SA7036 (sa7036-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7036 (sa7036-il) Reynolds number: 500,000 Max Cl/Cd: 97.12 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7036-il-500000.txt Download as CSV file: xf-sa7036-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3927 0.08148 0.07933 -0.0362 1.0000 0.0151
-8.250 -0.3974 0.07758 0.07547 -0.0374 1.0000 0.0152
-8.000 -0.4081 0.07440 0.07234 -0.0371 1.0000 0.0155
-7.750 -0.4285 0.07160 0.06963 -0.0359 1.0000 0.0154
-7.500 -0.4449 0.06854 0.06661 -0.0359 1.0000 0.0154
-7.250 -0.4399 0.06376 0.06182 -0.0409 0.9980 0.0157
-7.000 -0.4153 0.05857 0.05655 -0.0489 0.9945 0.0163
-6.750 -0.3914 0.05227 0.05011 -0.0570 0.9895 0.0168
-6.500 -0.3638 0.04588 0.04351 -0.0644 0.9856 0.0180
-6.250 -0.3266 0.04007 0.03718 -0.0702 0.9823 0.0210
-6.000 -0.3113 0.03130 0.02787 -0.0746 0.9757 0.0224
-5.750 -0.2791 0.02948 0.02604 -0.0773 0.9735 0.0239
-5.500 -0.2448 0.02701 0.02329 -0.0799 0.9714 0.0266
-5.250 -0.2185 0.02398 0.01980 -0.0808 0.9659 0.0318
-5.000 -0.1900 0.01620 0.01087 -0.0793 0.9607 0.0156
-4.750 -0.1579 0.01463 0.00908 -0.0799 0.9575 0.0154
-4.500 -0.1331 0.01320 0.00749 -0.0792 0.9508 0.0157
-4.250 -0.1061 0.01210 0.00631 -0.0789 0.9452 0.0167
-4.000 -0.0806 0.01144 0.00559 -0.0782 0.9384 0.0179
-3.750 -0.0549 0.01095 0.00505 -0.0775 0.9313 0.0196
-3.500 -0.0294 0.01055 0.00459 -0.0767 0.9241 0.0210
-3.250 -0.0046 0.00973 0.00366 -0.0759 0.9165 0.0235
-3.000 0.0213 0.00936 0.00324 -0.0752 0.9086 0.0272
-2.750 0.0474 0.00895 0.00280 -0.0745 0.9010 0.0394
-2.500 0.0723 0.00822 0.00247 -0.0740 0.8916 0.1379
-2.250 0.0980 0.00777 0.00226 -0.0736 0.8828 0.2237
-2.000 0.1235 0.00729 0.00211 -0.0732 0.8729 0.3313
-1.750 0.1488 0.00684 0.00200 -0.0728 0.8617 0.4475
-1.500 0.1739 0.00642 0.00193 -0.0722 0.8503 0.5680
-1.250 0.1990 0.00611 0.00188 -0.0714 0.8384 0.6648
-1.000 0.2237 0.00588 0.00183 -0.0704 0.8259 0.7423
-0.750 0.2473 0.00569 0.00180 -0.0691 0.8125 0.8146
-0.500 0.2693 0.00555 0.00178 -0.0672 0.7981 0.8829
-0.250 0.2954 0.00549 0.00173 -0.0662 0.7831 0.9423
0.000 0.3350 0.00548 0.00164 -0.0685 0.7670 0.9787
0.250 0.3779 0.00551 0.00153 -0.0717 0.7490 1.0000
0.500 0.4025 0.00560 0.00150 -0.0709 0.7309 1.0000
0.750 0.4276 0.00570 0.00149 -0.0703 0.7123 1.0000
1.000 0.4531 0.00582 0.00149 -0.0697 0.6932 1.0000
1.250 0.4788 0.00595 0.00150 -0.0692 0.6744 1.0000
1.500 0.5047 0.00607 0.00153 -0.0688 0.6550 1.0000
1.750 0.5307 0.00622 0.00157 -0.0684 0.6344 1.0000
2.000 0.5566 0.00638 0.00163 -0.0679 0.6134 1.0000
2.250 0.5827 0.00653 0.00169 -0.0676 0.5922 1.0000
2.500 0.6087 0.00671 0.00177 -0.0672 0.5718 1.0000
2.750 0.6350 0.00688 0.00185 -0.0669 0.5512 1.0000
3.250 0.6872 0.00726 0.00207 -0.0662 0.5097 1.0000
3.500 0.7132 0.00747 0.00220 -0.0659 0.4895 1.0000
