REPUBLIC S-3 AIRFOIL (s3-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: REPUBLIC S-3 AIRFOIL (s3-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.48 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3-il-1000000-n5.txt Download as CSV file: xf-s3-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.9608 0.04143 0.03912 -0.0380 1.0000 0.0034
-12.250 -0.9832 0.03743 0.03490 -0.0364 1.0000 0.0034
-12.000 -1.0006 0.03431 0.03154 -0.0329 1.0000 0.0034
-11.750 -1.0041 0.03151 0.02848 -0.0305 1.0000 0.0035
-11.500 -1.0005 0.02912 0.02585 -0.0286 1.0000 0.0035
-11.250 -0.9903 0.02729 0.02383 -0.0271 1.0000 0.0036
-11.000 -0.9774 0.02568 0.02203 -0.0257 1.0000 0.0036
-10.750 -0.9625 0.02422 0.02040 -0.0244 1.0000 0.0037
-10.500 -0.9465 0.02283 0.01883 -0.0232 1.0000 0.0037
-10.250 -0.9302 0.02137 0.01718 -0.0219 1.0000 0.0038
-10.000 -0.9136 0.01989 0.01552 -0.0206 1.0000 0.0039
-9.750 -0.8942 0.01881 0.01431 -0.0196 1.0000 0.0040
-9.500 -0.8734 0.01794 0.01334 -0.0187 1.0000 0.0041
-9.250 -0.8513 0.01726 0.01259 -0.0179 1.0000 0.0042
-9.000 -0.8287 0.01664 0.01191 -0.0171 1.0000 0.0043
-8.750 -0.8064 0.01600 0.01120 -0.0163 1.0000 0.0044
-8.500 -0.7796 0.01537 0.01049 -0.0163 0.9906 0.0046
-8.250 -0.7430 0.01462 0.00964 -0.0186 0.9688 0.0048
-8.000 -0.7080 0.01396 0.00886 -0.0203 0.9422 0.0050
-7.750 -0.6824 0.01351 0.00828 -0.0199 0.9118 0.0052
-7.500 -0.6593 0.01311 0.00773 -0.0189 0.8843 0.0053
-7.250 -0.6358 0.01273 0.00721 -0.0180 0.8588 0.0055
-7.000 -0.6118 0.01239 0.00673 -0.0172 0.8334 0.0057
-6.750 -0.5884 0.01191 0.00612 -0.0164 0.8063 0.0061
-6.500 -0.5637 0.01164 0.00574 -0.0157 0.7820 0.0065
-6.250 -0.5384 0.01136 0.00536 -0.0152 0.7636 0.0069
-6.000 -0.5127 0.01108 0.00499 -0.0147 0.7496 0.0073
-5.750 -0.4868 0.01082 0.00464 -0.0143 0.7370 0.0077
-5.500 -0.4606 0.01058 0.00431 -0.0139 0.7255 0.0081
-5.250 -0.4345 0.01027 0.00393 -0.0135 0.7153 0.0087
-5.000 -0.4081 0.01000 0.00361 -0.0132 0.7078 0.0096
-4.750 -0.3812 0.00978 0.00337 -0.0130 0.7006 0.0107
-4.500 -0.3542 0.00960 0.00314 -0.0127 0.6934 0.0117
-4.250 -0.3273 0.00938 0.00287 -0.0124 0.6839 0.0135
-4.000 -0.3001 0.00919 0.00266 -0.0122 0.6755 0.0160
-3.750 -0.2731 0.00903 0.00247 -0.0120 0.6629 0.0200
-3.500 -0.2459 0.00890 0.00231 -0.0118 0.6439 0.0251
-3.250 -0.2188 0.00877 0.00215 -0.0115 0.6250 0.0310
-3.000 -0.1913 0.00868 0.00200 -0.0114 0.6097 0.0348
-2.750 -0.1641 0.00858 0.00187 -0.0112 0.5915 0.0420
-2.500 -0.1367 0.00853 0.00174 -0.0110 0.5667 0.0472
-2.250 -0.1101 0.00852 0.00163 -0.0108 0.5270 0.0579
-2.000 -0.0840 0.00860 0.00155 -0.0105 0.4670 0.0744
-1.750 -0.0582 0.00855 0.00146 -0.0102 0.4241 0.1138
-1.500 -0.0347 0.00792 0.00127 -0.0097 0.4046 0.2743
-1.250 -0.0092 0.00759 0.00117 -0.0094 0.3910 0.3607
-1.000 0.0168 0.00733 0.00112 -0.0091 0.3789 0.4413
-0.750 0.0435 0.00719 0.00109 -0.0089 0.3662 0.4916
-0.500 0.0703 0.00708 0.00108 -0.0087 0.3514 0.5395
-0.250 0.0972 0.00703 0.00107 -0.0085 0.3341 0.5768
0.250 0.1505 0.00699 0.00111 -0.0080 0.2961 0.6524
0.500 0.1780 0.00705 0.00114 -0.0078 0.2819 0.6688
0.750 0.2053 0.00709 0.00118 -0.0077 0.2711 0.6890
1.000 0.2324 0.00712 0.00123 -0.0075 0.2620 0.7145
1.250 0.2597 0.00714 0.00128 -0.0073 0.2546 0.7368
