SA7035 (sa7035-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7035 (sa7035-il) Reynolds number: 500,000 Max Cl/Cd: 94.89 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7035-il-500000.txt Download as CSV file: xf-sa7035-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: SA7035
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4020 0.08318 0.08099 -0.0322 1.0000 0.0166
-8.250 -0.4023 0.07944 0.07728 -0.0342 1.0000 0.0168
-8.000 -0.4046 0.07564 0.07353 -0.0360 1.0000 0.0170
-7.750 -0.4138 0.07225 0.07019 -0.0369 1.0000 0.0170
-7.500 -0.4275 0.06889 0.06689 -0.0377 1.0000 0.0170
-7.250 -0.4420 0.06551 0.06353 -0.0378 1.0000 0.0169
-7.000 -0.4366 0.05893 0.05684 -0.0435 0.9982 0.0172
-6.750 -0.4112 0.05128 0.04892 -0.0524 0.9940 0.0173
-6.500 -0.3997 0.04041 0.03760 -0.0604 0.9873 0.0180
-6.250 -0.3720 0.03689 0.03396 -0.0641 0.9846 0.0187
-6.000 -0.3435 0.03400 0.03090 -0.0670 0.9811 0.0197
-5.750 -0.3148 0.03077 0.02739 -0.0692 0.9767 0.0214
-5.500 -0.2753 0.03039 0.02660 -0.0708 0.9742 0.0247
-5.250 -0.2496 0.01793 0.01277 -0.0717 0.9709 0.0123
-5.000 -0.2218 0.01584 0.01039 -0.0717 0.9656 0.0124
-4.750 -0.1916 0.01419 0.00854 -0.0722 0.9612 0.0126
-4.500 -0.1599 0.01303 0.00729 -0.0730 0.9575 0.0134
-4.250 -0.1341 0.01252 0.00676 -0.0726 0.9503 0.0148
-4.000 -0.1065 0.01167 0.00582 -0.0722 0.9444 0.0153
-3.750 -0.0820 0.01094 0.00499 -0.0713 0.9365 0.0157
-3.500 -0.0562 0.01032 0.00428 -0.0705 0.9297 0.0164
-3.250 -0.0313 0.00978 0.00364 -0.0696 0.9212 0.0179
-3.000 -0.0055 0.00926 0.00305 -0.0689 0.9142 0.0241
-2.750 0.0185 0.00839 0.00260 -0.0682 0.9046 0.1227
-2.500 0.0436 0.00789 0.00239 -0.0677 0.8957 0.2123
-2.250 0.0683 0.00728 0.00221 -0.0672 0.8868 0.3437
-2.000 0.0927 0.00672 0.00210 -0.0666 0.8758 0.4831
-1.750 0.1182 0.00642 0.00200 -0.0660 0.8649 0.5656
-1.500 0.1436 0.00617 0.00192 -0.0653 0.8535 0.6417
-1.250 0.1690 0.00597 0.00185 -0.0645 0.8416 0.7029
-1.000 0.1938 0.00579 0.00180 -0.0635 0.8287 0.7648
-0.750 0.2176 0.00563 0.00177 -0.0622 0.8149 0.8256
-0.500 0.2403 0.00552 0.00174 -0.0606 0.8001 0.8815
-0.250 0.2651 0.00548 0.00170 -0.0593 0.7842 0.9310
0.000 0.2997 0.00549 0.00163 -0.0604 0.7671 0.9665
0.250 0.3412 0.00552 0.00154 -0.0632 0.7491 0.9883
0.500 0.3802 0.00558 0.00147 -0.0656 0.7308 1.0000
0.750 0.4044 0.00567 0.00146 -0.0648 0.7117 1.0000
1.000 0.4290 0.00578 0.00146 -0.0641 0.6927 1.0000
1.250 0.4539 0.00591 0.00147 -0.0635 0.6734 1.0000
1.500 0.4794 0.00603 0.00150 -0.0629 0.6534 1.0000
1.750 0.5048 0.00618 0.00153 -0.0624 0.6328 1.0000
2.000 0.5305 0.00633 0.00158 -0.0620 0.6110 1.0000
2.500 0.5822 0.00665 0.00173 -0.0612 0.5692 1.0000
2.750 0.6082 0.00683 0.00181 -0.0608 0.5488 1.0000
3.000 0.6343 0.00701 0.00191 -0.0604 0.5276 1.0000
3.250 0.6602 0.00721 0.00204 -0.0601 0.5064 1.0000
3.500 0.6862 0.00741 0.00216 -0.0598 0.4848 1.0000
4.000 0.7379 0.00785 0.00244 -0.0591 0.4397 1.0000
