SD7034 (sd7034-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7034 (sd7034-il) Reynolds number: 100,000 Max Cl/Cd: 54.29 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7034-il-100000.txt Download as CSV file: xf-sd7034-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3036 0.09482 0.09025 -0.0351 1.0000 0.0997
-8.000 -0.3288 0.09431 0.08994 -0.0377 1.0000 0.1013
-7.750 -0.3559 0.09407 0.08988 -0.0355 1.0000 0.1015
-7.500 -0.3836 0.09363 0.08956 -0.0343 1.0000 0.1017
-7.250 -0.4069 0.09253 0.08853 -0.0349 1.0000 0.1019
-7.000 -0.3806 0.08756 0.08361 -0.0249 1.0000 0.1045
-6.750 -0.3886 0.08611 0.08222 -0.0216 1.0000 0.1060
-6.500 -0.3994 0.08468 0.08086 -0.0195 1.0000 0.1077
-6.250 -0.3991 0.08203 0.07824 -0.0215 0.9977 0.1112
-6.000 -0.3714 0.07464 0.07076 -0.0380 0.9872 0.1189
-5.750 -0.3434 0.07149 0.06760 -0.0392 0.9816 0.1261
-5.500 -0.3143 0.06606 0.06206 -0.0484 0.9731 0.1367
-5.250 -0.2864 0.06117 0.05701 -0.0568 0.9636 0.1502
-5.000 -0.2508 0.05664 0.05231 -0.0642 0.9571 0.1652
-4.750 -0.2100 0.04060 0.03476 -0.0774 0.9479 0.0890
-4.500 -0.1673 0.03595 0.02959 -0.0817 0.9435 0.0851
-4.250 -0.1396 0.03258 0.02571 -0.0828 0.9343 0.0841
-4.000 -0.0948 0.02946 0.02183 -0.0862 0.9296 0.0862
-3.750 -0.0651 0.02735 0.01936 -0.0869 0.9208 0.0903
-3.500 -0.0207 0.02574 0.01749 -0.0899 0.9156 0.0982
-3.250 0.0127 0.02434 0.01587 -0.0908 0.9076 0.1064
-3.000 0.0527 0.02314 0.01454 -0.0928 0.9012 0.1206
-2.750 0.0856 0.02224 0.01364 -0.0935 0.8932 0.1380
-2.500 0.1215 0.02140 0.01280 -0.0946 0.8858 0.1643
-2.250 0.1507 0.02072 0.01230 -0.0948 0.8771 0.1963
-2.000 0.1837 0.01985 0.01174 -0.0954 0.8697 0.2508
-1.750 0.2075 0.01881 0.01151 -0.0946 0.8602 0.3978
-1.500 0.2291 0.01761 0.01149 -0.0918 0.8533 0.7077
-1.250 0.2881 0.01690 0.01103 -0.0958 0.8469 1.0000
-1.000 0.3172 0.01692 0.01078 -0.0956 0.8379 1.0000
-0.750 0.3410 0.01711 0.01075 -0.0948 0.8269 1.0000
-0.500 0.3723 0.01702 0.01043 -0.0946 0.8200 1.0000
-0.250 0.3951 0.01724 0.01049 -0.0936 0.8080 1.0000
0.000 0.4204 0.01737 0.01047 -0.0928 0.7978 1.0000
0.250 0.4492 0.01730 0.01023 -0.0922 0.7898 1.0000
0.500 0.4730 0.01749 0.01032 -0.0913 0.7781 1.0000
0.750 0.4996 0.01754 0.01024 -0.0905 0.7686 1.0000
1.000 0.5269 0.01750 0.01009 -0.0897 0.7593 1.0000
1.250 0.5515 0.01767 0.01017 -0.0888 0.7477 1.0000
1.500 0.5786 0.01767 0.01007 -0.0880 0.7383 1.0000
1.750 0.6055 0.01765 0.00996 -0.0872 0.7282 1.0000
2.000 0.6305 0.01781 0.01007 -0.0864 0.7163 1.0000
2.250 0.6571 0.01785 0.01004 -0.0856 0.7058 1.0000
2.500 0.6851 0.01775 0.00985 -0.0849 0.6963 1.0000
2.750 0.7102 0.01791 0.00997 -0.0841 0.6836 1.0000
3.000 0.7361 0.01802 0.01006 -0.0833 0.6715 1.0000
3.250 0.7631 0.01803 0.01001 -0.0826 0.6603 1.0000
3.500 0.7910 0.01798 0.00987 -0.0819 0.6496 1.0000
3.750 0.8164 0.01813 0.01001 -0.0812 0.6361 1.0000
