SA7036 (sa7036-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7036 (sa7036-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.99 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7036-il-1000000.txt Download as CSV file: xf-sa7036-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3924 0.08194 0.08039 -0.0328 1.0000 0.0084
-8.250 -0.3950 0.07836 0.07683 -0.0339 1.0000 0.0084
-8.000 -0.4019 0.07499 0.07352 -0.0345 1.0000 0.0086
-7.750 -0.4184 0.07268 0.07125 -0.0328 0.9996 0.0085
-7.500 -0.3981 0.06459 0.06316 -0.0466 0.9938 0.0087
-7.250 -0.3758 0.05406 0.05253 -0.0625 0.9875 0.0090
-7.000 -0.3808 0.02376 0.02071 -0.0799 0.9736 0.0073
-6.250 -0.3169 0.01851 0.01483 -0.0789 0.9548 0.0082
-6.000 -0.2971 0.01606 0.01199 -0.0776 0.9473 0.0082
-5.750 -0.2744 0.01470 0.01038 -0.0766 0.9416 0.0083
-5.500 -0.2505 0.01344 0.00893 -0.0759 0.9350 0.0084
-5.250 -0.2259 0.01274 0.00810 -0.0751 0.9293 0.0089
-5.000 -0.2005 0.01203 0.00729 -0.0746 0.9226 0.0093
-4.750 -0.1756 0.01113 0.00624 -0.0738 0.9158 0.0096
-4.500 -0.1498 0.01040 0.00540 -0.0733 0.9086 0.0099
-4.250 -0.1234 0.01005 0.00496 -0.0728 0.9016 0.0103
-4.000 -0.0985 0.00889 0.00367 -0.0722 0.8940 0.0116
-3.750 -0.0720 0.00852 0.00324 -0.0718 0.8867 0.0125
-3.500 -0.0447 0.00819 0.00286 -0.0716 0.8783 0.0135
-3.250 -0.0176 0.00798 0.00258 -0.0713 0.8700 0.0147
-3.000 0.0097 0.00758 0.00209 -0.0710 0.8602 0.0171
-2.750 0.0372 0.00737 0.00182 -0.0708 0.8499 0.0197
-2.500 0.0646 0.00713 0.00157 -0.0706 0.8389 0.0312
-2.250 0.0913 0.00671 0.00137 -0.0704 0.8268 0.0987
-2.000 0.1183 0.00642 0.00123 -0.0703 0.8141 0.1621
-1.750 0.1454 0.00615 0.00113 -0.0702 0.8004 0.2299
-1.500 0.1723 0.00587 0.00105 -0.0701 0.7856 0.3137
-1.250 0.1992 0.00560 0.00099 -0.0701 0.7701 0.4064
-1.000 0.2260 0.00535 0.00095 -0.0699 0.7537 0.4978
-0.750 0.2525 0.00512 0.00095 -0.0697 0.7364 0.5976
-0.500 0.2790 0.00497 0.00095 -0.0693 0.7186 0.6762
-0.250 0.3053 0.00488 0.00096 -0.0689 0.7008 0.7391
0.000 0.3312 0.00480 0.00098 -0.0684 0.6829 0.7987
0.250 0.3559 0.00473 0.00101 -0.0675 0.6647 0.8568
0.500 0.3789 0.00470 0.00105 -0.0661 0.6470 0.9130
0.750 0.4053 0.00472 0.00106 -0.0655 0.6288 0.9623
1.000 0.4439 0.00480 0.00105 -0.0678 0.6081 0.9912
1.250 0.4762 0.00493 0.00107 -0.0688 0.5861 1.0000
1.500 0.5025 0.00506 0.00111 -0.0685 0.5655 1.0000
1.750 0.5289 0.00521 0.00115 -0.0682 0.5459 1.0000
2.000 0.5556 0.00535 0.00121 -0.0680 0.5266 1.0000
2.250 0.5823 0.00549 0.00127 -0.0678 0.5073 1.0000
2.500 0.6090 0.00566 0.00134 -0.0675 0.4876 1.0000
2.750 0.6359 0.00581 0.00142 -0.0674 0.4692 1.0000
3.000 0.6626 0.00598 0.00152 -0.0672 0.4495 1.0000
3.250 0.6892 0.00617 0.00162 -0.0670 0.4287 1.0000
3.500 0.7158 0.00637 0.00172 -0.0668 0.4061 1.0000
3.750 0.7423 0.00658 0.00184 -0.0666 0.3861 1.0000
