SELIG 3002-099-83 (s3002-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: SELIG 3002-099-83 (s3002-il) Reynolds number: 500,000 Max Cl/Cd: 89.19 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3002-il-500000-n5.txt Download as CSV file: xf-s3002-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SELIG 3002-099-83
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3884 0.08320 0.08090 -0.0365 1.0000 0.0076
-8.750 -0.3923 0.07919 0.07693 -0.0379 1.0000 0.0076
-8.500 -0.4019 0.07458 0.07236 -0.0395 1.0000 0.0076
-8.250 -0.4137 0.06979 0.06765 -0.0417 0.9985 0.0075
-8.000 -0.4047 0.05739 0.05521 -0.0619 0.9798 0.0074
-7.750 -0.4383 0.02057 0.01606 -0.0859 0.9456 0.0078
-7.500 -0.4134 0.01844 0.01351 -0.0864 0.9363 0.0080
-7.000 -0.3617 0.01601 0.01065 -0.0867 0.9182 0.0085
-6.750 -0.3352 0.01537 0.00990 -0.0866 0.9098 0.0088
-6.500 -0.3087 0.01489 0.00931 -0.0865 0.9008 0.0092
-6.250 -0.2822 0.01435 0.00863 -0.0863 0.8927 0.0098
-6.000 -0.2559 0.01366 0.00777 -0.0860 0.8844 0.0104
-5.750 -0.2294 0.01300 0.00696 -0.0858 0.8766 0.0108
-5.500 -0.2029 0.01242 0.00631 -0.0856 0.8688 0.0114
-5.250 -0.1758 0.01205 0.00588 -0.0855 0.8615 0.0120
-5.000 -0.1487 0.01165 0.00540 -0.0854 0.8537 0.0128
-4.750 -0.1213 0.01126 0.00491 -0.0852 0.8467 0.0137
-4.500 -0.0940 0.01088 0.00448 -0.0851 0.8390 0.0148
-4.250 -0.0664 0.01065 0.00422 -0.0850 0.8317 0.0163
-4.000 -0.0387 0.01042 0.00390 -0.0849 0.8236 0.0178
-3.750 -0.0111 0.01006 0.00351 -0.0849 0.8159 0.0194
-3.500 0.0167 0.00983 0.00322 -0.0848 0.8072 0.0212
-3.250 0.0445 0.00960 0.00294 -0.0847 0.7990 0.0234
-3.000 0.0724 0.00939 0.00270 -0.0846 0.7900 0.0261
-2.750 0.1004 0.00922 0.00247 -0.0846 0.7807 0.0290
-2.500 0.1283 0.00904 0.00226 -0.0845 0.7712 0.0332
-2.250 0.1564 0.00886 0.00208 -0.0845 0.7610 0.0418
-2.000 0.1845 0.00862 0.00192 -0.0845 0.7512 0.0708
-1.750 0.2124 0.00840 0.00179 -0.0845 0.7410 0.1128
-1.500 0.2405 0.00817 0.00169 -0.0846 0.7300 0.1661
-1.250 0.2684 0.00784 0.00160 -0.0848 0.7188 0.2524
-1.000 0.2962 0.00739 0.00151 -0.0851 0.7070 0.3897
-0.750 0.3237 0.00692 0.00148 -0.0853 0.6945 0.5468
-0.500 0.3502 0.00671 0.00159 -0.0849 0.6808 0.6682
-0.250 0.3775 0.00675 0.00164 -0.0846 0.6660 0.7089
0.000 0.4050 0.00682 0.00166 -0.0843 0.6503 0.7258
0.250 0.4325 0.00691 0.00168 -0.0841 0.6333 0.7391
0.500 0.4597 0.00702 0.00172 -0.0837 0.6143 0.7557
0.750 0.4865 0.00713 0.00178 -0.0833 0.5939 0.7713
1.000 0.5132 0.00728 0.00183 -0.0830 0.5721 0.7831
1.250 0.5401 0.00743 0.00189 -0.0827 0.5485 0.7921
1.500 0.5668 0.00759 0.00195 -0.0824 0.5250 0.7977
1.750 0.5936 0.00776 0.00202 -0.0821 0.5011 0.8027
2.000 0.6205 0.00796 0.00210 -0.0819 0.4770 0.8076
2.250 0.6471 0.00815 0.00220 -0.0816 0.4533 0.8119
2.500 0.6736 0.00835 0.00231 -0.0814 0.4299 0.8162
2.750 0.7001 0.00856 0.00243 -0.0811 0.4073 0.8209
3.000 0.7267 0.00879 0.00256 -0.0809 0.3854 0.8256
3.250 0.7528 0.00900 0.00271 -0.0806 0.3638 0.8301
3.750 0.8054 0.00945 0.00301 -0.0801 0.3258 0.8406
4.000 0.8314 0.00966 0.00319 -0.0798 0.3081 0.8461
4.250 0.8573 0.00990 0.00337 -0.0794 0.2904 0.8525
