REPUBLIC S-3 AIRFOIL (s3-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: REPUBLIC S-3 AIRFOIL (s3-il) Reynolds number: 100,000 Max Cl/Cd: 42.68 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3-il-100000-n5.txt Download as CSV file: xf-s3-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5313 0.09160 0.08686 -0.0108 1.0000 0.0236
-9.500 -0.5351 0.08593 0.08123 -0.0144 1.0000 0.0233
-9.250 -0.5424 0.07911 0.07446 -0.0196 1.0000 0.0229
-9.000 -0.5553 0.07284 0.06818 -0.0247 1.0000 0.0226
-8.750 -0.5716 0.06792 0.06324 -0.0273 1.0000 0.0224
-8.500 -0.5847 0.06379 0.05902 -0.0278 1.0000 0.0221
-8.250 -0.5927 0.05951 0.05458 -0.0280 1.0000 0.0220
-8.000 -0.5960 0.05541 0.05022 -0.0277 1.0000 0.0220
-7.750 -0.5956 0.05137 0.04591 -0.0270 1.0000 0.0224
-7.500 -0.5916 0.04751 0.04172 -0.0259 1.0000 0.0229
-7.250 -0.5843 0.04382 0.03767 -0.0246 1.0000 0.0234
-7.000 -0.5745 0.04031 0.03374 -0.0231 1.0000 0.0239
-6.750 -0.5622 0.03704 0.03006 -0.0214 1.0000 0.0241
-6.500 -0.5478 0.03405 0.02664 -0.0197 1.0000 0.0244
-6.250 -0.5313 0.03140 0.02356 -0.0179 1.0000 0.0249
-6.000 -0.5139 0.02906 0.02087 -0.0162 1.0000 0.0257
-5.750 -0.4968 0.02752 0.01928 -0.0149 1.0000 0.0272
-5.500 -0.4789 0.02637 0.01802 -0.0134 1.0000 0.0294
-5.250 -0.4608 0.02488 0.01634 -0.0117 1.0000 0.0311
-5.000 -0.4432 0.02345 0.01471 -0.0097 1.0000 0.0327
-4.750 -0.4109 0.02191 0.01304 -0.0108 0.9914 0.0359
-4.500 -0.3734 0.02076 0.01189 -0.0131 0.9801 0.0411
-4.250 -0.3361 0.01951 0.01054 -0.0149 0.9691 0.0467
-4.000 -0.3003 0.01850 0.00954 -0.0168 0.9571 0.0561
-3.750 -0.2671 0.01761 0.00861 -0.0180 0.9436 0.0675
-3.500 -0.2343 0.01685 0.00780 -0.0191 0.9298 0.0829
-3.250 -0.2029 0.01612 0.00706 -0.0199 0.9156 0.1055
-3.000 -0.1803 0.01435 0.00629 -0.0197 0.9001 0.3024
-2.750 -0.1607 0.01330 0.00625 -0.0179 0.8843 0.5463
-2.500 -0.1361 0.01307 0.00622 -0.0163 0.8688 0.6305
-2.250 -0.1119 0.01298 0.00621 -0.0146 0.8530 0.6911
-2.000 -0.0885 0.01297 0.00621 -0.0125 0.8361 0.7411
-1.750 -0.0657 0.01299 0.00621 -0.0102 0.8190 0.7850
-1.500 -0.0406 0.01300 0.00613 -0.0086 0.8026 0.8137
-1.250 -0.0136 0.01297 0.00598 -0.0077 0.7874 0.8324
-1.000 0.0145 0.01295 0.00585 -0.0071 0.7727 0.8493
-0.750 0.0433 0.01294 0.00571 -0.0067 0.7576 0.8650
-0.500 0.0728 0.01294 0.00558 -0.0065 0.7418 0.8797
-0.250 0.1031 0.01294 0.00547 -0.0065 0.7233 0.8940
0.000 0.1342 0.01295 0.00534 -0.0067 0.7013 0.9079
0.250 0.1663 0.01296 0.00521 -0.0072 0.6758 0.9212
0.500 0.1999 0.01298 0.00508 -0.0081 0.6462 0.9341
0.750 0.2346 0.01300 0.00496 -0.0093 0.6126 0.9462
1.000 0.2704 0.01305 0.00483 -0.0107 0.5762 0.9578
