SPICA 11.73% smoothed (spicasm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SPICA 11.73% smoothed (spicasm-il) Reynolds number: 500,000 Max Cl/Cd: 112.06 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-spicasm-il-500000.txt Download as CSV file: xf-spicasm-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2711 0.09958 0.09735 -0.0371 1.0000 0.0247
-9.250 -0.2691 0.09704 0.09484 -0.0372 1.0000 0.0252
-9.000 -0.2687 0.09448 0.09232 -0.0373 1.0000 0.0257
-8.750 -0.2552 0.09034 0.08819 -0.0418 0.9972 0.0267
-8.500 -0.2490 0.08311 0.08096 -0.0549 0.9768 0.0278
-8.250 -0.2323 0.07653 0.07438 -0.0643 0.9575 0.0280
-8.000 -0.1996 0.07266 0.07046 -0.0688 0.9435 0.0284
-7.750 -0.1551 0.06794 0.06565 -0.0792 0.9195 0.0289
-7.500 -0.1232 0.06352 0.06102 -0.0884 0.8751 0.0296
-7.250 -0.1167 0.06043 0.05771 -0.0911 0.8357 0.0303
-7.000 -0.1135 0.05725 0.05437 -0.0929 0.8093 0.0311
-6.750 -0.1160 0.04994 0.04660 -0.0987 0.7875 0.0331
-6.500 -0.1124 0.04570 0.04223 -0.0984 0.7719 0.0335
-6.250 -0.0997 0.04380 0.04026 -0.0978 0.7575 0.0338
-6.000 -0.0853 0.04206 0.03842 -0.0973 0.7447 0.0342
-5.750 -0.0700 0.04023 0.03645 -0.0969 0.7332 0.0347
-5.500 -0.0537 0.03818 0.03427 -0.0966 0.7224 0.0355
-5.250 -0.0335 0.03553 0.03105 -0.0957 0.7134 0.0392
-5.000 -0.0223 0.03127 0.02656 -0.0950 0.7051 0.0399
-4.750 -0.0024 0.02975 0.02501 -0.0947 0.6969 0.0405
-4.500 0.0185 0.02853 0.02371 -0.0942 0.6891 0.0413
-4.250 0.0400 0.02722 0.02227 -0.0936 0.6823 0.0426
-4.000 0.0666 0.02740 0.02192 -0.0920 0.6752 0.0466
-3.750 0.0827 0.02340 0.01774 -0.0913 0.6695 0.0480
-3.500 0.1060 0.02216 0.01647 -0.0909 0.6633 0.0489
-3.250 0.1299 0.02116 0.01536 -0.0904 0.6574 0.0504
-3.000 0.1525 0.01720 0.01053 -0.0879 0.6528 0.0403
-2.750 0.1784 0.01599 0.00924 -0.0873 0.6472 0.0379
-2.500 0.2041 0.01479 0.00785 -0.0867 0.6419 0.0371
-2.250 0.2301 0.01365 0.00649 -0.0860 0.6371 0.0362
-2.000 0.2565 0.01289 0.00564 -0.0855 0.6319 0.0362
-1.750 0.2828 0.01234 0.00503 -0.0850 0.6267 0.0365
-1.500 0.3090 0.01196 0.00455 -0.0845 0.6219 0.0371
-1.250 0.3351 0.01158 0.00416 -0.0840 0.6168 0.0378
-1.000 0.3612 0.01129 0.00383 -0.0835 0.6117 0.0386
-0.750 0.3871 0.01104 0.00352 -0.0830 0.6068 0.0399
-0.500 0.4129 0.01077 0.00328 -0.0825 0.6019 0.0419
-0.250 0.4391 0.01060 0.00312 -0.0821 0.5966 0.0439
0.000 0.4656 0.01050 0.00296 -0.0816 0.5916 0.0463
0.250 0.4916 0.01032 0.00280 -0.0812 0.5864 0.0512
0.500 0.5177 0.01014 0.00265 -0.0807 0.5805 0.0624
0.750 0.5431 0.00993 0.00253 -0.0802 0.5748 0.1108
1.000 0.5482 0.00804 0.00265 -0.0760 0.5700 0.7849
1.250 0.6678 0.00786 0.00271 -0.0954 0.5609 1.0000
1.500 0.6915 0.00795 0.00272 -0.0945 0.5558 1.0000
1.750 0.7153 0.00799 0.00274 -0.0936 0.5500 1.0000
2.000 0.7389 0.00807 0.00275 -0.0927 0.5443 1.0000
2.250 0.7629 0.00815 0.00279 -0.0918 0.5388 1.0000
2.500 0.7869 0.00821 0.00283 -0.0910 0.5325 1.0000
2.750 0.8106 0.00832 0.00286 -0.0901 0.5265 1.0000
