SPICA 11.73% smoothed (spicasm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SPICA 11.73% smoothed (spicasm-il) Reynolds number: 100,000 Max Cl/Cd: 50.89 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-spicasm-il-100000.txt Download as CSV file: xf-spicasm-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2803 0.11123 0.10637 -0.0404 1.0000 0.0785
-9.250 -0.2955 0.11051 0.10577 -0.0427 1.0000 0.0790
-9.000 -0.3115 0.10950 0.10490 -0.0437 1.0000 0.0791
-8.750 -0.2741 0.10143 0.09678 -0.0395 1.0000 0.0812
-8.500 -0.2671 0.09860 0.09401 -0.0378 1.0000 0.0829
-8.250 -0.2686 0.09654 0.09205 -0.0365 1.0000 0.0846
-8.000 -0.2792 0.09527 0.09092 -0.0342 1.0000 0.0859
-7.750 -0.3116 0.09626 0.09212 -0.0281 1.0000 0.0855
-7.500 -0.3116 0.09425 0.09018 -0.0303 0.9943 0.0876
-7.250 -0.2920 0.08948 0.08533 -0.0513 0.9735 0.0928
-7.000 -0.2701 0.08340 0.07922 -0.0584 0.9626 0.0945
-6.750 -0.2385 0.07961 0.07547 -0.0561 0.9591 0.0985
-6.500 -0.2124 0.07543 0.07121 -0.0637 0.9471 0.1049
-6.250 -0.1899 0.06993 0.06553 -0.0757 0.9336 0.1105
-6.000 -0.1558 0.06609 0.06172 -0.0774 0.9292 0.1152
-5.750 -0.1325 0.06211 0.05736 -0.0878 0.9153 0.1258
-5.500 -0.1017 0.05813 0.05350 -0.0883 0.9102 0.1300
-5.250 -0.0788 0.05498 0.05004 -0.0937 0.8982 0.1427
-5.000 -0.0562 0.05215 0.04730 -0.0933 0.8888 0.1483
-4.750 -0.0287 0.04901 0.04398 -0.0965 0.8811 0.1625
-4.500 -0.0122 0.04696 0.04182 -0.0968 0.8694 0.1781
-4.250 0.0106 0.04476 0.03957 -0.0971 0.8613 0.1971
-4.000 0.0279 0.04322 0.03785 -0.0972 0.8512 0.2261
-3.750 0.0453 0.04125 0.03594 -0.0959 0.8423 0.2459
-3.500 0.0640 0.03958 0.03426 -0.0947 0.8343 0.2794
-3.000 0.0935 0.03683 0.03160 -0.0899 0.8179 0.3609
-2.750 0.1058 0.03562 0.03049 -0.0864 0.8094 0.3996
-2.500 0.1925 0.02957 0.02127 -0.0972 0.8028 0.1096
-2.250 0.2188 0.02814 0.01967 -0.0966 0.7959 0.1070
-2.000 0.2430 0.02680 0.01815 -0.0958 0.7880 0.1037
-1.750 0.2752 0.02543 0.01644 -0.0956 0.7829 0.0994
-1.500 0.2959 0.02490 0.01571 -0.0941 0.7737 0.0976
-1.250 0.3267 0.02399 0.01462 -0.0939 0.7681 0.0976
-1.000 0.3488 0.02361 0.01422 -0.0928 0.7598 0.1000
-0.750 0.3768 0.02309 0.01362 -0.0923 0.7534 0.1054
-0.500 0.4012 0.02272 0.01321 -0.0913 0.7463 0.1095
-0.250 0.4243 0.02216 0.01279 -0.0902 0.7389 0.1163
0.000 0.4518 0.02164 0.01225 -0.0895 0.7335 0.1307
0.250 0.4707 0.02151 0.01225 -0.0880 0.7246 0.1608
0.500 0.5653 0.01868 0.01133 -0.0997 0.7194 1.0000
0.750 0.5826 0.01917 0.01170 -0.0979 0.7105 1.0000
1.000 0.6085 0.01930 0.01164 -0.0972 0.7039 1.0000
1.250 0.6268 0.01978 0.01202 -0.0955 0.6953 1.0000
1.500 0.6524 0.01991 0.01201 -0.0947 0.6883 1.0000
1.750 0.6716 0.02035 0.01238 -0.0932 0.6798 1.0000
2.000 0.6974 0.02047 0.01237 -0.0924 0.6724 1.0000
2.250 0.7171 0.02089 0.01274 -0.0909 0.6637 1.0000
2.500 0.7438 0.02095 0.01269 -0.0902 0.6562 1.0000
2.750 0.7633 0.02137 0.01308 -0.0887 0.6470 1.0000
3.000 0.7911 0.02139 0.01299 -0.0882 0.6397 1.0000
