SD7034 (sd7034-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7034 (sd7034-il) Reynolds number: 100,000 Max Cl/Cd: 57.56 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7034-il-100000-n5.txt Download as CSV file: xf-sd7034-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD7034
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3324 0.09764 0.09275 -0.0353 1.0000 0.0324
-9.000 -0.3254 0.09474 0.08988 -0.0357 1.0000 0.0319
-8.750 -0.3222 0.09132 0.08652 -0.0368 1.0000 0.0315
-8.500 -0.3206 0.08796 0.08323 -0.0380 1.0000 0.0310
-8.250 -0.3217 0.08458 0.07993 -0.0392 1.0000 0.0305
-8.000 -0.3278 0.08146 0.07693 -0.0398 1.0000 0.0303
-7.750 -0.3430 0.07946 0.07506 -0.0382 1.0000 0.0299
-7.500 -0.3402 0.07465 0.07031 -0.0435 0.9870 0.0296
-7.250 -0.3213 0.06697 0.06259 -0.0555 0.9740 0.0297
-7.000 -0.3019 0.05818 0.05366 -0.0681 0.9610 0.0301
-6.750 -0.2863 0.04798 0.04307 -0.0793 0.9477 0.0309
-6.500 -0.2710 0.03985 0.03428 -0.0855 0.9356 0.0314
-6.250 -0.2514 0.03351 0.02705 -0.0888 0.9259 0.0322
-6.000 -0.2282 0.03030 0.02334 -0.0898 0.9168 0.0334
-5.750 -0.2024 0.02924 0.02214 -0.0902 0.9084 0.0357
-5.500 -0.1764 0.02694 0.01928 -0.0906 0.9004 0.0386
-5.250 -0.1512 0.02489 0.01679 -0.0904 0.8917 0.0405
-5.000 -0.1240 0.02404 0.01585 -0.0906 0.8843 0.0437
-4.750 -0.0981 0.02279 0.01425 -0.0901 0.8756 0.0473
-4.500 -0.0712 0.02161 0.01291 -0.0899 0.8684 0.0504
-4.250 -0.0456 0.02094 0.01214 -0.0895 0.8596 0.0551
-4.000 -0.0185 0.01997 0.01095 -0.0889 0.8525 0.0597
-3.750 0.0067 0.01934 0.01034 -0.0885 0.8436 0.0656
-3.500 0.0334 0.01864 0.00953 -0.0879 0.8365 0.0732
-3.250 0.0589 0.01814 0.00898 -0.0874 0.8274 0.0828
-3.000 0.0854 0.01762 0.00843 -0.0869 0.8204 0.0953
-2.750 0.1110 0.01721 0.00802 -0.0864 0.8110 0.1109
-2.500 0.1376 0.01675 0.00757 -0.0859 0.8041 0.1308
-2.250 0.1632 0.01637 0.00726 -0.0855 0.7945 0.1568
-2.000 0.1897 0.01591 0.00691 -0.0850 0.7875 0.1968
-1.750 0.2151 0.01549 0.00672 -0.0846 0.7779 0.2624
-1.500 0.2409 0.01499 0.00654 -0.0841 0.7703 0.3664
-1.250 0.2653 0.01455 0.00648 -0.0833 0.7612 0.4910
-1.000 0.2884 0.01411 0.00643 -0.0818 0.7531 0.6241
-0.750 0.3089 0.01366 0.00638 -0.0792 0.7444 0.7702
-0.500 0.3557 0.01324 0.00608 -0.0819 0.7357 1.0000
-0.250 0.3823 0.01328 0.00592 -0.0815 0.7270 1.0000
0.000 0.4085 0.01338 0.00585 -0.0811 0.7168 1.0000
0.250 0.4353 0.01344 0.00573 -0.0806 0.7081 1.0000
0.500 0.4617 0.01354 0.00570 -0.0802 0.6978 1.0000
0.750 0.4882 0.01364 0.00567 -0.0798 0.6877 1.0000
1.000 0.5152 0.01371 0.00558 -0.0794 0.6787 1.0000
1.250 0.5415 0.01384 0.00562 -0.0790 0.6674 1.0000
1.500 0.5680 0.01396 0.00565 -0.0786 0.6567 1.0000
1.750 0.5949 0.01405 0.00562 -0.0781 0.6469 1.0000
2.000 0.6213 0.01419 0.00569 -0.0777 0.6354 1.0000
2.250 0.6477 0.01434 0.00578 -0.0774 0.6239 1.0000
2.500 0.6742 0.01448 0.00584 -0.0769 0.6128 1.0000
2.750 0.7008 0.01462 0.00588 -0.0765 0.6019 1.0000
3.000 0.7268 0.01480 0.00604 -0.0761 0.5892 1.0000