3.750 0.7392 0.00768 0.00233 -0.0656 0.4677 1.0000
4.250 0.7907 0.00816 0.00266 -0.0649 0.4220 1.0000
4.500 0.8163 0.00842 0.00284 -0.0645 0.4011 1.0000
4.750 0.8420 0.00867 0.00303 -0.0642 0.3794 1.0000
5.000 0.8675 0.00895 0.00325 -0.0638 0.3586 1.0000
5.250 0.8930 0.00922 0.00347 -0.0635 0.3379 1.0000
5.500 0.9181 0.00955 0.00371 -0.0631 0.3162 1.0000
5.750 0.9432 0.00986 0.00396 -0.0627 0.2945 1.0000
6.000 0.9679 0.01022 0.00425 -0.0623 0.2725 1.0000
6.250 0.9925 0.01058 0.00454 -0.0619 0.2506 1.0000
6.500 1.0170 0.01095 0.00486 -0.0614 0.2304 1.0000
6.750 1.0411 0.01136 0.00520 -0.0610 0.2086 1.0000
7.000 1.0649 0.01179 0.00557 -0.0604 0.1883 1.0000
7.250 1.0885 0.01224 0.00596 -0.0599 0.1681 1.0000
7.500 1.1116 0.01273 0.00638 -0.0593 0.1489 1.0000
7.750 1.1347 0.01320 0.00681 -0.0587 0.1315 1.0000
8.000 1.1572 0.01374 0.00729 -0.0580 0.1137 1.0000
8.250 1.1790 0.01432 0.00783 -0.0573 0.0963 1.0000
8.500 1.2005 0.01492 0.00838 -0.0565 0.0800 1.0000
8.750 1.2208 0.01563 0.00900 -0.0555 0.0638 1.0000
9.000 1.2401 0.01641 0.00969 -0.0545 0.0491 1.0000
9.250 1.2595 0.01714 0.01039 -0.0534 0.0393 1.0000
9.500 1.2794 0.01778 0.01106 -0.0524 0.0328 1.0000
9.750 1.2976 0.01856 0.01188 -0.0511 0.0273 1.0000
10.000 1.3150 0.01936 0.01270 -0.0498 0.0224 1.0000
10.250 1.3316 0.02017 0.01360 -0.0483 0.0184 1.0000
10.500 1.3430 0.02137 0.01483 -0.0461 0.0136 1.0000
10.750 1.3536 0.02244 0.01595 -0.0438 0.0107 1.0000
11.000 1.3560 0.02387 0.01751 -0.0403 0.0094 1.0000
11.250 1.3642 0.02494 0.01868 -0.0378 0.0084 1.0000
11.500 1.3723 0.02602 0.01985 -0.0356 0.0077 1.0000
11.750 1.3743 0.02757 0.02148 -0.0329 0.0070 1.0000
12.000 1.3677 0.02985 0.02392 -0.0298 0.0067 1.0000
12.250 1.3718 0.03145 0.02564 -0.0279 0.0063 1.0000
12.500 1.3731 0.03338 0.02773 -0.0262 0.0061 1.0000
12.750 1.3737 0.03551 0.03000 -0.0248 0.0059 1.0000
13.000 1.3716 0.03805 0.03268 -0.0236 0.0057 1.0000
13.250 1.3685 0.04088 0.03565 -0.0228 0.0057 1.0000
13.500 1.3655 0.04388 0.03880 -0.0225 0.0055 1.0000
13.750 1.3616 0.04718 0.04223 -0.0226 0.0053 1.0000
14.000 1.3553 0.05101 0.04621 -0.0230 0.0053 1.0000
14.250 1.3508 0.05482 0.05016 -0.0239 0.0051 1.0000
14.500 1.3437 0.05919 0.05467 -0.0252 0.0050 1.0000
14.750 1.3356 0.06391 0.05953 -0.0269 0.0050 1.0000
15.000 1.3265 0.06903 0.06479 -0.0289 0.0049 1.0000
15.250 1.3162 0.07460 0.07049 -0.0314 0.0048 1.0000
15.500 1.3057 0.08037 0.07642 -0.0340 0.0048 1.0000
15.750 1.2938 0.08664 0.08282 -0.0371 0.0047 1.0000
16.000 1.2822 0.09308 0.08941 -0.0403 0.0047 1.0000
16.250 1.2699 0.09983 0.09631 -0.0438 0.0047 1.0000
16.500 1.2565 0.10701 0.10365 -0.0475 0.0048 1.0000
16.750 1.2447 0.11409 0.11083 -0.0515 0.0047 1.0000
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Polar data table (+)
Polar graphs
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