3.250 0.8101 0.02183 0.01344 -0.0866 0.6301 1.0000
3.500 0.8392 0.02180 0.01329 -0.0863 0.6231 1.0000
3.750 0.8573 0.02228 0.01380 -0.0846 0.6131 1.0000
4.000 0.8881 0.02218 0.01360 -0.0845 0.6064 1.0000
4.250 0.9051 0.02270 0.01417 -0.0827 0.5958 1.0000
4.500 0.9359 0.02261 0.01397 -0.0826 0.5890 1.0000
4.750 0.9539 0.02303 0.01445 -0.0810 0.5781 1.0000
5.000 0.9777 0.02323 0.01466 -0.0800 0.5691 1.0000
5.250 1.0044 0.02324 0.01463 -0.0794 0.5600 1.0000
5.500 1.0237 0.02361 0.01506 -0.0779 0.5493 1.0000
5.750 1.0559 0.02340 0.01475 -0.0780 0.5415 1.0000
6.000 1.0738 0.02374 0.01518 -0.0762 0.5296 1.0000
6.250 1.0947 0.02399 0.01547 -0.0749 0.5186 1.0000
6.500 1.1250 0.02381 0.01522 -0.0748 0.5096 1.0000
6.750 1.1450 0.02404 0.01552 -0.0733 0.4977 1.0000
7.000 1.1650 0.02430 0.01583 -0.0718 0.4857 1.0000
7.250 1.1884 0.02441 0.01594 -0.0708 0.4745 1.0000
7.500 1.2178 0.02429 0.01574 -0.0706 0.4642 1.0000
7.750 1.2355 0.02464 0.01617 -0.0689 0.4515 1.0000
8.000 1.2546 0.02500 0.01659 -0.0674 0.4391 1.0000
8.250 1.2758 0.02534 0.01694 -0.0662 0.4275 1.0000
8.500 1.3002 0.02560 0.01717 -0.0655 0.4163 1.0000
8.750 1.3221 0.02598 0.01755 -0.0645 0.4048 1.0000
9.000 1.3376 0.02664 0.01832 -0.0626 0.3931 1.0000
9.250 1.3570 0.02723 0.01894 -0.0613 0.3824 1.0000
9.500 1.3830 0.02766 0.01931 -0.0610 0.3721 1.0000
9.750 1.3959 0.02843 0.02023 -0.0589 0.3614 1.0000
10.000 1.4122 0.02921 0.02109 -0.0573 0.3515 1.0000
10.250 1.4371 0.02973 0.02156 -0.0569 0.3415 1.0000
10.500 1.4474 0.03058 0.02258 -0.0544 0.3315 1.0000
10.750 1.4610 0.03136 0.02345 -0.0525 0.3214 1.0000
11.000 1.4797 0.03184 0.02388 -0.0513 0.3104 1.0000
11.250 1.4905 0.03235 0.02443 -0.0489 0.2989 1.0000
11.500 1.4906 0.03319 0.02543 -0.0451 0.2885 1.0000
11.750 1.4948 0.03380 0.02605 -0.0419 0.2778 1.0000
12.000 1.5038 0.03430 0.02647 -0.0394 0.2669 1.0000
12.250 1.4932 0.03545 0.02783 -0.0348 0.2584 1.0000
12.500 1.4928 0.03640 0.02881 -0.0317 0.2488 1.0000
12.750 1.4923 0.03743 0.02987 -0.0290 0.2392 1.0000
13.000 1.4836 0.03912 0.03175 -0.0260 0.2310 1.0000
13.250 1.4843 0.04040 0.03302 -0.0240 0.2219 1.0000
13.500 1.4737 0.04257 0.03542 -0.0218 0.2137 1.0000
13.750 1.4682 0.04458 0.03751 -0.0201 0.2052 1.0000
14.000 1.4597 0.04697 0.04001 -0.0188 0.1963 1.0000
14.250 1.4477 0.04997 0.04319 -0.0178 0.1873 1.0000
14.500 1.4365 0.05304 0.04633 -0.0172 0.1776 1.0000
14.750 1.4216 0.05675 0.05014 -0.0170 0.1672 1.0000
15.000 1.4028 0.06133 0.05486 -0.0174 0.1553 1.0000
15.250 1.3832 0.06637 0.05997 -0.0182 0.1423 1.0000
15.500 1.3620 0.07198 0.06558 -0.0194 0.1287 1.0000
15.750 1.3384 0.07824 0.07178 -0.0210 0.1149 1.0000
16.000 1.3157 0.08473 0.07818 -0.0228 0.1023 1.0000
16.250 1.2951 0.09117 0.08455 -0.0247 0.0912 1.0000
16.500 1.2800 0.09694 0.09030 -0.0264 0.0824 1.0000
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Polar data table (+)
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