REPUBLIC S-3 AIRFOIL (s3-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: REPUBLIC S-3 AIRFOIL (s3-il) Reynolds number: 200,000 Max Cl/Cd: 56.63 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3-il-200000.txt Download as CSV file: xf-s3-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: REPUBLIC S-3 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5433 0.08518 0.08188 -0.0121 1.0000 0.0483
-9.000 -0.5540 0.07850 0.07525 -0.0180 1.0000 0.0487
-8.750 -0.5730 0.07236 0.06909 -0.0233 1.0000 0.0489
-8.500 -0.5904 0.06826 0.06494 -0.0244 1.0000 0.0492
-8.250 -0.6000 0.06424 0.06079 -0.0250 1.0000 0.0500
-8.000 -0.6079 0.06051 0.05683 -0.0251 1.0000 0.0522
-7.500 -0.6172 0.05244 0.04806 -0.0233 1.0000 0.0557
-7.250 -0.6015 0.04889 0.04465 -0.0231 1.0000 0.0576
-7.000 -0.5882 0.04642 0.04213 -0.0224 1.0000 0.0605
-6.500 -0.5696 0.04069 0.03577 -0.0194 1.0000 0.0702
-6.250 -0.5538 0.03809 0.03316 -0.0183 1.0000 0.0729
-6.000 -0.5383 0.03187 0.02558 -0.0128 1.0000 0.0432
-5.750 -0.5221 0.02786 0.02151 -0.0112 1.0000 0.0398
-5.500 -0.5070 0.02527 0.01862 -0.0088 1.0000 0.0385
-5.250 -0.4936 0.02388 0.01702 -0.0062 1.0000 0.0398
-5.000 -0.4839 0.02288 0.01583 -0.0032 1.0000 0.0411
-4.750 -0.4419 0.02087 0.01351 -0.0057 0.9936 0.0419
-4.500 -0.4015 0.01863 0.01109 -0.0079 0.9865 0.0437
-4.250 -0.3608 0.01733 0.00985 -0.0108 0.9789 0.0494
-4.000 -0.3177 0.01633 0.00876 -0.0135 0.9717 0.0539
-3.750 -0.2796 0.01491 0.00743 -0.0158 0.9615 0.0624
-3.500 -0.2419 0.01385 0.00639 -0.0177 0.9494 0.0733
-3.250 -0.2075 0.01305 0.00561 -0.0189 0.9348 0.0900
-3.000 -0.1788 0.01222 0.00489 -0.0190 0.9190 0.1269
-2.750 -0.1718 0.00987 0.00451 -0.0157 0.9016 0.5671
-2.500 -0.1507 0.00963 0.00454 -0.0134 0.8862 0.6596
-2.250 -0.1276 0.00958 0.00456 -0.0116 0.8721 0.7074
-2.000 -0.1042 0.00960 0.00457 -0.0099 0.8589 0.7451
-1.750 -0.0810 0.00961 0.00457 -0.0081 0.8456 0.7763
-1.500 -0.0582 0.00963 0.00458 -0.0061 0.8313 0.8044
-1.250 -0.0360 0.00966 0.00460 -0.0039 0.8159 0.8312
-1.000 -0.0139 0.00969 0.00459 -0.0016 0.7997 0.8559
-0.750 0.0096 0.00969 0.00452 0.0002 0.7823 0.8754
-0.500 0.0344 0.00970 0.00443 0.0017 0.7647 0.8929
-0.250 0.0612 0.00974 0.00436 0.0027 0.7477 0.9091
0.000 0.0922 0.00978 0.00430 0.0026 0.7297 0.9222
0.250 0.1266 0.00983 0.00425 0.0018 0.7092 0.9334
0.500 0.1623 0.00989 0.00417 0.0006 0.6874 0.9441
0.750 0.1984 0.00993 0.00411 -0.0008 0.6608 0.9551
1.000 0.2421 0.00997 0.00401 -0.0039 0.6278 0.9610
1.250 0.2809 0.01003 0.00390 -0.0060 0.5850 0.9702
1.500 0.3232 0.01018 0.00377 -0.0089 0.5304 0.9771
1.750 0.3621 0.01044 0.00372 -0.0114 0.4795 0.9854
2.000 0.4022 0.01075 0.00374 -0.0143 0.4388 0.9931
2.250 0.4426 0.01106 0.00380 -0.0174 0.4072 1.0000
2.500 0.4611 0.01124 0.00388 -0.0160 0.3858 1.0000
2.750 0.4796 0.01144 0.00398 -0.0147 0.3664 1.0000
3.000 0.4982 0.01164 0.00408 -0.0132 0.3491 1.0000
3.250 0.5175 0.01187 0.00421 -0.0119 0.3334 1.0000
3.500 0.5375 0.01213 0.00437 -0.0106 0.3190 1.0000
3.750 0.5584 0.01242 0.00459 -0.0095 0.3060 1.0000
