SD7003-085-88 (sd7003-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7003-085-88 (sd7003-il) Reynolds number: 50,000 Max Cl/Cd: 32.72 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7003-il-50000-n5.txt Download as CSV file: xf-sd7003-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD7003-085-88
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5626 0.09336 0.08630 -0.0130 1.0000 0.0482
-9.000 -0.5667 0.08775 0.08076 -0.0166 1.0000 0.0482
-8.750 -0.5706 0.08217 0.07524 -0.0203 1.0000 0.0480
-8.500 -0.5765 0.07658 0.06970 -0.0243 1.0000 0.0478
-8.250 -0.5826 0.07102 0.06410 -0.0279 1.0000 0.0477
-8.000 -0.5875 0.06550 0.05848 -0.0310 1.0000 0.0476
-7.750 -0.5902 0.05998 0.05274 -0.0335 1.0000 0.0476
-7.500 -0.5893 0.05456 0.04698 -0.0354 1.0000 0.0478
-7.250 -0.5839 0.04941 0.04141 -0.0365 1.0000 0.0484
-7.000 -0.5688 0.04719 0.03921 -0.0363 1.0000 0.0510
-6.750 -0.5546 0.04406 0.03578 -0.0364 1.0000 0.0546
-6.500 -0.5398 0.03986 0.03094 -0.0367 1.0000 0.0577
-6.250 -0.5217 0.03607 0.02651 -0.0365 1.0000 0.0607
-6.000 -0.5013 0.03433 0.02471 -0.0360 1.0000 0.0663
-5.750 -0.4790 0.03156 0.02128 -0.0354 1.0000 0.0718
-5.500 -0.4571 0.02976 0.01942 -0.0348 1.0000 0.0783
-5.250 -0.4334 0.02787 0.01710 -0.0340 1.0000 0.0866
-5.000 -0.4106 0.02647 0.01567 -0.0332 1.0000 0.0958
-4.750 -0.3873 0.02508 0.01419 -0.0323 1.0000 0.1059
-4.500 -0.3640 0.02390 0.01290 -0.0315 1.0000 0.1190
-4.250 -0.3406 0.02279 0.01172 -0.0305 1.0000 0.1328
-4.000 -0.3174 0.02183 0.01075 -0.0297 1.0000 0.1515
-3.750 -0.2936 0.02087 0.00980 -0.0289 1.0000 0.1733
-3.500 -0.2708 0.01997 0.00901 -0.0282 1.0000 0.2043
-3.250 -0.2481 0.01907 0.00832 -0.0274 1.0000 0.2477
-3.000 -0.2261 0.01819 0.00778 -0.0267 1.0000 0.3153
-2.750 -0.2053 0.01735 0.00741 -0.0255 1.0000 0.4093
-2.500 -0.1869 0.01663 0.00721 -0.0235 1.0000 0.5224
-2.250 -0.1713 0.01613 0.00719 -0.0202 1.0000 0.6381
-2.000 -0.1569 0.01581 0.00716 -0.0164 1.0000 0.7432
-1.750 -0.1380 0.01557 0.00707 -0.0133 1.0000 0.8431
-1.500 -0.0846 0.01534 0.00672 -0.0174 1.0000 0.9652
-1.250 -0.0567 0.01528 0.00644 -0.0184 1.0000 1.0000
-1.000 -0.0397 0.01534 0.00631 -0.0174 1.0000 1.0000
-0.750 -0.0218 0.01546 0.00627 -0.0165 1.0000 1.0000
-0.500 0.0129 0.01567 0.00630 -0.0188 0.9896 1.0000
-0.250 0.0626 0.01590 0.00637 -0.0236 0.9699 1.0000
0.000 0.1090 0.01604 0.00639 -0.0276 0.9479 1.0000
0.250 0.1581 0.01615 0.00641 -0.0317 0.9276 1.0000
0.500 0.2008 0.01621 0.00641 -0.0345 0.9030 1.0000
