SD7034 (sd7034-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7034 (sd7034-il) Reynolds number: 200,000 Max Cl/Cd: 77.81 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7034-il-200000.txt Download as CSV file: xf-sd7034-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3256 0.09119 0.08797 -0.0423 1.0000 0.0507
-8.250 -0.3388 0.08881 0.08572 -0.0433 1.0000 0.0508
-8.000 -0.3700 0.08913 0.08617 -0.0376 1.0000 0.0508
-7.750 -0.3592 0.08401 0.08107 -0.0374 0.9972 0.0517
-7.500 -0.3337 0.08094 0.07798 -0.0373 0.9941 0.0531
-7.250 -0.3097 0.07701 0.07404 -0.0425 0.9867 0.0551
-7.000 -0.2818 0.07054 0.06754 -0.0557 0.9773 0.0594
-6.750 -0.2534 0.05881 0.05559 -0.0781 0.9662 0.0630
-6.500 -0.2273 0.05776 0.05461 -0.0767 0.9616 0.0655
-6.250 -0.2009 0.05306 0.04979 -0.0834 0.9527 0.0695
-6.000 -0.1961 0.03196 0.02691 -0.0963 0.9355 0.0421
-5.750 -0.1718 0.02822 0.02278 -0.0970 0.9286 0.0412
-5.250 -0.1292 0.02353 0.01746 -0.0960 0.9100 0.0444
-5.000 -0.1055 0.02201 0.01566 -0.0952 0.9014 0.0462
-4.750 -0.0812 0.02042 0.01371 -0.0943 0.8930 0.0481
-4.500 -0.0560 0.01942 0.01233 -0.0933 0.8851 0.0512
-4.250 -0.0319 0.01814 0.01102 -0.0926 0.8766 0.0548
-4.000 -0.0065 0.01736 0.01008 -0.0917 0.8691 0.0588
-3.750 0.0188 0.01644 0.00904 -0.0909 0.8605 0.0640
-3.500 0.0442 0.01579 0.00836 -0.0900 0.8532 0.0699
-3.250 0.0696 0.01510 0.00764 -0.0893 0.8445 0.0783
-3.000 0.0954 0.01452 0.00699 -0.0885 0.8373 0.0893
-2.750 0.1212 0.01402 0.00654 -0.0880 0.8284 0.1046
-2.500 0.1471 0.01355 0.00609 -0.0873 0.8213 0.1229
-2.250 0.1735 0.01320 0.00577 -0.0868 0.8122 0.1472
-2.000 0.1994 0.01268 0.00541 -0.0863 0.8051 0.1859
-1.750 0.2249 0.01206 0.00521 -0.0860 0.7957 0.2815
-1.500 0.2491 0.01134 0.00507 -0.0852 0.7888 0.4551
-1.250 0.2718 0.01083 0.00509 -0.0840 0.7790 0.6133
-1.000 0.2920 0.01035 0.00503 -0.0815 0.7718 0.7573
-0.750 0.3241 0.00994 0.00489 -0.0810 0.7624 0.9368
-0.500 0.3647 0.00987 0.00464 -0.0833 0.7540 1.0000
-0.250 0.3913 0.00990 0.00452 -0.0829 0.7446 1.0000
0.000 0.4180 0.00997 0.00445 -0.0825 0.7349 1.0000
0.250 0.4450 0.01001 0.00431 -0.0820 0.7266 1.0000
0.500 0.4719 0.01008 0.00430 -0.0817 0.7158 1.0000
0.750 0.4989 0.01015 0.00425 -0.0813 0.7063 1.0000
1.000 0.5261 0.01021 0.00418 -0.0810 0.6967 1.0000
1.250 0.5531 0.01029 0.00420 -0.0807 0.6858 1.0000
1.500 0.5803 0.01038 0.00418 -0.0803 0.6758 1.0000
1.750 0.6075 0.01046 0.00415 -0.0800 0.6655 1.0000
2.000 0.6345 0.01056 0.00420 -0.0797 0.6539 1.0000
2.250 0.6615 0.01067 0.00424 -0.0793 0.6427 1.0000
2.500 0.6887 0.01078 0.00425 -0.0790 0.6321 1.0000
2.750 0.7156 0.01089 0.00430 -0.0787 0.6200 1.0000
3.000 0.7424 0.01102 0.00440 -0.0784 0.6076 1.0000
3.250 0.7692 0.01116 0.00449 -0.0781 0.5953 1.0000
3.500 0.7960 0.01131 0.00458 -0.0777 0.5832 1.0000
