SA7036 (sa7036-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7036 (sa7036-il) Reynolds number: 100,000 Max Cl/Cd: 53.92 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7036-il-100000.txt Download as CSV file: xf-sa7036-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SA7036
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3817 0.09983 0.09496 -0.0275 1.0000 0.0887
-8.500 -0.3925 0.09759 0.09282 -0.0312 1.0000 0.0918
-8.250 -0.4125 0.09584 0.09123 -0.0354 1.0000 0.0926
-8.000 -0.3893 0.09032 0.08569 -0.0315 1.0000 0.0955
-7.750 -0.3821 0.08751 0.08292 -0.0303 1.0000 0.0989
-7.500 -0.3877 0.08507 0.08057 -0.0303 1.0000 0.1022
-7.250 -0.4086 0.08285 0.07850 -0.0328 1.0000 0.1053
-7.000 -0.4368 0.08011 0.07573 -0.0413 1.0000 0.1067
-6.750 -0.4183 0.07619 0.07198 -0.0332 1.0000 0.1094
-6.500 -0.4154 0.07385 0.06969 -0.0307 1.0000 0.1128
-6.000 -0.4289 0.06685 0.06265 -0.0353 1.0000 0.1226
-5.750 -0.4229 0.06462 0.06050 -0.0318 1.0000 0.1263
-5.500 -0.4238 0.06073 0.05643 -0.0356 1.0000 0.1364
-5.250 -0.4163 0.05841 0.05422 -0.0323 1.0000 0.1407
-5.000 -0.4101 0.05516 0.05086 -0.0334 1.0000 0.1523
-4.750 -0.4016 0.05252 0.04818 -0.0330 1.0000 0.1664
-4.500 -0.3918 0.05009 0.04569 -0.0321 1.0000 0.1813
-4.250 -0.3406 0.03602 0.02964 -0.0414 1.0000 0.0780
-4.000 -0.3144 0.03141 0.02430 -0.0412 1.0000 0.0646
-3.750 -0.2908 0.02825 0.02078 -0.0410 1.0000 0.0617
-3.500 -0.2651 0.02579 0.01785 -0.0406 1.0000 0.0598
-3.250 -0.2397 0.02391 0.01556 -0.0400 1.0000 0.0599
-3.000 -0.2162 0.02283 0.01417 -0.0392 1.0000 0.0640
-2.750 -0.1925 0.02141 0.01259 -0.0385 1.0000 0.0677
-2.500 -0.1699 0.02037 0.01156 -0.0378 1.0000 0.0727
-2.250 -0.1276 0.01935 0.01054 -0.0406 0.9941 0.0899
-2.000 -0.0870 0.01716 0.00934 -0.0433 0.9876 0.2367
-1.750 -0.0591 0.01546 0.00981 -0.0427 0.9810 0.7301
-1.500 -0.0040 0.01519 0.00964 -0.0468 0.9727 1.0000
-1.250 0.0412 0.01549 0.00955 -0.0507 0.9619 1.0000
-1.000 0.0865 0.01577 0.00952 -0.0545 0.9514 1.0000
-0.750 0.1371 0.01602 0.00949 -0.0591 0.9427 1.0000
-0.500 0.1778 0.01615 0.00943 -0.0618 0.9305 1.0000
-0.250 0.2191 0.01625 0.00936 -0.0645 0.9186 1.0000
0.000 0.2623 0.01628 0.00925 -0.0674 0.9073 1.0000
0.250 0.3171 0.01614 0.00900 -0.0722 0.8999 1.0000
0.500 0.3551 0.01605 0.00881 -0.0738 0.8871 1.0000
0.750 0.3918 0.01592 0.00862 -0.0750 0.8742 1.0000
1.000 0.4270 0.01576 0.00841 -0.0758 0.8612 1.0000
1.250 0.4609 0.01558 0.00819 -0.0762 0.8478 1.0000
1.500 0.4932 0.01537 0.00794 -0.0763 0.8339 1.0000
1.750 0.5241 0.01517 0.00770 -0.0760 0.8193 1.0000
