SPICA 11.73% smoothed (spicasm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SPICA 11.73% smoothed (spicasm-il) Reynolds number: 50,000 Max Cl/Cd: 30.89 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-spicasm-il-50000-n5.txt Download as CSV file: xf-spicasm-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SPICA 11.73% smoothed
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 -0.2671 0.11105 0.10422 -0.0373 1.0000 0.1169
-9.000 -0.2818 0.11039 0.10371 -0.0387 1.0000 0.1196
-8.750 -0.3017 0.11001 0.10354 -0.0397 1.0000 0.1204
-8.500 -0.2910 0.10549 0.09911 -0.0382 1.0000 0.1219
-8.250 -0.2769 0.10178 0.09543 -0.0360 1.0000 0.1249
-8.000 -0.2796 0.09983 0.09361 -0.0343 1.0000 0.1277
-7.750 -0.2927 0.09877 0.09272 -0.0318 1.0000 0.1300
-7.500 -0.3058 0.09770 0.09180 -0.0312 0.9953 0.1329
-7.250 -0.3006 0.09389 0.08801 -0.0447 0.9703 0.1380
-7.000 -0.2716 0.08945 0.08354 -0.0426 0.9643 0.1426
-6.500 -0.2343 0.08177 0.07583 -0.0523 0.9363 0.1602
-6.250 -0.2200 0.07808 0.07208 -0.0592 0.9216 0.1729
-6.000 -0.2031 0.07490 0.06881 -0.0650 0.9086 0.1880
-5.750 -0.1747 0.07092 0.06483 -0.0649 0.9017 0.1942
-5.500 -0.1430 0.06072 0.05370 -0.0810 0.8863 0.0884
-5.000 -0.0956 0.05263 0.04494 -0.0860 0.8671 0.0751
-4.750 -0.0757 0.04990 0.04204 -0.0865 0.8561 0.0736
-4.500 -0.0527 0.04716 0.03900 -0.0875 0.8468 0.0730
-4.250 -0.0283 0.04466 0.03613 -0.0884 0.8381 0.0734
-4.000 -0.0063 0.04251 0.03363 -0.0884 0.8285 0.0734
-3.750 0.0203 0.04029 0.03103 -0.0889 0.8208 0.0729
-3.500 0.0423 0.03851 0.02891 -0.0884 0.8116 0.0722
-3.250 0.0701 0.03666 0.02666 -0.0886 0.8044 0.0717
-3.000 0.0936 0.03525 0.02490 -0.0880 0.7955 0.0716
-2.750 0.1221 0.03379 0.02307 -0.0879 0.7885 0.0718
-2.500 0.1475 0.03273 0.02169 -0.0874 0.7805 0.0732
-2.250 0.1755 0.03180 0.02036 -0.0871 0.7730 0.0756
-2.000 0.2032 0.03077 0.01915 -0.0869 0.7662 0.0777
-1.750 0.2288 0.02998 0.01825 -0.0864 0.7582 0.0794
-1.500 0.2624 0.02905 0.01715 -0.0869 0.7530 0.0816
-1.250 0.2855 0.02869 0.01667 -0.0860 0.7440 0.0841
-1.000 0.3177 0.02814 0.01588 -0.0861 0.7382 0.0896
-0.750 0.3400 0.02779 0.01556 -0.0853 0.7302 0.0959
-0.500 0.3671 0.02743 0.01504 -0.0848 0.7237 0.1034
-0.250 0.3919 0.02709 0.01470 -0.0843 0.7169 0.1158
0.000 0.4146 0.02687 0.01450 -0.0834 0.7093 0.1363
0.250 0.4862 0.02363 0.01377 -0.0909 0.7050 1.0000
0.500 0.5033 0.02415 0.01402 -0.0891 0.6963 1.0000
0.750 0.5292 0.02437 0.01394 -0.0885 0.6899 1.0000
1.000 0.5482 0.02486 0.01424 -0.0870 0.6817 1.0000
1.250 0.5721 0.02515 0.01433 -0.0862 0.6746 1.0000
1.500 0.5935 0.02556 0.01458 -0.0851 0.6671 1.0000
1.750 0.6153 0.02594 0.01483 -0.0840 0.6593 1.0000
