SPICA 11.73% smoothed (spicasm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SPICA 11.73% smoothed (spicasm-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.73 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-spicasm-il-1000000.txt Download as CSV file: xf-spicasm-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3240 0.13326 0.13151 -0.0287 1.0000 0.0159
-12.250 -0.3250 0.12914 0.12740 -0.0309 1.0000 0.0160
-12.000 -0.3227 0.12555 0.12382 -0.0323 1.0000 0.0160
-11.750 -0.3173 0.12182 0.12010 -0.0323 1.0000 0.0162
-11.500 -0.3113 0.11904 0.11733 -0.0327 1.0000 0.0163
-11.250 -0.3035 0.11692 0.11522 -0.0326 1.0000 0.0165
-11.000 -0.2983 0.11427 0.11259 -0.0332 1.0000 0.0166
-10.750 -0.2931 0.11176 0.11009 -0.0336 1.0000 0.0168
-10.500 -0.2885 0.10916 0.10750 -0.0341 1.0000 0.0171
-10.250 -0.1817 0.09217 0.09062 -0.0500 0.9731 0.0193
-10.000 -0.1669 0.08581 0.08423 -0.0565 0.9605 0.0194
-9.750 -0.1419 0.07873 0.07709 -0.0643 0.9456 0.0197
-9.500 -0.1029 0.07299 0.07123 -0.0736 0.9148 0.0199
-9.250 -0.0895 0.06990 0.06784 -0.0761 0.8514 0.0202
-9.000 -0.0879 0.06740 0.06520 -0.0759 0.8167 0.0204
-8.750 -0.0858 0.06473 0.06243 -0.0761 0.7933 0.0206
-8.500 -0.0847 0.06185 0.05947 -0.0766 0.7732 0.0209
-8.250 -0.0846 0.05880 0.05637 -0.0772 0.7564 0.0213
-8.000 -0.0858 0.05562 0.05314 -0.0779 0.7414 0.0217
-7.750 -0.1284 0.06355 0.06109 -0.0889 0.7744 0.0212
-7.500 -0.1322 0.06054 0.05800 -0.0903 0.7540 0.0215
-7.250 -0.1319 0.05686 0.05424 -0.0925 0.7377 0.0221
-7.000 -0.1345 0.04871 0.04586 -0.0977 0.7245 0.0233
-6.750 -0.1414 0.04197 0.03890 -0.0984 0.7136 0.0237
-6.500 -0.1294 0.03981 0.03661 -0.0979 0.7016 0.0238
-6.250 -0.1142 0.03810 0.03481 -0.0976 0.6910 0.0240
-6.000 -0.0978 0.03640 0.03300 -0.0972 0.6814 0.0243
-5.750 -0.0810 0.03450 0.03097 -0.0967 0.6724 0.0247
-5.500 -0.0632 0.03245 0.02877 -0.0962 0.6645 0.0252
-5.250 -0.0451 0.03008 0.02622 -0.0955 0.6570 0.0262
-5.000 -0.0361 0.02368 0.01914 -0.0930 0.6515 0.0284
-4.750 -0.0140 0.02258 0.01797 -0.0925 0.6446 0.0287
-4.500 0.0085 0.02172 0.01700 -0.0919 0.6381 0.0290
-4.250 0.0323 0.02096 0.01618 -0.0915 0.6326 0.0296
-4.000 0.0475 0.01590 0.01031 -0.0886 0.6279 0.0285
-3.750 0.0726 0.01544 0.00982 -0.0882 0.6223 0.0291
-3.500 0.0956 0.01281 0.00681 -0.0869 0.6179 0.0257
-3.250 0.1213 0.01191 0.00576 -0.0863 0.6130 0.0255
-3.000 0.1470 0.01131 0.00505 -0.0858 0.6081 0.0256
-2.750 0.1734 0.01092 0.00459 -0.0854 0.6035 0.0260
-2.500 0.2000 0.01053 0.00416 -0.0850 0.5990 0.0265
-2.250 0.2262 0.01017 0.00374 -0.0845 0.5944 0.0269
-2.000 0.2522 0.00992 0.00342 -0.0840 0.5895 0.0273
-1.750 0.2791 0.00965 0.00314 -0.0837 0.5855 0.0276
-1.500 0.3059 0.00948 0.00294 -0.0833 0.5808 0.0279
-1.250 0.3308 0.00908 0.00249 -0.0827 0.5762 0.0286
-1.000 0.3571 0.00889 0.00227 -0.0823 0.5719 0.0293
-0.750 0.3841 0.00873 0.00212 -0.0820 0.5675 0.0301
-0.500 0.4109 0.00863 0.00200 -0.0817 0.5626 0.0311
-0.250 0.4375 0.00858 0.00190 -0.0813 0.5572 0.0324
0.000 0.4648 0.00845 0.00178 -0.0811 0.5518 0.0341
0.250 0.4915 0.00837 0.00170 -0.0807 0.5461 0.0371
0.500 0.5182 0.00833 0.00165 -0.0804 0.5411 0.0425
0.750 0.5455 0.00821 0.00162 -0.0802 0.5367 0.0630
1.000 0.5723 0.00815 0.00160 -0.0799 0.5314 0.0828
1.250 0.5951 0.00769 0.00163 -0.0791 0.5261 0.2971
1.500 0.6054 0.00639 0.00173 -0.0758 0.5221 0.7920
1.750 0.6964 0.00623 0.00193 -0.0893 0.5139 0.9931
2.000 0.7536 0.00630 0.00193 -0.0958 0.5067 1.0000
2.250 0.7775 0.00635 0.00195 -0.0949 0.5005 1.0000
