SA7036 (sa7036-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7036 (sa7036-il) Reynolds number: 500,000 Max Cl/Cd: 88.94 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7036-il-500000-n5.txt Download as CSV file: xf-sa7036-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4122 0.08350 0.08127 -0.0322 1.0000 0.0049
-8.750 -0.4154 0.07916 0.07697 -0.0339 1.0000 0.0048
-8.250 -0.4294 0.07157 0.06948 -0.0361 1.0000 0.0047
-8.000 -0.4457 0.06705 0.06502 -0.0380 0.9981 0.0047
-7.750 -0.4310 0.05561 0.05351 -0.0557 0.9871 0.0046
-7.500 -0.4369 0.03056 0.02750 -0.0743 0.9729 0.0046
-7.250 -0.4236 0.02291 0.01888 -0.0761 0.9645 0.0048
-7.000 -0.4019 0.01970 0.01515 -0.0766 0.9584 0.0050
-6.750 -0.3766 0.01870 0.01400 -0.0767 0.9530 0.0053
-6.500 -0.3521 0.01763 0.01274 -0.0764 0.9467 0.0055
-6.250 -0.3267 0.01653 0.01143 -0.0763 0.9416 0.0058
-6.000 -0.3026 0.01554 0.01023 -0.0757 0.9346 0.0062
-5.750 -0.2769 0.01482 0.00935 -0.0753 0.9289 0.0068
-5.500 -0.2515 0.01424 0.00861 -0.0748 0.9218 0.0074
-5.250 -0.2262 0.01347 0.00768 -0.0742 0.9153 0.0079
-5.000 -0.2018 0.01241 0.00651 -0.0737 0.9078 0.0085
-4.750 -0.1761 0.01186 0.00588 -0.0732 0.9010 0.0091
-4.500 -0.1500 0.01133 0.00527 -0.0728 0.8934 0.0100
-4.250 -0.1239 0.01087 0.00470 -0.0724 0.8860 0.0108
-4.000 -0.0972 0.01056 0.00432 -0.0721 0.8767 0.0116
-3.750 -0.0713 0.00999 0.00367 -0.0717 0.8671 0.0135
-3.500 -0.0446 0.00967 0.00326 -0.0713 0.8573 0.0146
-3.250 -0.0175 0.00940 0.00290 -0.0710 0.8468 0.0157
-3.000 0.0097 0.00919 0.00262 -0.0707 0.8362 0.0172
-2.750 0.0368 0.00894 0.00230 -0.0704 0.8248 0.0212
-2.500 0.0639 0.00871 0.00207 -0.0702 0.8123 0.0344
-2.250 0.0908 0.00845 0.00186 -0.0700 0.7987 0.0662
-2.000 0.1176 0.00819 0.00170 -0.0698 0.7836 0.1128
-1.750 0.1443 0.00796 0.00156 -0.0696 0.7673 0.1634
-1.500 0.1708 0.00768 0.00146 -0.0694 0.7502 0.2392
-1.250 0.1970 0.00736 0.00137 -0.0693 0.7328 0.3394
-1.000 0.2231 0.00704 0.00133 -0.0691 0.7157 0.4483
-0.750 0.2493 0.00684 0.00130 -0.0688 0.6982 0.5334
-0.500 0.2755 0.00669 0.00130 -0.0684 0.6805 0.6077
-0.250 0.3016 0.00661 0.00130 -0.0680 0.6627 0.6674
0.000 0.3275 0.00655 0.00131 -0.0675 0.6447 0.7196
0.250 0.3528 0.00649 0.00134 -0.0668 0.6260 0.7734
0.500 0.3767 0.00644 0.00138 -0.0657 0.6072 0.8316
0.750 0.3993 0.00641 0.00142 -0.0642 0.5891 0.8910
1.000 0.4277 0.00645 0.00144 -0.0640 0.5702 0.9468
1.250 0.4648 0.00655 0.00144 -0.0660 0.5502 0.9848
1.500 0.4962 0.00668 0.00147 -0.0668 0.5312 1.0000
1.750 0.5223 0.00684 0.00153 -0.0665 0.5108 1.0000
2.000 0.5483 0.00702 0.00159 -0.0662 0.4898 1.0000
2.250 0.5744 0.00720 0.00168 -0.0659 0.4687 1.0000
2.500 0.6006 0.00739 0.00177 -0.0656 0.4502 1.0000
2.750 0.6270 0.00757 0.00186 -0.0653 0.4322 1.0000
3.000 0.6532 0.00776 0.00199 -0.0651 0.4133 1.0000
3.250 0.6795 0.00796 0.00211 -0.0648 0.3960 1.0000