0.750 0.2422 0.01626 0.00640 -0.0367 0.8778 1.0000
1.000 0.2807 0.01631 0.00639 -0.0383 0.8508 1.0000
1.250 0.3151 0.01638 0.00639 -0.0389 0.8221 1.0000
1.500 0.3459 0.01649 0.00642 -0.0387 0.7920 1.0000
1.750 0.3741 0.01664 0.00648 -0.0380 0.7613 1.0000
2.000 0.4006 0.01683 0.00657 -0.0371 0.7304 1.0000
2.250 0.4262 0.01705 0.00671 -0.0360 0.6993 1.0000
2.500 0.4512 0.01730 0.00686 -0.0348 0.6684 1.0000
2.750 0.4759 0.01758 0.00704 -0.0337 0.6375 1.0000
3.000 0.5004 0.01788 0.00727 -0.0325 0.6069 1.0000
3.250 0.5247 0.01822 0.00752 -0.0314 0.5766 1.0000
3.500 0.5490 0.01858 0.00779 -0.0304 0.5466 1.0000
3.750 0.5732 0.01897 0.00811 -0.0294 0.5171 1.0000
4.000 0.5978 0.01940 0.00850 -0.0285 0.4878 1.0000
4.250 0.6223 0.01986 0.00891 -0.0277 0.4590 1.0000
4.500 0.6468 0.02036 0.00936 -0.0269 0.4308 1.0000
4.750 0.6711 0.02089 0.00988 -0.0262 0.4035 1.0000
5.000 0.6952 0.02146 0.01040 -0.0254 0.3773 1.0000
5.250 0.7192 0.02207 0.01099 -0.0247 0.3516 1.0000
5.500 0.7431 0.02273 0.01167 -0.0240 0.3269 1.0000
5.750 0.7666 0.02343 0.01238 -0.0233 0.3039 1.0000
6.000 0.7901 0.02418 0.01318 -0.0226 0.2815 1.0000
6.250 0.8131 0.02498 0.01396 -0.0219 0.2611 1.0000
6.500 0.8362 0.02586 0.01493 -0.0213 0.2410 1.0000
6.750 0.8586 0.02677 0.01588 -0.0205 0.2225 1.0000
7.000 0.8808 0.02774 0.01691 -0.0198 0.2058 1.0000
7.250 0.9026 0.02880 0.01804 -0.0191 0.1894 1.0000
7.500 0.9240 0.02994 0.01931 -0.0183 0.1739 1.0000
7.750 0.9447 0.03115 0.02065 -0.0175 0.1593 1.0000
8.000 0.9650 0.03246 0.02210 -0.0167 0.1462 1.0000
8.250 0.9843 0.03381 0.02355 -0.0159 0.1336 1.0000
8.500 1.0030 0.03531 0.02519 -0.0150 0.1221 1.0000
8.750 1.0200 0.03697 0.02710 -0.0141 0.1106 1.0000
9.000 1.0361 0.03891 0.02929 -0.0131 0.1008 1.0000
9.250 1.0509 0.04071 0.03119 -0.0122 0.0922 1.0000
9.500 1.0642 0.04280 0.03356 -0.0111 0.0846 1.0000
9.750 1.0747 0.04528 0.03632 -0.0101 0.0781 1.0000
10.000 1.0839 0.04771 0.03900 -0.0090 0.0726 1.0000
10.250 1.0919 0.05023 0.04162 -0.0081 0.0684 1.0000
10.500 1.0890 0.05394 0.04583 -0.0070 0.0650 1.0000
10.750 1.0854 0.05722 0.04939 -0.0060 0.0622 1.0000
11.000 1.0799 0.06034 0.05267 -0.0050 0.0604 1.0000
11.250 1.0736 0.06373 0.05619 -0.0046 0.0591 1.0000
11.500 1.0663 0.06756 0.06008 -0.0049 0.0580 1.0000
11.750 1.0450 0.07329 0.06605 -0.0074 0.0580 1.0000
12.000 1.0213 0.08028 0.07323 -0.0116 0.0581 1.0000
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Polar data table (+)
Polar graphs
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