2.500 0.8010 0.00644 0.00198 -0.0940 0.4942 1.0000
2.750 0.8254 0.00649 0.00201 -0.0932 0.4872 1.0000
3.000 0.8487 0.00659 0.00206 -0.0923 0.4794 1.0000
3.250 0.8731 0.00666 0.00211 -0.0915 0.4721 1.0000
3.500 0.8965 0.00678 0.00217 -0.0906 0.4638 1.0000
3.750 0.9207 0.00687 0.00224 -0.0899 0.4549 1.0000
4.000 0.9442 0.00699 0.00232 -0.0890 0.4458 1.0000
4.250 0.9676 0.00713 0.00241 -0.0881 0.4358 1.0000
4.500 0.9914 0.00726 0.00252 -0.0873 0.4260 1.0000
4.750 1.0145 0.00742 0.00263 -0.0863 0.4156 1.0000
5.000 1.0375 0.00760 0.00276 -0.0854 0.4044 1.0000
5.250 1.0609 0.00776 0.00288 -0.0845 0.3934 1.0000
5.500 1.0839 0.00794 0.00303 -0.0836 0.3816 1.0000
5.750 1.1065 0.00815 0.00319 -0.0826 0.3697 1.0000
6.000 1.1288 0.00838 0.00336 -0.0816 0.3565 1.0000
6.500 1.1734 0.00884 0.00374 -0.0796 0.3306 1.0000
6.750 1.1952 0.00909 0.00394 -0.0786 0.3180 1.0000
7.000 1.2165 0.00936 0.00416 -0.0774 0.3044 1.0000
7.250 1.2371 0.00967 0.00441 -0.0762 0.2895 1.0000
7.500 1.2575 0.00999 0.00467 -0.0749 0.2752 1.0000
7.750 1.2774 0.01033 0.00494 -0.0736 0.2608 1.0000
8.000 1.2974 0.01066 0.00523 -0.0723 0.2485 1.0000
8.250 1.3172 0.01099 0.00552 -0.0710 0.2386 1.0000
8.500 1.3381 0.01126 0.00577 -0.0698 0.2303 1.0000
8.750 1.3572 0.01160 0.00608 -0.0684 0.2205 1.0000
9.000 1.3755 0.01196 0.00641 -0.0669 0.2101 1.0000
9.250 1.3951 0.01225 0.00670 -0.0655 0.2026 1.0000
9.500 1.4119 0.01264 0.00706 -0.0638 0.1931 1.0000
9.750 1.4279 0.01299 0.00739 -0.0618 0.1839 1.0000
10.000 1.4420 0.01337 0.00775 -0.0595 0.1749 1.0000
10.250 1.4535 0.01386 0.00819 -0.0568 0.1623 1.0000
10.500 1.4638 0.01443 0.00870 -0.0541 0.1480 1.0000
10.750 1.4724 0.01512 0.00931 -0.0512 0.1325 1.0000
11.000 1.4782 0.01598 0.01006 -0.0481 0.1158 1.0000
11.250 1.4813 0.01702 0.01101 -0.0449 0.0968 1.0000
11.500 1.4774 0.01855 0.01239 -0.0411 0.0728 1.0000
11.750 1.4720 0.02036 0.01407 -0.0376 0.0514 1.0000
12.000 1.4600 0.02289 0.01644 -0.0343 0.0274 1.0000
12.250 1.4604 0.02478 0.01832 -0.0324 0.0204 1.0000
12.500 1.4666 0.02635 0.01993 -0.0312 0.0182 1.0000
12.750 1.4720 0.02805 0.02167 -0.0301 0.0168 1.0000
13.000 1.4782 0.02974 0.02344 -0.0292 0.0157 1.0000
13.250 1.4845 0.03148 0.02524 -0.0284 0.0151 1.0000
13.500 1.4889 0.03343 0.02725 -0.0276 0.0144 1.0000
13.750 1.4910 0.03565 0.02954 -0.0269 0.0137 1.0000
14.000 1.4905 0.03817 0.03213 -0.0263 0.0132 1.0000
14.250 1.4919 0.04054 0.03460 -0.0257 0.0129 1.0000
14.500 1.4948 0.04283 0.03696 -0.0254 0.0127 1.0000
14.750 1.4971 0.04521 0.03941 -0.0251 0.0123 1.0000
15.000 1.4964 0.04795 0.04224 -0.0248 0.0120 1.0000
15.250 1.4971 0.05060 0.04496 -0.0247 0.0117 1.0000
15.500 1.4956 0.05356 0.04799 -0.0246 0.0114 1.0000
15.750 1.4905 0.05699 0.05151 -0.0246 0.0112 1.0000
16.000 1.4859 0.06044 0.05505 -0.0248 0.0110 1.0000
16.250 1.4783 0.06435 0.05906 -0.0251 0.0109 1.0000
16.500 1.4670 0.06879 0.06359 -0.0256 0.0106 1.0000
16.750 1.4523 0.07382 0.06874 -0.0263 0.0104 1.0000
17.000 1.4465 0.07774 0.07275 -0.0269 0.0103 1.0000
17.250 1.4414 0.08160 0.07670 -0.0276 0.0102 1.0000
17.500 1.4332 0.08596 0.08116 -0.0285 0.0102 1.0000
17.750 1.4265 0.09020 0.08549 -0.0294 0.0100 1.0000
18.000 1.4189 0.09461 0.08999 -0.0305 0.0099 1.0000
18.250 1.4086 0.09945 0.09493 -0.0318 0.0099 1.0000
18.500 1.3985 0.10437 0.09994 -0.0332 0.0097 1.0000
18.750 1.3923 0.10875 0.10440 -0.0345 0.0095 1.0000
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Polar data table (+)
Polar graphs
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