.0000
6.250 1.0941 0.01430 0.00703 -0.0830 0.3873 1.0000
6.500 1.1174 0.01470 0.00742 -0.0823 0.3697 1.0000
6.750 1.1404 0.01510 0.00782 -0.0815 0.3521 1.0000
7.000 1.1631 0.01553 0.00824 -0.0808 0.3349 1.0000
7.250 1.1851 0.01599 0.00870 -0.0799 0.3177 1.0000
7.500 1.2066 0.01649 0.00916 -0.0790 0.3009 1.0000
7.750 1.2277 0.01701 0.00966 -0.0781 0.2844 1.0000
8.000 1.2487 0.01751 0.01018 -0.0771 0.2675 1.0000
8.250 1.2691 0.01804 0.01075 -0.0761 0.2513 1.0000
8.500 1.2888 0.01861 0.01134 -0.0750 0.2355 1.0000
8.750 1.3077 0.01922 0.01196 -0.0737 0.2199 1.0000
9.000 1.3257 0.01986 0.01262 -0.0724 0.2042 1.0000
9.250 1.3425 0.02056 0.01332 -0.0710 0.1889 1.0000
9.500 1.3577 0.02134 0.01410 -0.0693 0.1734 1.0000
9.750 1.3708 0.02222 0.01496 -0.0674 0.1580 1.0000
10.000 1.3823 0.02309 0.01584 -0.0652 0.1426 1.0000
10.250 1.3917 0.02407 0.01684 -0.0628 0.1278 1.0000
10.500 1.3994 0.02519 0.01796 -0.0603 0.1144 1.0000
10.750 1.4052 0.02649 0.01923 -0.0577 0.1028 1.0000
11.000 1.4101 0.02791 0.02064 -0.0553 0.0929 1.0000
11.250 1.4172 0.02926 0.02209 -0.0532 0.0840 1.0000
11.500 1.4199 0.03101 0.02387 -0.0509 0.0774 1.0000
11.750 1.4246 0.03262 0.02557 -0.0491 0.0711 1.0000
12.000 1.4260 0.03467 0.02766 -0.0471 0.0660 1.0000
12.250 1.4305 0.03646 0.02957 -0.0456 0.0608 1.0000
12.500 1.4280 0.03906 0.03214 -0.0440 0.0564 1.0000
12.750 1.4327 0.04096 0.03426 -0.0430 0.0520 1.0000
13.000 1.4321 0.04346 0.03681 -0.0420 0.0482 1.0000
13.250 1.4298 0.04639 0.03983 -0.0411 0.0448 1.0000
13.500 1.4305 0.04902 0.04264 -0.0407 0.0413 1.0000
13.750 1.4274 0.05215 0.04584 -0.0406 0.0385 1.0000
14.000 1.4218 0.05584 0.04959 -0.0402 0.0358 1.0000
14.250 1.4194 0.05925 0.05325 -0.0405 0.0334 1.0000
14.500 1.4153 0.06296 0.05707 -0.0413 0.0310 1.0000
14.750 1.4087 0.06711 0.06125 -0.0420 0.0291 1.0000
15.000 1.4016 0.07158 0.06588 -0.0428 0.0272 1.0000
15.250 1.3957 0.07612 0.07063 -0.0441 0.0256 1.0000
15.500 1.3899 0.08073 0.07538 -0.0457 0.0242 1.0000
15.750 1.3839 0.08541 0.08016 -0.0473 0.0230 1.0000
16.000 1.3772 0.09020 0.08500 -0.0487 0.0219 1.0000
16.250 1.3686 0.09555 0.09051 -0.0502 0.0210 1.0000
16.500 1.3595 0.10134 0.09653 -0.0528 0.0205 1.0000
16.750 1.3497 0.10740 0.10280 -0.0557 0.0200 1.0000
17.000 1.3394 0.11370 0.10930 -0.0589 0.0194 1.0000
17.250 1.3286 0.12026 0.11605 -0.0624 0.0190 1.0000
17.500 1.3170 0.12714 0.12312 -0.0664 0.0186 1.0000
17.750 1.3048 0.13439 0.13055 -0.0707 0.0184 1.0000
18.000 1.2920 0.14198 0.13832 -0.0755 0.0181 1.0000
18.250 1.2753 0.15082 0.14736 -0.0812 0.0182 1.0000
18.500 1.2530 0.16159 0.15835 -0.0884 0.0186 1.0000
18.750 1.2200 0.17616 0.17314 -0.0982 0.0197 1.0000
19.000 1.1860 0.19231 0.18942 -0.1089 0.0208 1.0000
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Polar data table (+)
Polar graphs
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