SD7034 (sd7034-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7034 (sd7034-il) Reynolds number: 50,000 Max Cl/Cd: 37.39 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7034-il-50000-n5.txt Download as CSV file: xf-sd7034-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3312 0.09505 0.08843 -0.0404 1.0000 0.0588
-8.250 -0.3236 0.09200 0.08543 -0.0395 1.0000 0.0578
-8.000 -0.3246 0.08907 0.08261 -0.0396 1.0000 0.0572
-7.750 -0.3311 0.08658 0.08024 -0.0391 1.0000 0.0568
-7.500 -0.3428 0.08445 0.07826 -0.0380 1.0000 0.0564
-7.250 -0.3555 0.08219 0.07613 -0.0371 1.0000 0.0562
-7.000 -0.3681 0.07998 0.07404 -0.0362 1.0000 0.0558
-6.750 -0.3807 0.07733 0.07145 -0.0360 1.0000 0.0559
-6.500 -0.3898 0.07449 0.06867 -0.0360 1.0000 0.0554
-6.250 -0.3678 0.06760 0.06161 -0.0456 0.9890 0.0560
-6.000 -0.3445 0.06086 0.05462 -0.0539 0.9788 0.0562
-5.750 -0.3184 0.05441 0.04779 -0.0612 0.9697 0.0561
-5.500 -0.2910 0.04826 0.04108 -0.0674 0.9606 0.0570
-5.250 -0.2626 0.04310 0.03521 -0.0719 0.9518 0.0596
-5.000 -0.2297 0.04061 0.03253 -0.0748 0.9450 0.0627
-4.750 -0.2001 0.03750 0.02890 -0.0769 0.9366 0.0655
-4.500 -0.1624 0.03433 0.02481 -0.0799 0.9302 0.0710
-4.250 -0.1330 0.03253 0.02288 -0.0810 0.9219 0.0747
-4.000 -0.0957 0.03079 0.02069 -0.0830 0.9156 0.0823
-3.750 -0.0656 0.02940 0.01911 -0.0836 0.9072 0.0885
-3.500 -0.0301 0.02817 0.01753 -0.0849 0.9003 0.0991
-3.250 -0.0013 0.02728 0.01656 -0.0851 0.8915 0.1105
-3.000 0.0335 0.02637 0.01551 -0.0863 0.8845 0.1271
-2.750 0.0608 0.02570 0.01481 -0.0862 0.8751 0.1455
-2.500 0.0953 0.02496 0.01404 -0.0872 0.8682 0.1730
-2.250 0.1213 0.02440 0.01357 -0.0870 0.8581 0.2069
-2.000 0.1549 0.02357 0.01301 -0.0880 0.8515 0.2708
-1.750 0.1775 0.02290 0.01287 -0.0873 0.8408 0.3787
-1.500 0.2011 0.02210 0.01281 -0.0858 0.8329 0.5635
-1.250 0.2198 0.02145 0.01280 -0.0823 0.8237 0.7732
-1.000 0.2725 0.02111 0.01230 -0.0861 0.8161 1.0000
-0.750 0.3005 0.02125 0.01212 -0.0860 0.8065 1.0000
-0.500 0.3258 0.02147 0.01208 -0.0856 0.7959 1.0000
-0.250 0.3573 0.02153 0.01186 -0.0858 0.7883 1.0000
0.000 0.3806 0.02180 0.01193 -0.0851 0.7767 1.0000
0.250 0.4067 0.02201 0.01195 -0.0847 0.7666 1.0000
0.500 0.4360 0.02209 0.01184 -0.0845 0.7580 1.0000
0.750 0.4598 0.02237 0.01198 -0.0838 0.7465 1.0000
1.000 0.4865 0.02254 0.01201 -0.0833 0.7366 1.0000
1.250 0.5144 0.02264 0.01198 -0.0829 0.7272 1.0000
1.500 0.5384 0.02292 0.01217 -0.0821 0.7155 1.0000
1.750 0.5648 0.02309 0.01225 -0.0816 0.7053 1.0000
2.000 0.5928 0.02317 0.01223 -0.0811 0.6957 1.0000
2.250 0.6166 0.02346 0.01248 -0.0803 0.6836 1.0000
2.500 0.6420 0.02368 0.01263 -0.0796 0.6724 1.0000
2.750 0.6714 0.02365 0.01252 -0.0791 0.6635 1.0000
3.000 0.6948 0.02397 0.01284 -0.0783 0.6507 1.0000