4.250 0.7636 0.00810 0.00262 -0.0588 0.4185 1.0000
4.500 0.7894 0.00834 0.00279 -0.0585 0.3963 1.0000
4.750 0.8150 0.00860 0.00299 -0.0581 0.3753 1.0000
5.000 0.8407 0.00886 0.00319 -0.0578 0.3544 1.0000
5.250 0.8660 0.00916 0.00343 -0.0575 0.3321 1.0000
5.500 0.8911 0.00948 0.00367 -0.0571 0.3087 1.0000
5.750 0.9161 0.00981 0.00393 -0.0567 0.2843 1.0000
6.000 0.9408 0.01017 0.00421 -0.0563 0.2609 1.0000
6.250 0.9653 0.01055 0.00453 -0.0559 0.2387 1.0000
6.500 0.9900 0.01092 0.00485 -0.0555 0.2182 1.0000
7.000 1.0381 0.01176 0.00557 -0.0545 0.1762 1.0000
7.500 1.0845 0.01276 0.00642 -0.0534 0.1326 1.0000
7.750 1.1070 0.01332 0.00689 -0.0527 0.1114 1.0000
8.000 1.1292 0.01391 0.00740 -0.0520 0.0923 1.0000
8.250 1.1507 0.01454 0.00797 -0.0513 0.0742 1.0000
8.500 1.1716 0.01523 0.00859 -0.0504 0.0577 1.0000
8.750 1.1919 0.01596 0.00929 -0.0494 0.0452 1.0000
9.000 1.2118 0.01671 0.01003 -0.0484 0.0356 1.0000
9.250 1.2309 0.01751 0.01084 -0.0473 0.0275 1.0000
9.500 1.2478 0.01849 0.01186 -0.0458 0.0212 1.0000
9.750 1.2637 0.01949 0.01288 -0.0442 0.0168 1.0000
10.000 1.2804 0.02037 0.01385 -0.0428 0.0144 1.0000
10.250 1.2961 0.02126 0.01481 -0.0412 0.0125 1.0000
10.500 1.3013 0.02289 0.01655 -0.0383 0.0110 1.0000
10.750 1.3093 0.02398 0.01777 -0.0355 0.0103 1.0000
11.000 1.3176 0.02503 0.01897 -0.0330 0.0094 1.0000
11.250 1.3240 0.02623 0.02026 -0.0305 0.0088 1.0000
11.500 1.3294 0.02754 0.02165 -0.0281 0.0082 1.0000
11.750 1.3301 0.02926 0.02347 -0.0256 0.0077 1.0000
12.000 1.3187 0.03215 0.02653 -0.0225 0.0071 1.0000
12.250 1.3242 0.03376 0.02828 -0.0211 0.0068 1.0000
12.500 1.3279 0.03561 0.03026 -0.0199 0.0065 1.0000
12.750 1.3285 0.03788 0.03267 -0.0188 0.0062 1.0000
13.000 1.3251 0.04075 0.03569 -0.0179 0.0060 1.0000
13.250 1.3227 0.04368 0.03877 -0.0176 0.0059 1.0000
13.500 1.3190 0.04694 0.04218 -0.0176 0.0057 1.0000
13.750 1.3135 0.05064 0.04603 -0.0180 0.0056 1.0000
14.000 1.3101 0.05422 0.04973 -0.0189 0.0054 1.0000
14.250 1.3035 0.05848 0.05413 -0.0202 0.0053 1.0000
14.500 1.2955 0.06315 0.05895 -0.0218 0.0052 1.0000
14.750 1.2859 0.06829 0.06424 -0.0239 0.0052 1.0000
15.000 1.2749 0.07392 0.07002 -0.0264 0.0051 1.0000
15.250 1.2656 0.07949 0.07572 -0.0292 0.0050 1.0000
15.500 1.2526 0.08597 0.08235 -0.0324 0.0050 1.0000
15.750 1.2394 0.09276 0.08929 -0.0360 0.0049 1.0000
16.000 1.2260 0.09985 0.09654 -0.0398 0.0050 1.0000
16.250 1.2123 0.10727 0.10411 -0.0439 0.0050 1.0000
16.500 1.1988 0.11486 0.11183 -0.0483 0.0049 1.0000
16.750 1.1827 0.12341 0.12058 -0.0532 0.0051 1.0000
17.000 1.1696 0.13143 0.12871 -0.0580 0.0050 1.0000
17.250 1.1548 0.14016 0.13758 -0.0632 0.0050 1.0000
17.500 1.1391 0.14944 0.14701 -0.0688 0.0050 1.0000
17.750 1.1103 0.16319 0.16099 -0.0771 0.0053 1.0000
18.000 1.0050 0.20813 0.20613 -0.1004 0.0070 1.0000
18.250 1.0031 0.21601 0.21399 -0.1042 0.0072 1.0000
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