SD7034 (sd7034-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7034 (sd7034-il) Reynolds number: 200,000 Max Cl/Cd: 76.25 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7034-il-200000-n5.txt Download as CSV file: xf-sd7034-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3345 0.08867 0.08523 -0.0353 1.0000 0.0163
-8.750 -0.3355 0.08446 0.08107 -0.0373 1.0000 0.0163
-8.500 -0.3385 0.08031 0.07699 -0.0394 1.0000 0.0166
-8.250 -0.3401 0.07466 0.07140 -0.0442 0.9837 0.0171
-8.000 -0.3352 0.06602 0.06277 -0.0554 0.9559 0.0173
-7.750 -0.3347 0.05402 0.05066 -0.0713 0.9315 0.0173
-7.500 -0.3648 0.03207 0.02747 -0.0860 0.9070 0.0172
-7.250 -0.3549 0.02620 0.02057 -0.0868 0.8963 0.0178
-7.000 -0.3338 0.02463 0.01881 -0.0866 0.8870 0.0183
-6.750 -0.3112 0.02331 0.01726 -0.0863 0.8790 0.0190
-6.500 -0.2882 0.02182 0.01546 -0.0859 0.8706 0.0200
-6.250 -0.2642 0.02040 0.01362 -0.0854 0.8629 0.0216
-6.000 -0.2397 0.01951 0.01262 -0.0851 0.8549 0.0230
-5.750 -0.2145 0.01874 0.01170 -0.0847 0.8475 0.0245
-5.500 -0.1891 0.01775 0.01045 -0.0842 0.8397 0.0261
-5.250 -0.1635 0.01697 0.00955 -0.0838 0.8325 0.0279
-5.000 -0.1372 0.01649 0.00900 -0.0835 0.8245 0.0302
-4.750 -0.1109 0.01586 0.00816 -0.0830 0.8175 0.0325
-4.500 -0.0845 0.01531 0.00761 -0.0828 0.8093 0.0352
-4.250 -0.0579 0.01488 0.00706 -0.0824 0.8023 0.0384
-4.000 -0.0312 0.01434 0.00646 -0.0822 0.7940 0.0414
-3.750 -0.0043 0.01399 0.00604 -0.0818 0.7869 0.0460
-3.500 0.0228 0.01357 0.00558 -0.0816 0.7784 0.0511
-3.250 0.0499 0.01326 0.00518 -0.0813 0.7713 0.0577
-3.000 0.0772 0.01293 0.00485 -0.0811 0.7627 0.0669
-2.750 0.1045 0.01265 0.00453 -0.0809 0.7553 0.0771
-2.500 0.1320 0.01241 0.00428 -0.0807 0.7467 0.0896
-2.250 0.1594 0.01219 0.00405 -0.0805 0.7391 0.1065
-2.000 0.1869 0.01196 0.00385 -0.0804 0.7304 0.1294
-1.750 0.2142 0.01171 0.00367 -0.0803 0.7225 0.1616
-1.500 0.2415 0.01143 0.00352 -0.0801 0.7137 0.2091
-1.250 0.2686 0.01114 0.00342 -0.0800 0.7051 0.2766
-1.000 0.2954 0.01084 0.00333 -0.0799 0.6964 0.3583
-0.750 0.3218 0.01053 0.00330 -0.0796 0.6872 0.4557
-0.500 0.3474 0.01025 0.00326 -0.0790 0.6786 0.5548
-0.250 0.3718 0.00994 0.00328 -0.0780 0.6687 0.6621
0.000 0.3933 0.00960 0.00329 -0.0760 0.6597 0.7917
0.250 0.4334 0.00931 0.00315 -0.0777 0.6495 0.9803
0.500 0.4626 0.00938 0.00310 -0.0779 0.6390 1.0000
0.750 0.4898 0.00947 0.00307 -0.0777 0.6290 1.0000
1.000 0.5171 0.00958 0.00306 -0.0775 0.6186 1.0000
1.250 0.5444 0.00968 0.00307 -0.0773 0.6076 1.0000
1.500 0.5717 0.00980 0.00309 -0.0771 0.5970 1.0000
1.750 0.5987 0.00993 0.00311 -0.0768 0.5862 1.0000
2.000 0.6259 0.01006 0.00317 -0.0766 0.5743 1.0000
2.250 0.6530 0.01020 0.00324 -0.0764 0.5626 1.0000
2.500 0.6800 0.01035 0.00331 -0.0762 0.5507 1.0000
2.750 0.7068 0.01051 0.00339 -0.0759 0.5388 1.0000
3.000 0.7335 0.01068 0.00350 -0.0757 0.5261 1.0000
3.250 0.7603 0.01085 0.00362 -0.0754 0.5133 1.0000
3.500 0.7869 0.01104 0.00375 -0.0752 0.5006 1.0000