2.000 0.6393 0.02626 0.01500 -0.0832 0.6523 1.0000
2.250 0.6588 0.02675 0.01540 -0.0818 0.6437 1.0000
2.500 0.6850 0.02697 0.01550 -0.0812 0.6371 1.0000
2.750 0.7024 0.02755 0.01603 -0.0797 0.6278 1.0000
3.000 0.7294 0.02772 0.01610 -0.0792 0.6211 1.0000
3.250 0.7462 0.02832 0.01668 -0.0775 0.6114 1.0000
3.500 0.7715 0.02855 0.01684 -0.0768 0.6040 1.0000
3.750 0.7902 0.02906 0.01732 -0.0754 0.5946 1.0000
4.000 0.8118 0.02944 0.01768 -0.0742 0.5860 1.0000
4.500 0.8519 0.03031 0.01854 -0.0716 0.5676 1.0000
4.750 0.8792 0.03037 0.01858 -0.0711 0.5599 1.0000
5.000 0.8925 0.03114 0.01939 -0.0691 0.5492 1.0000
5.250 0.9242 0.03095 0.01916 -0.0690 0.5423 1.0000
5.500 0.9337 0.03190 0.02020 -0.0666 0.5308 1.0000
5.750 0.9538 0.03231 0.02064 -0.0653 0.5217 1.0000
6.000 0.9762 0.03255 0.02091 -0.0643 0.5125 1.0000
6.250 0.9878 0.03338 0.02181 -0.0621 0.5016 1.0000
6.500 1.0204 0.03307 0.02152 -0.0621 0.4946 1.0000
6.750 1.0269 0.03414 0.02269 -0.0595 0.4826 1.0000
7.000 1.0401 0.03486 0.02348 -0.0575 0.4721 1.0000
7.250 1.0702 0.03464 0.02329 -0.0572 0.4642 1.0000
7.500 1.0755 0.03580 0.02456 -0.0545 0.4526 1.0000
7.750 1.0900 0.03644 0.02526 -0.0528 0.4426 1.0000
8.000 1.1171 0.03636 0.02522 -0.0521 0.4340 1.0000
8.250 1.1192 0.03770 0.02666 -0.0492 0.4231 1.0000
8.500 1.1384 0.03808 0.02711 -0.0478 0.4139 1.0000
8.750 1.1543 0.03864 0.02773 -0.0462 0.4044 1.0000
9.000 1.1565 0.04008 0.02927 -0.0436 0.3944 1.0000
9.250 1.1914 0.03961 0.02880 -0.0436 0.3864 1.0000
9.500 1.1814 0.04186 0.03121 -0.0403 0.3759 1.0000
9.750 1.1952 0.04274 0.03217 -0.0388 0.3672 1.0000
10.000 1.2072 0.04377 0.03328 -0.0373 0.3585 1.0000
10.250 1.2057 0.04584 0.03547 -0.0354 0.3494 1.0000
10.500 1.2322 0.04583 0.03551 -0.0346 0.3417 1.0000
10.750 1.2167 0.04923 0.03906 -0.0326 0.3327 1.0000
11.000 1.2530 0.04837 0.03827 -0.0320 0.3256 1.0000
11.250 1.2235 0.05325 0.04332 -0.0302 0.3166 1.0000
11.500 1.2663 0.05169 0.04181 -0.0294 0.3101 1.0000
11.750 1.2215 0.05855 0.04887 -0.0284 0.3013 1.0000
12.000 1.2698 0.05609 0.04648 -0.0272 0.2950 1.0000
12.250 1.2068 0.06575 0.05630 -0.0276 0.2858 1.0000
12.500 1.2573 0.06253 0.05320 -0.0258 0.2803 1.0000
12.750 1.1722 0.07640 0.06716 -0.0285 0.2698 1.0000
13.000 1.2299 0.07144 0.06236 -0.0258 0.2656 1.0000
13.250 1.1347 0.08865 0.07957 -0.0310 0.2533 1.0000
13.500 1.1885 0.08338 0.07452 -0.0277 0.2504 1.0000
14.000 1.1323 0.09923 0.09048 -0.0322 0.2335 1.0000
14.250 1.0805 0.11252 0.10374 -0.0376 0.2219 1.0000
14.500 1.1183 0.10881 0.10024 -0.0346 0.2195 1.0000
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Polar data table (+)
Polar graphs
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