3.000 0.8347 0.00837 0.00293 -0.0893 0.5199 1.0000
3.250 0.8586 0.00847 0.00298 -0.0885 0.5134 1.0000
3.500 0.8826 0.00856 0.00305 -0.0877 0.5066 1.0000
3.750 0.9064 0.00865 0.00312 -0.0868 0.4988 1.0000
4.000 0.9302 0.00875 0.00320 -0.0860 0.4913 1.0000
4.250 0.9540 0.00886 0.00329 -0.0851 0.4833 1.0000
4.500 0.9776 0.00897 0.00339 -0.0843 0.4749 1.0000
4.750 1.0008 0.00911 0.00349 -0.0833 0.4657 1.0000
5.000 1.0244 0.00924 0.00361 -0.0825 0.4560 1.0000
5.250 1.0472 0.00940 0.00374 -0.0815 0.4464 1.0000
5.500 1.0698 0.00958 0.00389 -0.0805 0.4354 1.0000
5.750 1.0926 0.00975 0.00405 -0.0796 0.4241 1.0000
6.000 1.1148 0.00996 0.00423 -0.0785 0.4127 1.0000
6.250 1.1365 0.01020 0.00443 -0.0774 0.4007 1.0000
6.750 1.1793 0.01071 0.00487 -0.0751 0.3751 1.0000
7.000 1.2005 0.01098 0.00511 -0.0740 0.3616 1.0000
7.250 1.2212 0.01127 0.00538 -0.0727 0.3484 1.0000
7.500 1.2413 0.01159 0.00567 -0.0714 0.3356 1.0000
7.750 1.2607 0.01194 0.00598 -0.0700 0.3223 1.0000
8.000 1.2792 0.01232 0.00631 -0.0685 0.3083 1.0000
8.250 1.2971 0.01273 0.00667 -0.0669 0.2949 1.0000
8.500 1.3141 0.01315 0.00705 -0.0651 0.2807 1.0000
9.000 1.3484 0.01395 0.00780 -0.0617 0.2578 1.0000
9.250 1.3632 0.01436 0.00821 -0.0596 0.2492 1.0000
9.500 1.3763 0.01480 0.00864 -0.0571 0.2399 1.0000
9.750 1.3909 0.01520 0.00906 -0.0550 0.2313 1.0000
10.000 1.4024 0.01574 0.00956 -0.0525 0.2220 1.0000
10.250 1.4163 0.01621 0.01006 -0.0505 0.2126 1.0000
10.500 1.4294 0.01674 0.01060 -0.0484 0.2051 1.0000
10.750 1.4401 0.01740 0.01124 -0.0461 0.1953 1.0000
11.000 1.4532 0.01798 0.01185 -0.0442 0.1861 1.0000
11.250 1.4627 0.01876 0.01262 -0.0420 0.1744 1.0000
11.500 1.4709 0.01966 0.01350 -0.0398 0.1624 1.0000
11.750 1.4772 0.02074 0.01454 -0.0376 0.1482 1.0000
12.000 1.4804 0.02211 0.01584 -0.0354 0.1315 1.0000
12.250 1.4792 0.02388 0.01752 -0.0330 0.1133 1.0000
12.500 1.4731 0.02619 0.01969 -0.0307 0.0905 1.0000
12.750 1.4625 0.02905 0.02242 -0.0285 0.0670 1.0000
13.250 1.4343 0.03603 0.02919 -0.0252 0.0301 1.0000
13.500 1.4301 0.03885 0.03204 -0.0243 0.0260 1.0000
13.750 1.4264 0.04170 0.03496 -0.0236 0.0237 1.0000
14.000 1.4264 0.04427 0.03762 -0.0231 0.0225 1.0000
14.250 1.4235 0.04719 0.04061 -0.0227 0.0214 1.0000
14.500 1.4186 0.05044 0.04395 -0.0225 0.0206 1.0000
14.750 1.4108 0.05411 0.04771 -0.0224 0.0198 1.0000
15.000 1.4094 0.05715 0.05086 -0.0224 0.0191 1.0000
15.250 1.4059 0.06051 0.05433 -0.0226 0.0187 1.0000
15.500 1.4012 0.06411 0.05803 -0.0229 0.0183 1.0000
15.750 1.3947 0.06801 0.06203 -0.0234 0.0178 1.0000
16.000 1.3878 0.07207 0.06619 -0.0240 0.0175 1.0000
16.250 1.3792 0.07649 0.07071 -0.0249 0.0172 1.0000
16.500 1.3697 0.08111 0.07542 -0.0259 0.0169 1.0000
16.750 1.3571 0.08628 0.08070 -0.0271 0.0166 1.0000
17.000 1.3452 0.09145 0.08596 -0.0285 0.0164 1.0000
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Polar data table (+)
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