SD7003-085-88 (sd7003-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7003-085-88 (sd7003-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.15 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7003-il-1000000-n5.txt Download as CSV file: xf-sd7003-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.8200 0.09509 0.09314 -0.0049 1.0000 0.0040
-13.250 -0.9124 0.07343 0.07139 -0.0184 1.0000 0.0037
-13.000 -1.0534 0.03891 0.03636 -0.0466 1.0000 0.0034
-12.750 -1.0731 0.03525 0.03251 -0.0463 1.0000 0.0034
-12.500 -1.0751 0.03229 0.02935 -0.0460 1.0000 0.0034
-12.250 -1.0699 0.02981 0.02667 -0.0455 1.0000 0.0034
-12.000 -1.0582 0.02796 0.02466 -0.0450 1.0000 0.0035
-11.750 -1.0448 0.02615 0.02267 -0.0444 1.0000 0.0036
-11.500 -1.0291 0.02457 0.02092 -0.0438 1.0000 0.0036
-11.250 -1.0113 0.02319 0.01938 -0.0433 1.0000 0.0037
-11.000 -0.9922 0.02194 0.01799 -0.0427 1.0000 0.0038
-10.750 -0.9718 0.02085 0.01676 -0.0422 1.0000 0.0039
-10.500 -0.9511 0.01975 0.01551 -0.0417 1.0000 0.0040
-10.250 -0.9293 0.01882 0.01446 -0.0412 1.0000 0.0041
-10.000 -0.9070 0.01798 0.01350 -0.0406 1.0000 0.0042
-9.750 -0.8842 0.01718 0.01259 -0.0401 1.0000 0.0043
-9.500 -0.8612 0.01643 0.01174 -0.0396 1.0000 0.0043
-9.250 -0.8376 0.01578 0.01099 -0.0390 1.0000 0.0044
-9.000 -0.8144 0.01505 0.01015 -0.0384 1.0000 0.0045
-8.750 -0.7916 0.01419 0.00918 -0.0378 1.0000 0.0047
-8.500 -0.7680 0.01354 0.00846 -0.0371 1.0000 0.0049
-8.250 -0.7441 0.01298 0.00783 -0.0365 1.0000 0.0051
-8.000 -0.7199 0.01249 0.00729 -0.0359 1.0000 0.0054
-7.750 -0.6955 0.01204 0.00678 -0.0352 1.0000 0.0056
-7.500 -0.6711 0.01163 0.00632 -0.0346 1.0000 0.0059
-7.250 -0.6465 0.01124 0.00588 -0.0340 1.0000 0.0062
-7.000 -0.6219 0.01088 0.00548 -0.0333 1.0000 0.0065
-6.750 -0.5966 0.01049 0.00505 -0.0328 0.9998 0.0071
-6.500 -0.5636 0.01009 0.00463 -0.0340 0.9976 0.0081
-6.250 -0.5303 0.00976 0.00427 -0.0352 0.9951 0.0092
-6.000 -0.4981 0.00942 0.00393 -0.0362 0.9919 0.0110
-5.750 -0.4655 0.00913 0.00363 -0.0372 0.9879 0.0133
-5.250 -0.4003 0.00858 0.00308 -0.0392 0.9764 0.0191
-5.000 -0.3672 0.00834 0.00285 -0.0403 0.9677 0.0224
-4.750 -0.3342 0.00808 0.00261 -0.0413 0.9535 0.0277
-4.500 -0.3024 0.00788 0.00239 -0.0420 0.9302 0.0326
-4.250 -0.2750 0.00777 0.00220 -0.0416 0.8986 0.0377
-4.000 -0.2491 0.00767 0.00203 -0.0410 0.8658 0.0454
-3.750 -0.2229 0.00762 0.00187 -0.0404 0.8338 0.0516
-3.500 -0.1965 0.00756 0.00172 -0.0400 0.8035 0.0577
-3.250 -0.1697 0.00752 0.00159 -0.0396 0.7746 0.0642
-3.000 -0.1427 0.00748 0.00147 -0.0393 0.7473 0.0726
-2.750 -0.1156 0.00741 0.00135 -0.0390 0.7212 0.0847
-2.500 -0.0883 0.00734 0.00125 -0.0388 0.6957 0.1012
-2.250 -0.0610 0.00726 0.00115 -0.0386 0.6707 0.1209
-2.000 -0.0337 0.00720 0.00106 -0.0384 0.6457 0.1434
-1.500 0.0212 0.00705 0.00093 -0.0382 0.5966 0.1991
-1.250 0.0486 0.00697 0.00088 -0.0381 0.5718 0.2363
-1.000 0.0761 0.00691 0.00083 -0.0379 0.5472 0.2706
-0.750 0.1037 0.00687 0.00080 -0.0378 0.5235 0.3034
-0.500 0.1312 0.00681 0.00079 -0.0378 0.5007 0.3443
-0.250 0.1586 0.00669 0.00077 -0.0377 0.4795 0.4061
0.000 0.1859 0.00659 0.00078 -0.0376 0.4573 0.4657
0.250 0.2132 0.00649 0.00079 -0.0375 0.4364 0.5301
0.500 0.2406 0.00641 0.00082 -0.0374 0.4157 0.5888
0.750 0.2678 0.00638 0.00086 -0.0372 0.3948 0.6417
1.000 0.2951 0.00637 0.00092 -0.0370 0.3753 0.6870
1.250 0.3224 0.00640 0.00098 -0.0368 0.3549 0.7249
1.500 0.3495 0.00645 0.00104 -0.0365 0.3352 0.7561
