SD7034 (sd7034-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7034 (sd7034-il) Reynolds number: 500,000 Max Cl/Cd: 107.41 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7034-il-500000.txt Download as CSV file: xf-sd7034-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3362 0.09604 0.09383 -0.0338 1.0000 0.0229
-9.250 -0.3359 0.09153 0.08936 -0.0366 1.0000 0.0230
-9.000 -0.3342 0.08788 0.08575 -0.0370 1.0000 0.0234
-8.750 -0.3251 0.08606 0.08395 -0.0370 1.0000 0.0238
-8.500 -0.3181 0.08383 0.08176 -0.0375 1.0000 0.0243
-8.250 -0.3131 0.08065 0.07862 -0.0395 0.9932 0.0247
-8.000 -0.2923 0.07562 0.07357 -0.0470 0.9733 0.0257
-7.750 -0.3518 0.04257 0.04012 -0.0795 0.9177 0.0186
-7.500 -0.3515 0.03740 0.03470 -0.0816 0.9035 0.0180
-7.250 -0.3645 0.02477 0.02084 -0.0845 0.8896 0.0171
-7.000 -0.3477 0.02119 0.01664 -0.0841 0.8815 0.0175
-6.750 -0.3252 0.01912 0.01414 -0.0838 0.8730 0.0181
-6.500 -0.3008 0.01797 0.01263 -0.0832 0.8660 0.0186
-6.250 -0.2773 0.01606 0.01051 -0.0830 0.8579 0.0195
-6.000 -0.2516 0.01564 0.01001 -0.0826 0.8512 0.0207
-5.750 -0.2247 0.01501 0.00926 -0.0824 0.8432 0.0220
-5.500 -0.1980 0.01449 0.00852 -0.0820 0.8364 0.0230
-5.250 -0.1724 0.01323 0.00720 -0.0817 0.8286 0.0245
-5.000 -0.1456 0.01278 0.00666 -0.0814 0.8216 0.0261
-4.750 -0.1180 0.01240 0.00618 -0.0812 0.8140 0.0279
-4.500 -0.0915 0.01171 0.00544 -0.0810 0.8067 0.0303
-4.250 -0.0638 0.01140 0.00508 -0.0808 0.7993 0.0328
-4.000 -0.0365 0.01093 0.00452 -0.0805 0.7918 0.0353
-3.750 -0.0089 0.01063 0.00420 -0.0804 0.7845 0.0390
-3.500 0.0189 0.01032 0.00382 -0.0802 0.7767 0.0427
-3.250 0.0467 0.01003 0.00353 -0.0801 0.7694 0.0487
-3.000 0.0746 0.00972 0.00320 -0.0800 0.7614 0.0570
-2.750 0.1026 0.00947 0.00294 -0.0799 0.7540 0.0685
-2.500 0.1306 0.00926 0.00274 -0.0798 0.7457 0.0813
-2.250 0.1587 0.00909 0.00256 -0.0797 0.7380 0.0951
-2.000 0.1867 0.00891 0.00240 -0.0796 0.7295 0.1133
-1.750 0.2148 0.00870 0.00226 -0.0796 0.7213 0.1426
-1.250 0.2701 0.00809 0.00207 -0.0797 0.7041 0.2869
-1.000 0.2973 0.00776 0.00201 -0.0796 0.6957 0.3927
-0.750 0.3246 0.00745 0.00200 -0.0795 0.6863 0.4977
-0.500 0.3512 0.00718 0.00200 -0.0792 0.6777 0.6017
-0.250 0.3769 0.00689 0.00201 -0.0786 0.6682 0.7103
0.000 0.4001 0.00660 0.00204 -0.0772 0.6592 0.8225
0.250 0.4333 0.00635 0.00197 -0.0777 0.6498 0.9735
0.500 0.4664 0.00639 0.00193 -0.0787 0.6394 1.0000
0.750 0.4942 0.00647 0.00192 -0.0786 0.6295 1.0000
1.000 0.5219 0.00657 0.00192 -0.0784 0.6193 1.0000
1.250 0.5498 0.00665 0.00193 -0.0784 0.6084 1.0000
1.500 0.5776 0.00674 0.00195 -0.0783 0.5978 1.0000
1.750 0.6052 0.00686 0.00198 -0.0781 0.5871 1.0000
2.000 0.6330 0.00696 0.00202 -0.0780 0.5755 1.0000
2.250 0.6607 0.00707 0.00208 -0.0779 0.5641 1.0000
2.500 0.6883 0.00720 0.00214 -0.0778 0.5526 1.0000
2.750 0.7157 0.00734 0.00221 -0.0777 0.5408 1.0000