3.500 0.7056 0.00817 0.00224 -0.0645 0.3779 1.0000
3.750 0.7317 0.00838 0.00239 -0.0643 0.3599 1.0000
4.000 0.7575 0.00863 0.00257 -0.0640 0.3387 1.0000
4.250 0.7833 0.00889 0.00274 -0.0637 0.3181 1.0000
4.500 0.8090 0.00915 0.00293 -0.0634 0.2988 1.0000
4.750 0.8347 0.00942 0.00313 -0.0631 0.2818 1.0000
5.000 0.8604 0.00968 0.00336 -0.0628 0.2661 1.0000
5.250 0.8858 0.00996 0.00359 -0.0625 0.2482 1.0000
5.500 0.9112 0.01026 0.00383 -0.0621 0.2312 1.0000
5.750 0.9360 0.01060 0.00410 -0.0617 0.2122 1.0000
6.000 0.9608 0.01095 0.00439 -0.0614 0.1942 1.0000
6.250 0.9855 0.01131 0.00471 -0.0609 0.1763 1.0000
6.500 1.0097 0.01170 0.00504 -0.0605 0.1585 1.0000
6.750 1.0338 0.01210 0.00539 -0.0600 0.1435 1.0000
7.000 1.0576 0.01252 0.00576 -0.0595 0.1266 1.0000
7.250 1.0810 0.01297 0.00616 -0.0589 0.1099 1.0000
7.500 1.1042 0.01344 0.00660 -0.0583 0.0955 1.0000
7.750 1.1272 0.01391 0.00704 -0.0577 0.0830 1.0000
8.000 1.1493 0.01446 0.00754 -0.0570 0.0691 1.0000
8.250 1.1710 0.01503 0.00806 -0.0562 0.0563 1.0000
8.500 1.1918 0.01568 0.00864 -0.0554 0.0433 1.0000
8.750 1.2127 0.01628 0.00922 -0.0545 0.0345 1.0000
9.000 1.2334 0.01688 0.00985 -0.0536 0.0276 1.0000
9.250 1.2536 0.01750 0.01048 -0.0526 0.0227 1.0000
9.500 1.2733 0.01813 0.01113 -0.0516 0.0184 1.0000
9.750 1.2926 0.01877 0.01181 -0.0505 0.0151 1.0000
10.000 1.3101 0.01952 0.01258 -0.0492 0.0113 1.0000
10.250 1.3269 0.02029 0.01337 -0.0478 0.0080 1.0000
10.500 1.3415 0.02118 0.01429 -0.0462 0.0051 1.0000
10.750 1.3546 0.02205 0.01525 -0.0442 0.0038 1.0000
11.000 1.3650 0.02296 0.01624 -0.0419 0.0032 1.0000
11.250 1.3748 0.02390 0.01728 -0.0395 0.0029 1.0000
11.500 1.3841 0.02490 0.01838 -0.0373 0.0026 1.0000
11.750 1.3930 0.02593 0.01953 -0.0351 0.0025 1.0000
12.000 1.3998 0.02715 0.02087 -0.0330 0.0023 1.0000
12.250 1.4063 0.02844 0.02229 -0.0310 0.0022 1.0000
12.500 1.4110 0.02992 0.02389 -0.0290 0.0021 1.0000
12.750 1.4152 0.03151 0.02560 -0.0273 0.0020 1.0000
13.000 1.4172 0.03338 0.02759 -0.0257 0.0019 1.0000
13.250 1.4181 0.03546 0.02982 -0.0244 0.0018 1.0000
13.500 1.4147 0.03811 0.03261 -0.0233 0.0017 1.0000
13.750 1.4125 0.04082 0.03546 -0.0227 0.0017 1.0000
14.000 1.4019 0.04470 0.03955 -0.0225 0.0016 1.0000
14.250 1.3967 0.04823 0.04323 -0.0229 0.0016 1.0000
14.500 1.3878 0.05251 0.04766 -0.0238 0.0016 1.0000
14.750 1.3797 0.05696 0.05227 -0.0251 0.0016 1.0000
15.000 1.3695 0.06201 0.05748 -0.0270 0.0016 1.0000
15.250 1.3592 0.06737 0.06299 -0.0293 0.0015 1.0000
15.500 1.3454 0.07358 0.06936 -0.0322 0.0015 1.0000
15.750 1.3311 0.08018 0.07612 -0.0354 0.0015 1.0000
16.000 1.3160 0.08718 0.08327 -0.0389 0.0015 1.0000
16.250 1.2991 0.09482 0.09106 -0.0429 0.0015 1.0000
16.500 1.2814 0.10287 0.09926 -0.0472 0.0015 1.0000
16.750 1.2639 0.11106 0.10759 -0.0516 0.0015 1.0000
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