1.250 0.3069 0.01315 0.00469 -0.0124 0.5330 0.9686
1.500 0.3437 0.01332 0.00460 -0.0143 0.4904 0.9791
2.000 0.4145 0.01380 0.00460 -0.0181 0.4269 1.0000
2.250 0.4337 0.01406 0.00470 -0.0167 0.4070 1.0000
2.500 0.4537 0.01431 0.00484 -0.0155 0.3882 1.0000
2.750 0.4745 0.01458 0.00501 -0.0144 0.3705 1.0000
3.000 0.4957 0.01485 0.00519 -0.0134 0.3536 1.0000
3.250 0.5175 0.01513 0.00540 -0.0125 0.3381 1.0000
3.500 0.5396 0.01542 0.00562 -0.0116 0.3243 1.0000
3.750 0.5621 0.01574 0.00586 -0.0107 0.3123 1.0000
4.000 0.5847 0.01608 0.00614 -0.0099 0.3019 1.0000
4.250 0.6079 0.01643 0.00645 -0.0092 0.2920 1.0000
4.500 0.6313 0.01680 0.00679 -0.0085 0.2834 1.0000
4.750 0.6547 0.01721 0.00717 -0.0078 0.2758 1.0000
5.000 0.6786 0.01763 0.00759 -0.0072 0.2686 1.0000
5.250 0.7024 0.01806 0.00801 -0.0067 0.2617 1.0000
5.500 0.7265 0.01852 0.00847 -0.0061 0.2557 1.0000
5.750 0.7508 0.01897 0.00901 -0.0057 0.2498 1.0000
6.000 0.7748 0.01945 0.00948 -0.0052 0.2445 1.0000
6.250 0.7990 0.01989 0.01003 -0.0047 0.2377 1.0000
6.500 0.8227 0.02031 0.01051 -0.0042 0.2307 1.0000
6.750 0.8464 0.02073 0.01103 -0.0037 0.2234 1.0000
7.000 0.8697 0.02111 0.01148 -0.0032 0.2157 1.0000
7.250 0.8931 0.02155 0.01204 -0.0026 0.2091 1.0000
7.500 0.9163 0.02196 0.01257 -0.0021 0.2025 1.0000
7.750 0.9387 0.02234 0.01309 -0.0015 0.1935 1.0000
8.000 0.9601 0.02268 0.01348 -0.0009 0.1827 1.0000
8.250 0.9815 0.02308 0.01398 -0.0002 0.1718 1.0000
8.500 1.0024 0.02350 0.01450 0.0004 0.1580 1.0000
8.750 1.0235 0.02398 0.01509 0.0010 0.1439 1.0000
9.000 1.0449 0.02451 0.01575 0.0017 0.1305 1.0000
9.250 1.0653 0.02512 0.01647 0.0023 0.1085 1.0000
9.500 1.0814 0.02610 0.01730 0.0033 0.0860 1.0000
9.750 1.0966 0.02724 0.01842 0.0044 0.0739 1.0000
10.000 1.1086 0.02868 0.01986 0.0057 0.0584 1.0000
10.250 1.1189 0.03020 0.02140 0.0071 0.0309 1.0000
10.500 1.1183 0.03258 0.02363 0.0091 0.0228 1.0000
10.750 1.1193 0.03444 0.02561 0.0112 0.0209 1.0000
11.000 1.1178 0.03639 0.02774 0.0132 0.0201 1.0000
11.250 1.1145 0.03864 0.03018 0.0146 0.0195 1.0000
11.500 1.1097 0.04126 0.03299 0.0153 0.0192 1.0000
11.750 1.1005 0.04466 0.03660 0.0151 0.0188 1.0000
12.000 1.0877 0.04892 0.04107 0.0138 0.0185 1.0000
12.250 1.0740 0.05384 0.04619 0.0116 0.0185 1.0000
12.500 1.0569 0.05989 0.05244 0.0083 0.0185 1.0000
12.750 1.0377 0.06696 0.05971 0.0042 0.0187 1.0000
13.000 1.0164 0.07467 0.06760 -0.0001 0.0187 1.0000
13.250 1.0001 0.08152 0.07460 -0.0037 0.0189 1.0000
13.500 0.9838 0.08835 0.08157 -0.0071 0.0190 1.0000
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Polar data table (+)
Polar graphs
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