4.000 0.5801 0.01274 0.00485 -0.0085 0.2948 1.0000
4.250 0.6022 0.01313 0.00514 -0.0075 0.2857 1.0000
4.500 0.6250 0.01348 0.00544 -0.0067 0.2769 1.0000
4.750 0.6481 0.01386 0.00580 -0.0059 0.2690 1.0000
5.000 0.6715 0.01421 0.00609 -0.0052 0.2610 1.0000
5.250 0.6952 0.01454 0.00643 -0.0045 0.2534 1.0000
5.500 0.7193 0.01488 0.00675 -0.0039 0.2470 1.0000
5.750 0.7436 0.01531 0.00719 -0.0034 0.2418 1.0000
6.000 0.7682 0.01561 0.00756 -0.0029 0.2362 1.0000
6.250 0.7928 0.01600 0.00793 -0.0024 0.2314 1.0000
6.500 0.8173 0.01636 0.00837 -0.0019 0.2260 1.0000
6.750 0.8416 0.01658 0.00865 -0.0014 0.2192 1.0000
7.000 0.8654 0.01680 0.00891 -0.0009 0.2110 1.0000
7.250 0.8892 0.01695 0.00906 -0.0004 0.2024 1.0000
7.500 0.9132 0.01717 0.00943 0.0001 0.1948 1.0000
7.750 0.9366 0.01747 0.00970 0.0006 0.1871 1.0000
8.000 0.9604 0.01759 0.00998 0.0011 0.1773 1.0000
8.250 0.9837 0.01790 0.01035 0.0017 0.1688 1.0000
8.500 1.0063 0.01821 0.01069 0.0022 0.1594 1.0000
8.750 1.0301 0.01841 0.01102 0.0027 0.1475 1.0000
9.000 1.0538 0.01869 0.01140 0.0032 0.1360 1.0000
9.250 1.0771 0.01902 0.01179 0.0037 0.1217 1.0000
9.500 1.0990 0.01951 0.01223 0.0043 0.1014 1.0000
9.750 1.1169 0.02042 0.01299 0.0052 0.0809 1.0000
10.000 1.1342 0.02141 0.01395 0.0063 0.0673 1.0000
10.250 1.1511 0.02241 0.01497 0.0074 0.0553 1.0000
10.500 1.1665 0.02351 0.01609 0.0087 0.0399 1.0000
10.750 1.1774 0.02491 0.01742 0.0103 0.0284 1.0000
11.000 1.1870 0.02630 0.01885 0.0121 0.0252 1.0000
11.250 1.1948 0.02765 0.02036 0.0141 0.0238 1.0000
11.500 1.1965 0.02910 0.02196 0.0167 0.0229 1.0000
11.750 1.1956 0.03076 0.02378 0.0190 0.0221 1.0000
12.000 1.1908 0.03292 0.02608 0.0208 0.0213 1.0000
12.250 1.1859 0.03537 0.02868 0.0217 0.0210 1.0000
12.500 1.1781 0.03842 0.03189 0.0218 0.0206 1.0000
12.750 1.1689 0.04202 0.03564 0.0212 0.0203 1.0000
13.000 1.1586 0.04610 0.03987 0.0199 0.0202 1.0000
13.250 1.1486 0.05055 0.04447 0.0180 0.0201 1.0000
13.500 1.1336 0.05603 0.05010 0.0154 0.0199 1.0000
13.750 1.1233 0.06115 0.05535 0.0129 0.0199 1.0000
14.000 1.1128 0.06638 0.06070 0.0103 0.0198 1.0000
14.250 1.1017 0.07162 0.06604 0.0079 0.0197 1.0000
14.500 1.0930 0.07645 0.07097 0.0057 0.0197 1.0000
14.750 1.0864 0.08088 0.07548 0.0040 0.0196 1.0000
15.000 1.0825 0.08499 0.07967 0.0024 0.0195 1.0000
15.250 1.0794 0.08897 0.08371 0.0010 0.0194 1.0000
15.500 1.0774 0.09290 0.08774 -0.0005 0.0193 1.0000
15.750 1.0763 0.09675 0.09168 -0.0018 0.0193 1.0000
16.000 1.0740 0.10098 0.09602 -0.0036 0.0193 1.0000
16.250 1.0700 0.10563 0.10080 -0.0056 0.0193 1.0000
16.500 1.0668 0.11021 0.10552 -0.0077 0.0193 1.0000
16.750 1.0612 0.11543 0.11087 -0.0102 0.0193 1.0000
17.000 1.0537 0.12119 0.11677 -0.0132 0.0193 1.0000
17.250 1.0460 0.12709 0.12279 -0.0164 0.0194 1.0000
17.500 1.0366 0.13366 0.12952 -0.0202 0.0195 1.0000
17.750 1.0259 0.14083 0.13682 -0.0245 0.0196 1.0000
18.000 1.0160 0.14805 0.14418 -0.0291 0.0198 1.0000
18.250 1.0008 0.15698 0.15327 -0.0347 0.0200 1.0000
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