4.000 0.7689 0.00677 0.00198 -0.0664 0.3667 1.0000
4.500 0.8218 0.00721 0.00227 -0.0660 0.3284 1.0000
4.750 0.8481 0.00744 0.00242 -0.0658 0.3092 1.0000
5.250 0.9002 0.00795 0.00280 -0.0654 0.2698 1.0000
5.500 0.9258 0.00825 0.00300 -0.0651 0.2484 1.0000
5.750 0.9516 0.00853 0.00321 -0.0648 0.2300 1.0000
6.000 0.9772 0.00883 0.00345 -0.0645 0.2107 1.0000
6.250 1.0023 0.00917 0.00371 -0.0642 0.1913 1.0000
6.500 1.0274 0.00950 0.00397 -0.0639 0.1723 1.0000
6.750 1.0521 0.00988 0.00426 -0.0635 0.1533 1.0000
7.000 1.0767 0.01025 0.00458 -0.0631 0.1371 1.0000
7.250 1.1013 0.01062 0.00489 -0.0627 0.1216 1.0000
7.500 1.1254 0.01103 0.00524 -0.0622 0.1047 1.0000
7.750 1.1485 0.01154 0.00564 -0.0616 0.0864 1.0000
8.000 1.1717 0.01203 0.00605 -0.0610 0.0707 1.0000
8.250 1.1946 0.01253 0.00650 -0.0604 0.0571 1.0000
8.500 1.2171 0.01306 0.00697 -0.0597 0.0449 1.0000
8.750 1.2395 0.01358 0.00745 -0.0590 0.0362 1.0000
9.000 1.2614 0.01414 0.00798 -0.0583 0.0287 1.0000
9.250 1.2838 0.01461 0.00846 -0.0576 0.0245 1.0000
9.500 1.3053 0.01516 0.00901 -0.0567 0.0199 1.0000
9.750 1.3261 0.01573 0.00959 -0.0559 0.0160 1.0000
10.000 1.3464 0.01634 0.01020 -0.0549 0.0119 1.0000
10.250 1.3646 0.01711 0.01096 -0.0536 0.0078 1.0000
10.500 1.3818 0.01793 0.01182 -0.0522 0.0054 1.0000
10.750 1.3962 0.01896 0.01292 -0.0503 0.0042 1.0000
11.000 1.4136 0.01962 0.01366 -0.0490 0.0040 1.0000
11.250 1.4290 0.02040 0.01452 -0.0473 0.0037 1.0000
11.500 1.4416 0.02117 0.01538 -0.0452 0.0035 1.0000
11.750 1.4514 0.02199 0.01630 -0.0427 0.0033 1.0000
12.000 1.4595 0.02293 0.01733 -0.0401 0.0032 1.0000
12.250 1.4662 0.02400 0.01848 -0.0375 0.0030 1.0000
12.500 1.4704 0.02528 0.01987 -0.0348 0.0029 1.0000
12.750 1.4700 0.02694 0.02166 -0.0320 0.0028 1.0000
13.000 1.4630 0.02922 0.02410 -0.0289 0.0026 1.0000
13.250 1.4631 0.03110 0.02611 -0.0270 0.0026 1.0000
13.500 1.4607 0.03334 0.02848 -0.0253 0.0026 1.0000
13.750 1.4637 0.03527 0.03051 -0.0242 0.0025 1.0000
14.000 1.4587 0.03810 0.03348 -0.0232 0.0025 1.0000
14.250 1.4605 0.04046 0.03595 -0.0227 0.0024 1.0000
14.500 1.4558 0.04372 0.03934 -0.0226 0.0023 1.0000
14.750 1.4496 0.04737 0.04313 -0.0230 0.0023 1.0000
15.000 1.4420 0.05150 0.04739 -0.0239 0.0023 1.0000
15.250 1.4321 0.05622 0.05225 -0.0253 0.0022 1.0000
15.500 1.4210 0.06142 0.05759 -0.0273 0.0022 1.0000
15.750 1.4075 0.06730 0.06363 -0.0298 0.0022 1.0000
16.000 1.3947 0.07336 0.06984 -0.0326 0.0022 1.0000
16.250 1.3783 0.08035 0.07697 -0.0360 0.0022 1.0000
16.500 1.3600 0.08792 0.08470 -0.0398 0.0023 1.0000
16.750 1.3456 0.09512 0.09202 -0.0436 0.0022 1.0000
17.000 1.3288 0.10297 0.10000 -0.0478 0.0021 1.0000
17.250 1.3098 0.11143 0.10859 -0.0524 0.0021 1.0000
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Polar data table (+)
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