1.750 0.3766 0.00651 0.00112 -0.0362 0.3170 0.7846
2.000 0.4035 0.00657 0.00120 -0.0359 0.2979 0.8123
2.250 0.4301 0.00665 0.00128 -0.0355 0.2804 0.8405
2.500 0.4560 0.00673 0.00138 -0.0349 0.2623 0.8700
2.750 0.4811 0.00679 0.00147 -0.0342 0.2475 0.9009
3.000 0.5055 0.00685 0.00156 -0.0332 0.2329 0.9361
3.250 0.5370 0.00696 0.00165 -0.0338 0.2157 0.9769
3.500 0.5686 0.00713 0.00175 -0.0346 0.2016 1.0000
3.750 0.5959 0.00732 0.00188 -0.0345 0.1862 1.0000
4.000 0.6232 0.00752 0.00202 -0.0344 0.1730 1.0000
4.250 0.6504 0.00773 0.00216 -0.0342 0.1589 1.0000
4.500 0.6776 0.00794 0.00232 -0.0341 0.1463 1.0000
4.750 0.7047 0.00817 0.00249 -0.0339 0.1335 1.0000
5.000 0.7318 0.00838 0.00267 -0.0337 0.1233 1.0000
5.250 0.7590 0.00858 0.00284 -0.0336 0.1148 1.0000
5.500 0.7858 0.00884 0.00305 -0.0334 0.1034 1.0000
5.750 0.8124 0.00912 0.00328 -0.0332 0.0911 1.0000
6.000 0.8388 0.00943 0.00352 -0.0330 0.0785 1.0000
6.250 0.8653 0.00973 0.00378 -0.0327 0.0688 1.0000
6.500 0.8918 0.01001 0.00404 -0.0325 0.0614 1.0000
6.750 0.9182 0.01030 0.00431 -0.0323 0.0549 1.0000
7.000 0.9443 0.01064 0.00461 -0.0320 0.0475 1.0000
7.250 0.9704 0.01095 0.00491 -0.0318 0.0416 1.0000
7.500 0.9963 0.01131 0.00526 -0.0315 0.0356 1.0000
7.750 1.0218 0.01170 0.00562 -0.0312 0.0298 1.0000
8.000 1.0474 0.01207 0.00599 -0.0309 0.0254 1.0000
8.250 1.0726 0.01250 0.00640 -0.0305 0.0208 1.0000
8.500 1.0974 0.01296 0.00686 -0.0301 0.0171 1.0000
8.750 1.1226 0.01336 0.00729 -0.0297 0.0152 1.0000
9.000 1.1472 0.01383 0.00777 -0.0293 0.0135 1.0000
9.250 1.1717 0.01430 0.00828 -0.0289 0.0122 1.0000
9.500 1.1963 0.01473 0.00875 -0.0285 0.0116 1.0000
9.750 1.2205 0.01520 0.00928 -0.0280 0.0110 1.0000
10.000 1.2442 0.01572 0.00984 -0.0275 0.0104 1.0000
10.250 1.2674 0.01630 0.01046 -0.0270 0.0098 1.0000
10.500 1.2896 0.01697 0.01120 -0.0263 0.0092 1.0000
10.750 1.3126 0.01751 0.01179 -0.0257 0.0089 1.0000
11.000 1.3352 0.01806 0.01242 -0.0251 0.0086 1.0000
11.250 1.3574 0.01864 0.01307 -0.0245 0.0083 1.0000
11.500 1.3791 0.01924 0.01374 -0.0238 0.0079 1.0000
11.750 1.4000 0.01990 0.01445 -0.0231 0.0075 1.0000
12.000 1.4199 0.02063 0.01525 -0.0222 0.0072 1.0000
12.250 1.4388 0.02143 0.01612 -0.0213 0.0069 1.0000
12.500 1.4554 0.02241 0.01719 -0.0201 0.0066 1.0000
12.750 1.4718 0.02333 0.01820 -0.0189 0.0064 1.0000
13.000 1.4890 0.02410 0.01906 -0.0178 0.0062 1.0000
13.250 1.5048 0.02492 0.01997 -0.0166 0.0060 1.0000
13.500 1.5189 0.02579 0.02092 -0.0152 0.0058 1.0000
13.750 1.5301 0.02671 0.02192 -0.0134 0.0056 1.0000
14.000 1.5359 0.02771 0.02301 -0.0109 0.0054 1.0000
14.250 1.5398 0.02887 0.02426 -0.0085 0.0053 1.0000
14.500 1.5416 0.03028 0.02577 -0.0064 0.0051 1.0000
14.750 1.5423 0.03196 0.02754 -0.0047 0.0050 1.0000
15.000 1.5399 0.03412 0.02981 -0.0036 0.0049 1.0000
15.250 1.5373 0.03663 0.03242 -0.0033 0.0047 1.0000
15.500 1.5309 0.03992 0.03583 -0.0037 0.0046 1.0000
15.750 1.5228 0.04387 0.03990 -0.0050 0.0045 1.0000
16.000 1.5095 0.04898 0.04518 -0.0073 0.0045 1.0000
16.250 1.4925 0.05522 0.05158 -0.0107 0.0044 1.0000
16.500 1.4720 0.06245 0.05896 -0.0148 0.0044 1.0000
16.750 1.4457 0.07104 0.06772 -0.0199 0.0044 1.0000
17.000 1.4179 0.08020 0.07705 -0.0252 0.0045 1.0000
17.250 1.3834 0.09087 0.08789 -0.0314 0.0046 1.0000
17.500 1.3467 0.10236 0.09955 -0.0381 0.0047 1.0000
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Polar data table (+)
Polar graphs
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