3.250 0.7529 0.01498 0.00618 -0.0757 0.5768 1.0000
3.500 0.7790 0.01517 0.00632 -0.0752 0.5644 1.0000
3.750 0.8050 0.01536 0.00648 -0.0748 0.5520 1.0000
4.000 0.8309 0.01557 0.00663 -0.0743 0.5394 1.0000
4.250 0.8565 0.01580 0.00683 -0.0738 0.5260 1.0000
4.500 0.8818 0.01605 0.00709 -0.0733 0.5123 1.0000
4.750 0.9071 0.01632 0.00734 -0.0729 0.4986 1.0000
5.000 0.9321 0.01660 0.00760 -0.0723 0.4847 1.0000
5.250 0.9569 0.01689 0.00791 -0.0718 0.4707 1.0000
5.500 0.9815 0.01721 0.00821 -0.0712 0.4564 1.0000
5.750 1.0057 0.01755 0.00854 -0.0706 0.4421 1.0000
6.000 1.0297 0.01791 0.00890 -0.0700 0.4276 1.0000
6.250 1.0533 0.01830 0.00930 -0.0693 0.4130 1.0000
6.500 1.0765 0.01871 0.00971 -0.0686 0.3983 1.0000
6.750 1.0994 0.01914 0.01015 -0.0679 0.3837 1.0000
7.000 1.1218 0.01960 0.01063 -0.0671 0.3690 1.0000
7.250 1.1437 0.02009 0.01114 -0.0663 0.3542 1.0000
7.500 1.1651 0.02061 0.01167 -0.0655 0.3397 1.0000
7.750 1.1859 0.02116 0.01224 -0.0645 0.3251 1.0000
8.000 1.2060 0.02174 0.01285 -0.0635 0.3106 1.0000
8.250 1.2253 0.02236 0.01349 -0.0625 0.2960 1.0000
8.500 1.2437 0.02302 0.01417 -0.0613 0.2814 1.0000
8.750 1.2612 0.02371 0.01490 -0.0601 0.2667 1.0000
9.000 1.2777 0.02445 0.01569 -0.0587 0.2521 1.0000
9.250 1.2931 0.02523 0.01652 -0.0573 0.2378 1.0000
9.500 1.3072 0.02606 0.01739 -0.0557 0.2238 1.0000
9.750 1.3198 0.02695 0.01833 -0.0540 0.2102 1.0000
10.000 1.3298 0.02788 0.01933 -0.0520 0.1972 1.0000
10.250 1.3382 0.02891 0.02042 -0.0499 0.1847 1.0000
10.500 1.3456 0.03007 0.02162 -0.0479 0.1727 1.0000
10.750 1.3518 0.03136 0.02296 -0.0460 0.1613 1.0000
11.000 1.3563 0.03284 0.02445 -0.0442 0.1503 1.0000
11.250 1.3606 0.03444 0.02611 -0.0425 0.1394 1.0000
11.500 1.3647 0.03615 0.02792 -0.0411 0.1291 1.0000
11.750 1.3670 0.03809 0.02992 -0.0398 0.1199 1.0000
12.000 1.3667 0.04034 0.03218 -0.0386 0.1120 1.0000
12.250 1.3690 0.04252 0.03447 -0.0377 0.1038 1.0000
12.500 1.3675 0.04511 0.03710 -0.0370 0.0973 1.0000
12.750 1.3673 0.04771 0.03982 -0.0364 0.0907 1.0000
13.000 1.3638 0.05074 0.04287 -0.0361 0.0859 1.0000
13.250 1.3631 0.05363 0.04592 -0.0359 0.0804 1.0000
13.500 1.3581 0.05706 0.04940 -0.0360 0.0764 1.0000
13.750 1.3553 0.06038 0.05286 -0.0362 0.0723 1.0000
14.000 1.3520 0.06389 0.05651 -0.0366 0.0686 1.0000
14.250 1.3463 0.06779 0.06048 -0.0373 0.0657 1.0000
14.500 1.3420 0.07166 0.06445 -0.0380 0.0628 1.0000
14.750 1.3386 0.07558 0.06855 -0.0389 0.0598 1.0000
15.000 1.3335 0.07984 0.07293 -0.0401 0.0572 1.0000
15.250 1.3279 0.08422 0.07737 -0.0415 0.0551 1.0000
15.500 1.3238 0.08849 0.08175 -0.0427 0.0529 1.0000
15.750 1.3191 0.09305 0.08651 -0.0443 0.0507 1.0000
16.000 1.3140 0.09776 0.09136 -0.0461 0.0488 1.0000
16.250 1.3086 0.10255 0.09625 -0.0480 0.0470 1.0000
16.500 1.3054 0.10683 0.10056 -0.0497 0.0454 1.0000
16.750 1.3000 0.11187 0.10579 -0.0518 0.0440 1.0000
17.000 1.2923 0.11753 0.11168 -0.0545 0.0426 1.0000
17.250 1.2843 0.12336 0.11770 -0.0574 0.0413 1.0000
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