REPUBLIC S-3 AIRFOIL (s3-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: REPUBLIC S-3 AIRFOIL (s3-il) Reynolds number: 50,000 Max Cl/Cd: 28.43 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s3-il-50000-n5.txt Download as CSV file: xf-s3-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5347 0.10092 0.09422 -0.0132 1.0000 0.0455
-9.750 -0.5309 0.09660 0.08993 -0.0141 1.0000 0.0449
-9.500 -0.5309 0.09167 0.08504 -0.0165 1.0000 0.0443
-9.250 -0.5353 0.08631 0.07973 -0.0200 1.0000 0.0439
-9.000 -0.5432 0.08128 0.07473 -0.0233 1.0000 0.0435
-8.750 -0.5544 0.07674 0.07019 -0.0255 1.0000 0.0431
-8.500 -0.5644 0.07272 0.06613 -0.0264 1.0000 0.0426
-8.250 -0.5726 0.06859 0.06189 -0.0272 1.0000 0.0426
-8.000 -0.5772 0.06461 0.05774 -0.0275 1.0000 0.0425
-7.750 -0.5790 0.06071 0.05361 -0.0274 1.0000 0.0428
-7.500 -0.5773 0.05695 0.04956 -0.0268 1.0000 0.0432
-7.250 -0.5723 0.05337 0.04562 -0.0260 1.0000 0.0437
-7.000 -0.5639 0.04995 0.04183 -0.0249 1.0000 0.0441
-6.750 -0.5528 0.04666 0.03815 -0.0237 1.0000 0.0444
-6.500 -0.5394 0.04358 0.03466 -0.0223 1.0000 0.0447
-6.250 -0.5238 0.04077 0.03141 -0.0208 1.0000 0.0453
-6.000 -0.5076 0.03794 0.02834 -0.0196 1.0000 0.0471
-5.750 -0.4898 0.03587 0.02619 -0.0185 1.0000 0.0501
-5.500 -0.4706 0.03387 0.02394 -0.0171 1.0000 0.0531
-5.250 -0.4496 0.03185 0.02158 -0.0156 1.0000 0.0552
-5.000 -0.4279 0.03022 0.01960 -0.0140 1.0000 0.0588
-4.750 -0.4080 0.02852 0.01797 -0.0127 1.0000 0.0640
-4.500 -0.3874 0.02720 0.01656 -0.0110 1.0000 0.0693
-4.250 -0.3684 0.02603 0.01528 -0.0091 1.0000 0.0757
-4.000 -0.3528 0.02503 0.01429 -0.0072 1.0000 0.0853
-3.750 -0.3384 0.02404 0.01323 -0.0051 1.0000 0.0934
-3.500 -0.3243 0.02318 0.01236 -0.0032 1.0000 0.1078
-3.250 -0.3093 0.02228 0.01143 -0.0015 1.0000 0.1231
-3.000 -0.2937 0.02117 0.01051 -0.0003 0.9994 0.1562
-2.750 -0.2716 0.01862 0.01042 0.0001 0.9859 0.5852
-2.500 -0.2404 0.01871 0.01084 0.0018 0.9703 0.7289
-2.250 -0.2034 0.01911 0.01126 0.0030 0.9571 0.8200
-2.000 -0.1511 0.01964 0.01160 0.0016 0.9479 0.8869
-1.750 -0.0954 0.01965 0.01129 -0.0035 0.9373 0.9065
-1.500 -0.0384 0.01960 0.01094 -0.0090 0.9257 0.9217
-1.250 0.0194 0.01946 0.01056 -0.0147 0.9109 0.9348
-1.000 0.0771 0.01924 0.01010 -0.0201 0.8918 0.9461
-0.750 0.1277 0.01901 0.00967 -0.0243 0.8684 0.9578
-0.500 0.1753 0.01876 0.00923 -0.0278 0.8450 0.9696
-0.250 0.2187 0.01854 0.00887 -0.0307 0.8209 0.9826