3.750 0.8133 0.01124 0.00391 -0.0749 0.4877 1.0000
4.000 0.8395 0.01146 0.00407 -0.0746 0.4747 1.0000
4.250 0.8656 0.01169 0.00425 -0.0743 0.4612 1.0000
4.500 0.8914 0.01194 0.00445 -0.0740 0.4476 1.0000
4.750 0.9171 0.01219 0.00467 -0.0736 0.4336 1.0000
5.000 0.9427 0.01246 0.00490 -0.0733 0.4193 1.0000
5.250 0.9680 0.01274 0.00516 -0.0729 0.4052 1.0000
5.500 0.9930 0.01304 0.00543 -0.0725 0.3908 1.0000
5.750 1.0179 0.01335 0.00572 -0.0721 0.3764 1.0000
6.000 1.0424 0.01369 0.00603 -0.0716 0.3621 1.0000
6.250 1.0666 0.01404 0.00637 -0.0711 0.3475 1.0000
6.500 1.0906 0.01441 0.00672 -0.0706 0.3333 1.0000
6.750 1.1141 0.01480 0.00709 -0.0700 0.3190 1.0000
7.000 1.1373 0.01521 0.00750 -0.0694 0.3049 1.0000
7.250 1.1600 0.01565 0.00792 -0.0687 0.2905 1.0000
7.500 1.1822 0.01611 0.00836 -0.0680 0.2760 1.0000
7.750 1.2039 0.01660 0.00885 -0.0673 0.2614 1.0000
8.000 1.2250 0.01712 0.00935 -0.0664 0.2467 1.0000
8.250 1.2455 0.01765 0.00988 -0.0655 0.2324 1.0000
8.500 1.2654 0.01822 0.01044 -0.0646 0.2184 1.0000
8.750 1.2845 0.01882 0.01104 -0.0635 0.2046 1.0000
9.000 1.3026 0.01946 0.01167 -0.0624 0.1910 1.0000
9.250 1.3198 0.02013 0.01234 -0.0611 0.1781 1.0000
9.500 1.3357 0.02085 0.01306 -0.0597 0.1649 1.0000
9.750 1.3503 0.02160 0.01382 -0.0581 0.1524 1.0000
10.000 1.3622 0.02238 0.01462 -0.0561 0.1401 1.0000
10.250 1.3728 0.02326 0.01550 -0.0541 0.1283 1.0000
10.500 1.3826 0.02423 0.01648 -0.0521 0.1174 1.0000
10.750 1.3912 0.02532 0.01758 -0.0502 0.1071 1.0000
11.000 1.3986 0.02655 0.01881 -0.0484 0.0978 1.0000
11.250 1.4058 0.02785 0.02015 -0.0467 0.0887 1.0000
11.500 1.4130 0.02922 0.02157 -0.0452 0.0810 1.0000
11.750 1.4178 0.03083 0.02320 -0.0437 0.0744 1.0000
12.000 1.4239 0.03243 0.02486 -0.0424 0.0683 1.0000
12.250 1.4274 0.03430 0.02678 -0.0412 0.0632 1.0000
12.500 1.4321 0.03615 0.02872 -0.0402 0.0585 1.0000
12.750 1.4334 0.03840 0.03103 -0.0393 0.0548 1.0000
13.000 1.4367 0.04053 0.03327 -0.0386 0.0513 1.0000
13.250 1.4382 0.04293 0.03575 -0.0380 0.0479 1.0000
13.500 1.4362 0.04579 0.03867 -0.0376 0.0454 1.0000
13.750 1.4373 0.04839 0.04141 -0.0374 0.0431 1.0000
14.000 1.4374 0.05123 0.04437 -0.0373 0.0408 1.0000
14.250 1.4347 0.05447 0.04772 -0.0375 0.0390 1.0000
14.500 1.4292 0.05821 0.05153 -0.0380 0.0374 1.0000
14.750 1.4266 0.06173 0.05518 -0.0385 0.0359 1.0000
15.000 1.4240 0.06535 0.05897 -0.0392 0.0345 1.0000
15.250 1.4205 0.06924 0.06298 -0.0401 0.0331 1.0000
15.500 1.4148 0.07356 0.06742 -0.0414 0.0319 1.0000
15.750 1.4074 0.07827 0.07223 -0.0429 0.0308 1.0000
16.000 1.3993 0.08321 0.07725 -0.0446 0.0299 1.0000
16.250 1.3953 0.08764 0.08185 -0.0462 0.0289 1.0000
16.500 1.3899 0.09236 0.08672 -0.0479 0.0279 1.0000
16.750 1.3839 0.09730 0.09179 -0.0499 0.0270 1.0000
17.000 1.3774 0.10241 0.09702 -0.0521 0.0262 1.0000
17.250 1.3702 0.10774 0.10246 -0.0545 0.0255 1.0000
17.500 1.3624 0.11320 0.10801 -0.0570 0.0249 1.0000
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