SPICA 11.73% smoothed (spicasm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SPICA 11.73% smoothed (spicasm-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.17 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-spicasm-il-1000000-n5.txt Download as CSV file: xf-spicasm-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1677 0.08464 0.08201 -0.0800 0.7872 0.0138
-9.750 -0.1655 0.08179 0.07907 -0.0808 0.7654 0.0138
-9.500 -0.1627 0.07906 0.07628 -0.0817 0.7474 0.0139
-9.250 -0.1608 0.07621 0.07338 -0.0826 0.7318 0.0141
-9.000 -0.1601 0.07323 0.07036 -0.0836 0.7175 0.0142
-8.750 -0.1603 0.07024 0.06733 -0.0846 0.7049 0.0146
-8.500 -0.1657 0.06667 0.06375 -0.0859 0.6927 0.0148
-8.250 -0.1784 0.06307 0.06015 -0.0871 0.6827 0.0149
-8.000 -0.1957 0.05730 0.05433 -0.0909 0.6731 0.0155
-7.750 -0.2115 0.04920 0.04611 -0.0952 0.6663 0.0158
-7.500 -0.2487 0.03402 0.03042 -0.0974 0.6618 0.0164
-7.250 -0.2354 0.03135 0.02757 -0.0968 0.6539 0.0166
-7.000 -0.2193 0.02910 0.02514 -0.0961 0.6460 0.0168
-6.750 -0.2292 0.01944 0.01459 -0.0928 0.6406 0.0175
-6.500 -0.2099 0.01765 0.01249 -0.0918 0.6336 0.0178
-6.250 -0.1885 0.01631 0.01089 -0.0909 0.6265 0.0180
-6.000 -0.1656 0.01528 0.00965 -0.0901 0.6203 0.0181
-5.750 -0.1415 0.01444 0.00864 -0.0895 0.6144 0.0183
-5.500 -0.1169 0.01376 0.00781 -0.0889 0.6087 0.0185
-5.250 -0.0917 0.01318 0.00710 -0.0884 0.6037 0.0186
-5.000 -0.0660 0.01267 0.00648 -0.0879 0.5990 0.0188
-4.750 -0.0400 0.01230 0.00602 -0.0875 0.5941 0.0190
-4.500 -0.0140 0.01194 0.00557 -0.0871 0.5895 0.0192
-4.250 0.0124 0.01158 0.00514 -0.0867 0.5854 0.0194
-4.000 0.0388 0.01127 0.00476 -0.0863 0.5813 0.0195
-3.750 0.0652 0.01098 0.00441 -0.0859 0.5772 0.0196
-3.500 0.0905 0.01050 0.00386 -0.0854 0.5732 0.0199
-3.250 0.1168 0.01017 0.00350 -0.0850 0.5694 0.0202
-3.000 0.1433 0.00994 0.00324 -0.0847 0.5654 0.0205
-2.750 0.1698 0.00976 0.00303 -0.0843 0.5611 0.0207
-2.500 0.1964 0.00959 0.00283 -0.0840 0.5573 0.0210
-2.250 0.2234 0.00942 0.00265 -0.0837 0.5536 0.0212
-2.000 0.2503 0.00927 0.00248 -0.0834 0.5491 0.0216
-1.750 0.2770 0.00914 0.00232 -0.0831 0.5446 0.0218
-1.500 0.3038 0.00903 0.00218 -0.0828 0.5405 0.0222
-1.250 0.3310 0.00891 0.00206 -0.0825 0.5361 0.0225
-1.000 0.3580 0.00882 0.00194 -0.0822 0.5312 0.0229
-0.750 0.3848 0.00876 0.00185 -0.0819 0.5263 0.0233
-0.500 0.4120 0.00867 0.00176 -0.0817 0.5214 0.0239
-0.250 0.4388 0.00859 0.00166 -0.0814 0.5145 0.0249
0.000 0.4656 0.00855 0.00160 -0.0811 0.5074 0.0256
0.250 0.4927 0.00852 0.00155 -0.0809 0.4997 0.0266
0.500 0.5195 0.00851 0.00152 -0.0806 0.4934 0.0277
0.750 0.5467 0.00848 0.00149 -0.0804 0.4869 0.0295
1.000 0.5734 0.00847 0.00148 -0.0801 0.4803 0.0348
1.250 0.6002 0.00844 0.00150 -0.0799 0.4737 0.0531
1.500 0.6268 0.00846 0.00152 -0.0796 0.4653 0.0633
2.000 0.6689 0.00730 0.00167 -0.0774 0.4505 0.6035
2.250 0.6817 0.00661 0.00179 -0.0740 0.4432 0.8863
2.500 0.7604 0.00674 0.00196 -0.0852 0.4287 0.9852
2.750 0.8031 0.00690 0.00204 -0.0886 0.4186 0.9964
3.000 0.8431 0.00703 0.00211 -0.0913 0.4083 1.0000
3.250 0.8662 0.00717 0.00219 -0.0904 0.3984 1.0000
3.500 0.8893 0.00731 0.00228 -0.0894 0.3884 1.0000
3.750 0.9129 0.00744 0.00237 -0.0885 0.3796 1.0000
4.000 0.9358 0.00761 0.00249 -0.0876 0.3690 1.0000