2.000 0.5539 0.01497 0.00747 -0.0754 0.8041 1.0000
2.250 0.5830 0.01478 0.00726 -0.0747 0.7883 1.0000
2.500 0.6104 0.01467 0.00710 -0.0738 0.7707 1.0000
2.750 0.6362 0.01464 0.00705 -0.0727 0.7510 1.0000
3.000 0.6634 0.01459 0.00693 -0.0717 0.7322 1.0000
3.250 0.6891 0.01464 0.00697 -0.0707 0.7112 1.0000
3.500 0.7151 0.01471 0.00697 -0.0697 0.6898 1.0000
3.750 0.7401 0.01485 0.00706 -0.0686 0.6668 1.0000
4.000 0.7660 0.01500 0.00714 -0.0676 0.6448 1.0000
4.250 0.7901 0.01524 0.00735 -0.0665 0.6200 1.0000
4.500 0.8147 0.01550 0.00756 -0.0655 0.5959 1.0000
4.750 0.8394 0.01579 0.00776 -0.0645 0.5722 1.0000
5.000 0.8633 0.01612 0.00809 -0.0635 0.5471 1.0000
5.250 0.8869 0.01649 0.00843 -0.0625 0.5216 1.0000
5.500 0.9103 0.01689 0.00878 -0.0615 0.4961 1.0000
5.750 0.9334 0.01731 0.00914 -0.0604 0.4705 1.0000
6.000 0.9564 0.01778 0.00955 -0.0594 0.4452 1.0000
6.250 0.9785 0.01828 0.01004 -0.0583 0.4187 1.0000
6.500 1.0004 0.01882 0.01057 -0.0572 0.3927 1.0000
6.750 1.0219 0.01942 0.01114 -0.0560 0.3670 1.0000
7.000 1.0431 0.02006 0.01174 -0.0549 0.3418 1.0000
7.250 1.0636 0.02074 0.01237 -0.0537 0.3167 1.0000
7.500 1.0832 0.02145 0.01309 -0.0524 0.2910 1.0000
7.750 1.1020 0.02221 0.01386 -0.0510 0.2653 1.0000
8.000 1.1202 0.02306 0.01470 -0.0496 0.2407 1.0000
8.250 1.1375 0.02400 0.01557 -0.0482 0.2169 1.0000
8.500 1.1537 0.02500 0.01655 -0.0466 0.1932 1.0000
8.750 1.1688 0.02614 0.01776 -0.0449 0.1701 1.0000
9.000 1.1832 0.02748 0.01898 -0.0432 0.1493 1.0000
9.250 1.1965 0.02887 0.02046 -0.0413 0.1294 1.0000
9.500 1.2098 0.03043 0.02196 -0.0396 0.1130 1.0000
9.750 1.2233 0.03216 0.02367 -0.0379 0.0991 1.0000
10.000 1.2367 0.03401 0.02561 -0.0361 0.0873 1.0000
10.250 1.2492 0.03607 0.02784 -0.0344 0.0774 1.0000
10.500 1.2629 0.03857 0.03044 -0.0329 0.0690 1.0000
11.000 1.2789 0.04322 0.03552 -0.0289 0.0557 1.0000
11.500 1.2849 0.04882 0.04148 -0.0244 0.0471 1.0000
11.750 1.2791 0.05146 0.04447 -0.0215 0.0446 1.0000
12.000 1.2744 0.05378 0.04697 -0.0193 0.0417 1.0000
12.250 1.2745 0.05706 0.05032 -0.0180 0.0396 1.0000
12.500 1.2660 0.06228 0.05579 -0.0168 0.0386 1.0000
12.750 1.2499 0.06676 0.06055 -0.0157 0.0384 1.0000
13.000 1.2310 0.07109 0.06517 -0.0153 0.0383 1.0000
13.250 1.2126 0.07600 0.07034 -0.0159 0.0383 1.0000
13.500 1.1921 0.08152 0.07610 -0.0175 0.0383 1.0000
13.750 1.1708 0.08773 0.08253 -0.0200 0.0384 1.0000
14.000 1.1512 0.09375 0.08880 -0.0233 0.0387 1.0000
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Polar data table (+)
Polar graphs
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