4.500 0.8830 0.01013 0.00356 -0.0791 0.2735 0.8591
4.750 0.9084 0.01036 0.00375 -0.0787 0.2573 0.8672
5.000 0.9333 0.01060 0.00397 -0.0782 0.2413 0.8766
5.250 0.9575 0.01085 0.00419 -0.0775 0.2247 0.8895
5.500 0.9803 0.01107 0.00441 -0.0765 0.2093 0.9115
5.750 1.0069 0.01129 0.00463 -0.0764 0.1941 1.0000
6.000 1.0326 0.01164 0.00491 -0.0762 0.1788 1.0000
6.250 1.0580 0.01200 0.00521 -0.0760 0.1643 1.0000
6.500 1.0832 0.01237 0.00553 -0.0757 0.1512 1.0000
6.750 1.1082 0.01274 0.00586 -0.0754 0.1391 1.0000
7.000 1.1330 0.01312 0.00620 -0.0750 0.1272 1.0000
7.250 1.1576 0.01351 0.00655 -0.0747 0.1173 1.0000
7.500 1.1818 0.01392 0.00694 -0.0742 0.1081 1.0000
8.000 1.2294 0.01478 0.00775 -0.0733 0.0899 1.0000
8.250 1.2527 0.01523 0.00820 -0.0727 0.0826 1.0000
8.500 1.2754 0.01572 0.00867 -0.0721 0.0751 1.0000
8.750 1.2982 0.01618 0.00914 -0.0715 0.0690 1.0000
9.000 1.3198 0.01673 0.00967 -0.0707 0.0627 1.0000
9.250 1.3421 0.01720 0.01018 -0.0700 0.0583 1.0000
9.500 1.3627 0.01778 0.01075 -0.0691 0.0531 1.0000
9.750 1.3838 0.01830 0.01131 -0.0683 0.0497 1.0000
10.000 1.4039 0.01886 0.01190 -0.0673 0.0463 1.0000
10.250 1.4224 0.01954 0.01260 -0.0661 0.0429 1.0000
10.500 1.4418 0.02008 0.01321 -0.0650 0.0408 1.0000
10.750 1.4597 0.02070 0.01388 -0.0638 0.0385 1.0000
11.000 1.4747 0.02141 0.01462 -0.0621 0.0363 1.0000
11.250 1.4880 0.02213 0.01539 -0.0601 0.0345 1.0000
11.500 1.5018 0.02279 0.01613 -0.0583 0.0331 1.0000
11.750 1.5143 0.02355 0.01697 -0.0564 0.0317 1.0000
12.000 1.5254 0.02442 0.01789 -0.0545 0.0303 1.0000
12.250 1.5344 0.02546 0.01898 -0.0524 0.0288 1.0000
12.500 1.5440 0.02649 0.02010 -0.0506 0.0277 1.0000
12.750 1.5544 0.02751 0.02122 -0.0490 0.0268 1.0000
13.000 1.5635 0.02867 0.02248 -0.0474 0.0258 1.0000
13.250 1.5714 0.02998 0.02388 -0.0459 0.0248 1.0000
13.500 1.5778 0.03146 0.02544 -0.0445 0.0239 1.0000
13.750 1.5819 0.03322 0.02726 -0.0431 0.0230 1.0000
14.000 1.5863 0.03502 0.02916 -0.0419 0.0222 1.0000
14.250 1.5924 0.03674 0.03100 -0.0410 0.0214 1.0000
14.500 1.5971 0.03867 0.03305 -0.0402 0.0206 1.0000
14.750 1.6009 0.04077 0.03524 -0.0395 0.0196 1.0000
15.000 1.6022 0.04323 0.03778 -0.0391 0.0188 1.0000
15.250 1.6003 0.04617 0.04081 -0.0389 0.0180 1.0000
15.500 1.6002 0.04902 0.04378 -0.0389 0.0174 1.0000
15.750 1.6001 0.05200 0.04690 -0.0392 0.0167 1.0000
16.000 1.5978 0.05542 0.05044 -0.0397 0.0161 1.0000
16.250 1.5934 0.05927 0.05441 -0.0406 0.0155 1.0000
16.500 1.5875 0.06353 0.05878 -0.0419 0.0149 1.0000
16.750 1.5790 0.06841 0.06379 -0.0436 0.0145 1.0000
17.000 1.5683 0.07386 0.06938 -0.0458 0.0143 1.0000
17.250 1.5563 0.07975 0.07540 -0.0483 0.0140 1.0000
17.500 1.5447 0.08577 0.08158 -0.0511 0.0137 1.0000
17.750 1.5313 0.09228 0.08824 -0.0542 0.0135 1.0000
18.000 1.5165 0.09922 0.09534 -0.0577 0.0134 1.0000
18.250 1.5007 0.10651 0.10278 -0.0614 0.0132 1.0000
18.500 1.4845 0.11402 0.11044 -0.0654 0.0130 1.0000
18.750 1.4680 0.12171 0.11827 -0.0697 0.0128 1.0000
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Polar data table (+)
Polar graphs
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