3.750 0.8227 0.01148 0.00466 -0.0774 0.5707 1.0000
4.000 0.8492 0.01165 0.00480 -0.0770 0.5576 1.0000
4.250 0.8755 0.01182 0.00495 -0.0767 0.5437 1.0000
4.500 0.9016 0.01202 0.00512 -0.0763 0.5297 1.0000
4.750 0.9276 0.01223 0.00531 -0.0759 0.5154 1.0000
5.000 0.9534 0.01246 0.00550 -0.0755 0.5009 1.0000
5.250 0.9790 0.01270 0.00571 -0.0751 0.4860 1.0000
5.500 1.0044 0.01297 0.00596 -0.0747 0.4710 1.0000
5.750 1.0295 0.01325 0.00621 -0.0742 0.4556 1.0000
6.000 1.0543 0.01355 0.00648 -0.0737 0.4401 1.0000
6.250 1.0788 0.01388 0.00679 -0.0732 0.4244 1.0000
6.500 1.1031 0.01422 0.00711 -0.0726 0.4087 1.0000
6.750 1.1269 0.01459 0.00746 -0.0720 0.3930 1.0000
7.000 1.1504 0.01498 0.00783 -0.0714 0.3771 1.0000
7.250 1.1734 0.01540 0.00823 -0.0707 0.3612 1.0000
7.500 1.1959 0.01584 0.00864 -0.0699 0.3453 1.0000
7.750 1.2179 0.01630 0.00909 -0.0692 0.3294 1.0000
8.000 1.2393 0.01680 0.00957 -0.0683 0.3136 1.0000
8.250 1.2602 0.01731 0.01007 -0.0674 0.2980 1.0000
8.500 1.2805 0.01784 0.01061 -0.0664 0.2825 1.0000
8.750 1.3001 0.01841 0.01118 -0.0654 0.2673 1.0000
9.000 1.3189 0.01900 0.01180 -0.0642 0.2522 1.0000
9.250 1.3367 0.01963 0.01244 -0.0630 0.2372 1.0000
9.500 1.3533 0.02030 0.01313 -0.0616 0.2223 1.0000
9.750 1.3686 0.02102 0.01386 -0.0600 0.2074 1.0000
10.000 1.3820 0.02179 0.01466 -0.0583 0.1924 1.0000
10.250 1.3922 0.02263 0.01550 -0.0561 0.1783 1.0000
10.500 1.4000 0.02357 0.01644 -0.0536 0.1643 1.0000
10.750 1.4066 0.02466 0.01752 -0.0513 0.1506 1.0000
11.000 1.4118 0.02593 0.01877 -0.0491 0.1376 1.0000
11.250 1.4154 0.02739 0.02021 -0.0469 0.1254 1.0000
11.500 1.4186 0.02900 0.02182 -0.0450 0.1142 1.0000
11.750 1.4227 0.03065 0.02352 -0.0433 0.1039 1.0000
12.000 1.4249 0.03255 0.02545 -0.0417 0.0953 1.0000
12.250 1.4231 0.03486 0.02770 -0.0402 0.0885 1.0000
12.500 1.4280 0.03674 0.02971 -0.0391 0.0817 1.0000
12.750 1.4247 0.03942 0.03232 -0.0379 0.0765 1.0000
13.000 1.4291 0.04149 0.03457 -0.0371 0.0713 1.0000
13.250 1.4282 0.04413 0.03722 -0.0365 0.0672 1.0000
13.500 1.4280 0.04681 0.03999 -0.0357 0.0634 1.0000
13.750 1.4293 0.04942 0.04272 -0.0354 0.0597 1.0000
14.000 1.4281 0.05233 0.04565 -0.0352 0.0567 1.0000
14.250 1.4279 0.05526 0.04864 -0.0347 0.0539 1.0000
14.500 1.4283 0.05820 0.05175 -0.0347 0.0513 1.0000
14.750 1.4281 0.06126 0.05490 -0.0349 0.0489 1.0000
15.000 1.4279 0.06436 0.05797 -0.0349 0.0465 1.0000
15.250 1.4285 0.06754 0.06129 -0.0349 0.0445 1.0000
15.500 1.4269 0.07109 0.06503 -0.0355 0.0428 1.0000
15.750 1.4259 0.07461 0.06869 -0.0362 0.0410 1.0000
16.000 1.4257 0.07804 0.07218 -0.0369 0.0395 1.0000
16.250 1.4298 0.08084 0.07493 -0.0364 0.0374 1.0000
16.500 1.4234 0.08545 0.07979 -0.0381 0.0366 1.0000
16.750 1.4176 0.09008 0.08464 -0.0398 0.0355 1.0000
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