3.250 0.7191 0.02425 0.01311 -0.0775 0.6385 1.0000
3.500 0.7447 0.02444 0.01328 -0.0768 0.6269 1.0000
3.750 0.7730 0.02446 0.01325 -0.0762 0.6168 1.0000
4.000 0.7968 0.02476 0.01359 -0.0754 0.6037 1.0000
4.250 0.8207 0.02508 0.01392 -0.0746 0.5907 1.0000
4.500 0.8451 0.02535 0.01421 -0.0738 0.5778 1.0000
4.750 0.8702 0.02559 0.01449 -0.0730 0.5653 1.0000
5.000 0.8959 0.02578 0.01468 -0.0722 0.5529 1.0000
5.250 0.9218 0.02596 0.01487 -0.0714 0.5403 1.0000
5.500 0.9448 0.02634 0.01531 -0.0705 0.5262 1.0000
5.750 0.9678 0.02674 0.01578 -0.0696 0.5122 1.0000
6.000 0.9908 0.02714 0.01624 -0.0687 0.4981 1.0000
6.250 1.0137 0.02756 0.01671 -0.0678 0.4839 1.0000
6.500 1.0364 0.02800 0.01723 -0.0669 0.4698 1.0000
6.750 1.0588 0.02847 0.01776 -0.0659 0.4555 1.0000
7.000 1.0808 0.02896 0.01831 -0.0649 0.4411 1.0000
7.250 1.1023 0.02948 0.01892 -0.0639 0.4266 1.0000
7.500 1.1234 0.03005 0.01955 -0.0628 0.4122 1.0000
7.750 1.1438 0.03065 0.02022 -0.0617 0.3976 1.0000
8.000 1.1636 0.03130 0.02094 -0.0605 0.3831 1.0000
8.250 1.1826 0.03200 0.02173 -0.0593 0.3686 1.0000
8.500 1.2008 0.03274 0.02254 -0.0580 0.3541 1.0000
8.750 1.2180 0.03353 0.02340 -0.0567 0.3396 1.0000
9.000 1.2342 0.03437 0.02431 -0.0553 0.3252 1.0000
9.250 1.2490 0.03527 0.02530 -0.0537 0.3109 1.0000
9.500 1.2621 0.03625 0.02638 -0.0521 0.2966 1.0000
9.750 1.2723 0.03738 0.02761 -0.0503 0.2825 1.0000
10.000 1.2804 0.03861 0.02894 -0.0483 0.2687 1.0000
10.250 1.2854 0.03993 0.03037 -0.0461 0.2556 1.0000
10.500 1.2897 0.04140 0.03195 -0.0441 0.2429 1.0000
10.750 1.2931 0.04298 0.03361 -0.0422 0.2306 1.0000
11.000 1.2962 0.04466 0.03534 -0.0405 0.2187 1.0000
11.250 1.2994 0.04639 0.03709 -0.0389 0.2072 1.0000
11.500 1.2984 0.04864 0.03949 -0.0376 0.1959 1.0000
11.750 1.2968 0.05112 0.04209 -0.0365 0.1852 1.0000
12.000 1.2966 0.05355 0.04459 -0.0356 0.1752 1.0000
12.250 1.2974 0.05589 0.04692 -0.0348 0.1657 1.0000
12.500 1.2917 0.05927 0.05054 -0.0346 0.1564 1.0000
12.750 1.2900 0.06224 0.05357 -0.0343 0.1482 1.0000
13.000 1.2872 0.06543 0.05685 -0.0342 0.1402 1.0000
13.250 1.2815 0.06925 0.06082 -0.0345 0.1331 1.0000
13.500 1.2800 0.07243 0.06404 -0.0346 0.1262 1.0000
13.750 1.2721 0.07691 0.06871 -0.0355 0.1205 1.0000
14.000 1.2667 0.08098 0.07291 -0.0363 0.1148 1.0000
14.250 1.2623 0.08502 0.07702 -0.0371 0.1097 1.0000
14.500 1.2474 0.09118 0.08345 -0.0393 0.1057 1.0000
14.750 1.2455 0.09499 0.08731 -0.0403 0.1010 1.0000
15.000 1.2364 0.10039 0.09284 -0.0423 0.0975 1.0000
15.250 1.2098 0.10969 0.10244 -0.0469 0.0956 1.0000
15.500 1.1715 0.12236 0.11536 -0.0539 0.0947 1.0000
15.750 1.1044 0.14434 0.13740 -0.0669 0.0947 1.0000
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Polar data table (+)
Polar graphs
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