4.000 0.8421 0.01828 0.01016 -0.0804 0.6228 1.0000
4.250 0.8681 0.01841 0.01026 -0.0797 0.6094 1.0000
4.500 0.8943 0.01854 0.01036 -0.0790 0.5962 1.0000
4.750 0.9206 0.01866 0.01046 -0.0784 0.5827 1.0000
5.000 0.9469 0.01880 0.01056 -0.0777 0.5691 1.0000
5.250 0.9731 0.01896 0.01068 -0.0770 0.5549 1.0000
5.500 0.9989 0.01916 0.01086 -0.0763 0.5403 1.0000
5.750 1.0243 0.01939 0.01108 -0.0756 0.5252 1.0000
6.000 1.0493 0.01967 0.01134 -0.0749 0.5096 1.0000
6.250 1.0739 0.01998 0.01165 -0.0742 0.4937 1.0000
6.500 1.0981 0.02032 0.01201 -0.0734 0.4776 1.0000
6.750 1.1220 0.02070 0.01239 -0.0726 0.4613 1.0000
7.000 1.1455 0.02110 0.01280 -0.0718 0.4448 1.0000
7.250 1.1688 0.02153 0.01326 -0.0710 0.4284 1.0000
7.500 1.1917 0.02199 0.01373 -0.0701 0.4118 1.0000
7.750 1.2142 0.02248 0.01422 -0.0692 0.3953 1.0000
8.000 1.2363 0.02299 0.01475 -0.0682 0.3787 1.0000
8.250 1.2578 0.02352 0.01528 -0.0673 0.3621 1.0000
8.500 1.2788 0.02408 0.01582 -0.0662 0.3454 1.0000
8.750 1.2992 0.02469 0.01639 -0.0651 0.3288 1.0000
9.000 1.3174 0.02537 0.01713 -0.0638 0.3118 1.0000
9.250 1.3344 0.02609 0.01792 -0.0624 0.2947 1.0000
9.500 1.3504 0.02686 0.01874 -0.0609 0.2776 1.0000
9.750 1.3653 0.02768 0.01959 -0.0592 0.2608 1.0000
10.000 1.3787 0.02856 0.02050 -0.0574 0.2441 1.0000
10.250 1.3906 0.02952 0.02146 -0.0555 0.2278 1.0000
10.500 1.4004 0.03058 0.02250 -0.0534 0.2118 1.0000
10.750 1.4084 0.03176 0.02365 -0.0512 0.1964 1.0000
11.000 1.4132 0.03303 0.02491 -0.0486 0.1820 1.0000
11.250 1.4145 0.03440 0.02631 -0.0457 0.1689 1.0000
11.500 1.4160 0.03596 0.02795 -0.0432 0.1565 1.0000
11.750 1.4178 0.03771 0.02975 -0.0409 0.1451 1.0000
12.000 1.4202 0.03959 0.03164 -0.0390 0.1348 1.0000
12.250 1.4262 0.04149 0.03345 -0.0374 0.1252 1.0000
12.500 1.4264 0.04357 0.03568 -0.0357 0.1171 1.0000
12.750 1.4304 0.04584 0.03801 -0.0343 0.1094 1.0000
13.000 1.4363 0.04788 0.04002 -0.0332 0.1024 1.0000
13.250 1.4375 0.05056 0.04290 -0.0320 0.0967 1.0000
13.500 1.4413 0.05285 0.04526 -0.0310 0.0911 1.0000
13.750 1.4471 0.05564 0.04814 -0.0301 0.0860 1.0000
14.000 1.4421 0.05876 0.05152 -0.0293 0.0824 1.0000
14.250 1.4629 0.06095 0.05349 -0.0288 0.0765 1.0000
14.500 1.4497 0.06476 0.05769 -0.0282 0.0748 1.0000
14.750 1.4381 0.06882 0.06207 -0.0281 0.0728 1.0000
15.000 1.4280 0.07296 0.06645 -0.0284 0.0707 1.0000
15.250 1.4238 0.07656 0.07017 -0.0286 0.0682 1.0000
15.500 1.4334 0.08008 0.07365 -0.0283 0.0651 1.0000
15.750 1.4113 0.08576 0.07966 -0.0298 0.0647 1.0000
16.000 1.3877 0.09209 0.08629 -0.0320 0.0644 1.0000
16.250 1.3622 0.09918 0.09367 -0.0351 0.0643 1.0000
16.500 1.3344 0.10722 0.10197 -0.0392 0.0644 1.0000
16.750 1.3051 0.11625 0.11124 -0.0443 0.0647 1.0000
17.000 1.2740 0.12637 0.12155 -0.0505 0.0651 1.0000
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