1.500 0.2872 0.00720 0.00134 -0.0072 0.2466 0.7512
1.750 0.3149 0.00727 0.00140 -0.0071 0.2393 0.7621
2.000 0.3424 0.00735 0.00146 -0.0070 0.2296 0.7734
2.250 0.3700 0.00743 0.00153 -0.0069 0.2198 0.7850
2.500 0.3971 0.00755 0.00161 -0.0067 0.2049 0.7959
2.750 0.4241 0.00769 0.00170 -0.0065 0.1907 0.8061
3.000 0.4513 0.00780 0.00179 -0.0064 0.1828 0.8166
3.250 0.4786 0.00788 0.00189 -0.0063 0.1777 0.8276
3.500 0.5055 0.00799 0.00200 -0.0061 0.1722 0.8389
3.750 0.5325 0.00807 0.00211 -0.0059 0.1678 0.8519
4.000 0.5593 0.00815 0.00223 -0.0056 0.1642 0.8660
4.250 0.5858 0.00824 0.00235 -0.0053 0.1611 0.8818
4.500 0.6121 0.00834 0.00249 -0.0050 0.1566 0.8992
4.750 0.6389 0.00841 0.00262 -0.0047 0.1542 0.9191
5.000 0.6679 0.00849 0.00276 -0.0049 0.1521 0.9408
5.250 0.7018 0.00865 0.00292 -0.0063 0.1456 0.9605
5.500 0.7389 0.00884 0.00310 -0.0085 0.1392 0.9772
5.750 0.7753 0.00907 0.00328 -0.0106 0.1279 0.9910
6.000 0.8056 0.00959 0.00358 -0.0116 0.0914 1.0000
6.250 0.8271 0.01020 0.00403 -0.0107 0.0633 1.0000
6.500 0.8513 0.01053 0.00433 -0.0101 0.0559 1.0000
6.750 0.8758 0.01083 0.00461 -0.0096 0.0489 1.0000
7.000 0.8961 0.01167 0.00523 -0.0086 0.0177 1.0000
7.250 0.9202 0.01206 0.00565 -0.0081 0.0121 1.0000
7.500 0.9448 0.01237 0.00600 -0.0076 0.0103 1.0000
7.750 0.9694 0.01269 0.00635 -0.0072 0.0091 1.0000
8.000 0.9933 0.01309 0.00678 -0.0067 0.0078 1.0000
8.250 1.0174 0.01346 0.00719 -0.0062 0.0071 1.0000
8.500 1.0415 0.01382 0.00759 -0.0058 0.0065 1.0000
8.750 1.0651 0.01422 0.00802 -0.0053 0.0060 1.0000
9.000 1.0881 0.01468 0.00853 -0.0047 0.0055 1.0000
9.250 1.1106 0.01519 0.00908 -0.0041 0.0050 1.0000
9.500 1.1332 0.01565 0.00959 -0.0035 0.0047 1.0000
9.750 1.1555 0.01612 0.01011 -0.0029 0.0044 1.0000
10.000 1.1772 0.01664 0.01067 -0.0022 0.0041 1.0000
10.250 1.1984 0.01717 0.01125 -0.0015 0.0039 1.0000
10.500 1.2182 0.01781 0.01193 -0.0006 0.0037 1.0000
10.750 1.2356 0.01864 0.01285 0.0006 0.0034 1.0000
11.000 1.2542 0.01931 0.01360 0.0016 0.0033 1.0000
11.250 1.2718 0.01999 0.01436 0.0027 0.0032 1.0000
11.500 1.2881 0.02073 0.01517 0.0039 0.0032 1.0000
11.750 1.3026 0.02153 0.01605 0.0053 0.0030 1.0000
12.000 1.3128 0.02245 0.01706 0.0073 0.0029 1.0000
12.250 1.3220 0.02320 0.01787 0.0096 0.0028 1.0000
12.500 1.3269 0.02423 0.01898 0.0121 0.0027 1.0000
12.750 1.3339 0.02523 0.02005 0.0139 0.0026 1.0000
13.000 1.3364 0.02666 0.02157 0.0157 0.0025 1.0000
13.250 1.3394 0.02822 0.02323 0.0169 0.0025 1.0000
13.500 1.3448 0.02975 0.02482 0.0176 0.0024 1.0000
13.750 1.3438 0.03205 0.02723 0.0181 0.0024 1.0000
14.000 1.3403 0.03485 0.03014 0.0180 0.0023 1.0000
14.250 1.3296 0.03873 0.03416 0.0172 0.0023 1.0000
14.500 1.3180 0.04313 0.03870 0.0158 0.0022 1.0000
14.750 1.3012 0.04870 0.04442 0.0133 0.0022 1.0000
15.000 1.2882 0.05427 0.05013 0.0104 0.0022 1.0000
15.250 1.2676 0.06144 0.05746 0.0066 0.0022 1.0000
15.500 1.2380 0.07007 0.06625 0.0022 0.0022 1.0000
15.750 1.2285 0.07537 0.07165 -0.0003 0.0022 1.0000
16.000 1.1933 0.08506 0.08148 -0.0050 0.0022 1.0000
16.250 1.1814 0.09097 0.08749 -0.0079 0.0023 1.0000
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Polar data table (+)
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