3.000 0.7432 0.00747 0.00229 -0.0776 0.5282 1.0000
3.250 0.7707 0.00761 0.00238 -0.0775 0.5157 1.0000
3.500 0.7980 0.00776 0.00248 -0.0774 0.5029 1.0000
3.750 0.8251 0.00793 0.00260 -0.0772 0.4898 1.0000
4.000 0.8521 0.00811 0.00273 -0.0771 0.4765 1.0000
4.250 0.8789 0.00830 0.00286 -0.0769 0.4626 1.0000
4.500 0.9056 0.00850 0.00301 -0.0767 0.4486 1.0000
4.750 0.9322 0.00872 0.00318 -0.0765 0.4342 1.0000
5.000 0.9586 0.00894 0.00335 -0.0763 0.4197 1.0000
5.250 0.9849 0.00917 0.00354 -0.0761 0.4049 1.0000
5.500 1.0110 0.00942 0.00375 -0.0758 0.3900 1.0000
5.750 1.0369 0.00968 0.00396 -0.0756 0.3751 1.0000
6.000 1.0626 0.00996 0.00420 -0.0753 0.3598 1.0000
6.250 1.0881 0.01025 0.00445 -0.0750 0.3446 1.0000
6.500 1.1132 0.01056 0.00471 -0.0746 0.3290 1.0000
6.750 1.1380 0.01090 0.00500 -0.0743 0.3131 1.0000
7.000 1.1626 0.01124 0.00530 -0.0739 0.2976 1.0000
7.250 1.1870 0.01159 0.00561 -0.0734 0.2822 1.0000
7.500 1.2110 0.01197 0.00595 -0.0730 0.2675 1.0000
7.750 1.2347 0.01236 0.00630 -0.0725 0.2530 1.0000
8.000 1.2581 0.01276 0.00667 -0.0719 0.2388 1.0000
8.500 1.3036 0.01363 0.00747 -0.0707 0.2105 1.0000
8.750 1.3256 0.01410 0.00791 -0.0700 0.1964 1.0000
9.000 1.3468 0.01460 0.00838 -0.0692 0.1820 1.0000
9.500 1.3869 0.01572 0.00941 -0.0672 0.1530 1.0000
9.750 1.4056 0.01633 0.00998 -0.0661 0.1386 1.0000
10.000 1.4230 0.01699 0.01060 -0.0648 0.1241 1.0000
10.250 1.4388 0.01771 0.01128 -0.0633 0.1106 1.0000
10.500 1.4522 0.01848 0.01200 -0.0615 0.0978 1.0000
10.750 1.4619 0.01930 0.01278 -0.0590 0.0869 1.0000
11.250 1.4793 0.02113 0.01460 -0.0544 0.0693 1.0000
11.500 1.4875 0.02217 0.01565 -0.0523 0.0627 1.0000
11.750 1.4941 0.02338 0.01686 -0.0503 0.0569 1.0000
12.000 1.5021 0.02456 0.01809 -0.0485 0.0522 1.0000
12.250 1.5080 0.02594 0.01949 -0.0468 0.0481 1.0000
12.500 1.5129 0.02749 0.02110 -0.0451 0.0446 1.0000
12.750 1.5199 0.02894 0.02262 -0.0438 0.0416 1.0000
13.000 1.5219 0.03088 0.02459 -0.0424 0.0387 1.0000
13.250 1.5248 0.03283 0.02663 -0.0412 0.0365 1.0000
13.500 1.5306 0.03460 0.02849 -0.0403 0.0343 1.0000
13.750 1.5318 0.03688 0.03081 -0.0395 0.0323 1.0000
14.000 1.5252 0.04005 0.03405 -0.0387 0.0305 1.0000
14.250 1.5299 0.04219 0.03631 -0.0382 0.0292 1.0000
14.500 1.5322 0.04464 0.03887 -0.0380 0.0277 1.0000
14.750 1.5309 0.04758 0.04189 -0.0379 0.0265 1.0000
15.000 1.5254 0.05117 0.04555 -0.0381 0.0254 1.0000
15.250 1.5135 0.05570 0.05018 -0.0386 0.0244 1.0000
15.500 1.5149 0.05873 0.05334 -0.0391 0.0236 1.0000
15.750 1.5135 0.06222 0.05695 -0.0398 0.0227 1.0000
16.000 1.5105 0.06604 0.06087 -0.0407 0.0218 1.0000
16.250 1.5050 0.07034 0.06526 -0.0419 0.0212 1.0000
16.500 1.4964 0.07524 0.07025 -0.0435 0.0205 1.0000
16.750 1.4839 0.08084 0.07594 -0.0454 0.0199 1.0000
17.000 1.4725 0.08640 0.08162 -0.0474 0.0194 1.0000
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