4.250 0.9586 0.00780 0.00261 -0.0866 0.3566 1.0000
4.500 0.9817 0.00797 0.00273 -0.0856 0.3451 1.0000
4.750 1.0045 0.00816 0.00287 -0.0847 0.3339 1.0000
5.000 1.0269 0.00838 0.00302 -0.0837 0.3219 1.0000
5.250 1.0492 0.00861 0.00319 -0.0826 0.3095 1.0000
5.500 1.0719 0.00881 0.00336 -0.0817 0.2986 1.0000
5.750 1.0942 0.00904 0.00354 -0.0807 0.2873 1.0000
6.000 1.1163 0.00928 0.00373 -0.0796 0.2773 1.0000
6.250 1.1387 0.00950 0.00392 -0.0787 0.2678 1.0000
6.500 1.1608 0.00973 0.00412 -0.0777 0.2588 1.0000
7.000 1.2045 0.01022 0.00454 -0.0756 0.2415 1.0000
7.250 1.2255 0.01050 0.00479 -0.0744 0.2320 1.0000
7.500 1.2459 0.01082 0.00505 -0.0732 0.2211 1.0000
7.750 1.2661 0.01112 0.00532 -0.0719 0.2098 1.0000
8.000 1.2862 0.01143 0.00559 -0.0706 0.2004 1.0000
8.250 1.3051 0.01179 0.00590 -0.0692 0.1900 1.0000
8.500 1.3253 0.01207 0.00618 -0.0679 0.1819 1.0000
8.750 1.3440 0.01241 0.00649 -0.0665 0.1742 1.0000
9.000 1.3615 0.01279 0.00682 -0.0648 0.1640 1.0000
9.250 1.3776 0.01317 0.00718 -0.0629 0.1539 1.0000
9.500 1.3905 0.01359 0.00756 -0.0604 0.1438 1.0000
9.750 1.4004 0.01414 0.00804 -0.0574 0.1297 1.0000
10.000 1.4089 0.01479 0.00861 -0.0544 0.1144 1.0000
10.250 1.4178 0.01547 0.00923 -0.0515 0.1012 1.0000
10.500 1.4225 0.01639 0.01005 -0.0483 0.0843 1.0000
10.750 1.4271 0.01738 0.01096 -0.0452 0.0688 1.0000
11.000 1.4288 0.01862 0.01212 -0.0421 0.0528 1.0000
11.250 1.4210 0.02058 0.01393 -0.0384 0.0283 1.0000
11.500 1.4235 0.02210 0.01541 -0.0362 0.0189 1.0000
11.750 1.4311 0.02338 0.01672 -0.0347 0.0156 1.0000
12.000 1.4407 0.02458 0.01796 -0.0335 0.0141 1.0000
12.250 1.4497 0.02590 0.01932 -0.0324 0.0130 1.0000
12.500 1.4582 0.02731 0.02077 -0.0314 0.0121 1.0000
12.750 1.4666 0.02878 0.02230 -0.0306 0.0115 1.0000
13.000 1.4754 0.03027 0.02385 -0.0299 0.0111 1.0000
13.250 1.4828 0.03190 0.02554 -0.0292 0.0106 1.0000
13.500 1.4892 0.03367 0.02736 -0.0285 0.0102 1.0000
13.750 1.4944 0.03559 0.02934 -0.0279 0.0098 1.0000
14.000 1.4974 0.03775 0.03155 -0.0273 0.0093 1.0000
14.250 1.5006 0.03993 0.03380 -0.0268 0.0091 1.0000
14.500 1.5054 0.04198 0.03593 -0.0264 0.0088 1.0000
14.750 1.5094 0.04415 0.03816 -0.0261 0.0086 1.0000
15.000 1.5118 0.04652 0.04060 -0.0258 0.0084 1.0000
15.250 1.5129 0.04907 0.04323 -0.0256 0.0082 1.0000
15.500 1.5138 0.05172 0.04595 -0.0255 0.0079 1.0000
15.750 1.5135 0.05451 0.04881 -0.0254 0.0078 1.0000
16.000 1.5116 0.05756 0.05193 -0.0255 0.0075 1.0000
16.250 1.5097 0.06067 0.05512 -0.0256 0.0074 1.0000
16.500 1.5062 0.06402 0.05855 -0.0258 0.0073 1.0000
16.750 1.5027 0.06740 0.06201 -0.0261 0.0072 1.0000
17.000 1.4958 0.07130 0.06600 -0.0265 0.0070 1.0000
17.250 1.4892 0.07524 0.07003 -0.0271 0.0069 1.0000
17.500 1.4856 0.07883 0.07370 -0.0277 0.0068 1.0000
17.750 1.4788 0.08288 0.07785 -0.0284 0.0068 1.0000
18.000 1.4740 0.08672 0.08177 -0.0291 0.0066 1.0000
18.250 1.4670 0.09094 0.08608 -0.0301 0.0065 1.0000
18.500 1.4571 0.09565 0.09089 -0.0312 0.0065 1.0000
18.750 1.4511 0.09981 0.09514 -0.0323 0.0063 1.0000
19.000 1.4431 0.10435 0.09976 -0.0337 0.0062 1.0000
19.250 1.4327 0.10935 0.10487 -0.0352 0.0062 1.0000
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Polar data table (+)
Polar graphs
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