0.000 0.2602 0.01832 0.00851 -0.0333 0.7960 0.9963
0.250 0.2841 0.01822 0.00827 -0.0326 0.7718 1.0000
0.500 0.3007 0.01821 0.00814 -0.0305 0.7463 1.0000
0.750 0.3173 0.01822 0.00801 -0.0283 0.7200 1.0000
1.000 0.3339 0.01825 0.00790 -0.0261 0.6917 1.0000
1.250 0.3506 0.01831 0.00783 -0.0239 0.6608 1.0000
1.500 0.3676 0.01838 0.00778 -0.0217 0.6274 1.0000
1.750 0.3854 0.01846 0.00771 -0.0197 0.5934 1.0000
2.000 0.4039 0.01859 0.00764 -0.0178 0.5605 1.0000
2.250 0.4230 0.01879 0.00763 -0.0160 0.5282 1.0000
2.500 0.4426 0.01906 0.00769 -0.0144 0.4988 1.0000
2.750 0.4627 0.01941 0.00783 -0.0129 0.4724 1.0000
3.000 0.4839 0.01982 0.00804 -0.0118 0.4486 1.0000
3.250 0.5056 0.02028 0.00834 -0.0108 0.4280 1.0000
3.500 0.5280 0.02080 0.00869 -0.0099 0.4100 1.0000
3.750 0.5510 0.02133 0.00912 -0.0091 0.3939 1.0000
4.000 0.5743 0.02189 0.00965 -0.0085 0.3792 1.0000
4.250 0.5977 0.02244 0.01020 -0.0078 0.3653 1.0000
4.500 0.6212 0.02301 0.01078 -0.0073 0.3524 1.0000
4.750 0.6449 0.02360 0.01141 -0.0067 0.3408 1.0000
5.000 0.6687 0.02420 0.01200 -0.0061 0.3310 1.0000
5.250 0.6927 0.02484 0.01270 -0.0056 0.3219 1.0000
5.500 0.7170 0.02554 0.01347 -0.0052 0.3143 1.0000
5.750 0.7412 0.02625 0.01428 -0.0048 0.3071 1.0000
6.000 0.7653 0.02701 0.01514 -0.0043 0.3001 1.0000
6.250 0.7890 0.02779 0.01603 -0.0039 0.2930 1.0000
6.500 0.8129 0.02859 0.01691 -0.0034 0.2868 1.0000
6.750 0.8359 0.02958 0.01817 -0.0030 0.2805 1.0000
7.000 0.8601 0.03045 0.01912 -0.0026 0.2754 1.0000
7.250 0.8816 0.03156 0.02048 -0.0021 0.2688 1.0000
7.500 0.9040 0.03228 0.02129 -0.0015 0.2605 1.0000
7.750 0.9229 0.03322 0.02248 -0.0007 0.2508 1.0000
8.000 0.9444 0.03381 0.02315 0.0001 0.2416 1.0000
8.250 0.9625 0.03472 0.02433 0.0009 0.2319 1.0000
8.500 0.9814 0.03573 0.02555 0.0017 0.2243 1.0000
8.750 1.0001 0.03675 0.02679 0.0025 0.2168 1.0000
9.000 1.0160 0.03774 0.02803 0.0035 0.2078 1.0000
9.250 1.0334 0.03800 0.02835 0.0046 0.1975 1.0000
9.500 1.0468 0.03836 0.02885 0.0059 0.1859 1.0000
9.750 1.0558 0.03910 0.02988 0.0074 0.1738 1.0000
10.000 1.0646 0.04001 0.03099 0.0087 0.1633 1.0000
10.250 1.0761 0.04077 0.03184 0.0100 0.1560 1.0000
10.500 1.0802 0.04258 0.03403 0.0113 0.1482 1.0000
10.750 1.0854 0.04369 0.03526 0.0127 0.1413 1.0000
11.000 1.0813 0.04606 0.03798 0.0142 0.1351 1.0000
11.250 1.0779 0.04837 0.04052 0.0151 0.1298 1.0000
11.500 1.0736 0.05101 0.04333 0.0153 0.1256 1.0000
11.750 1.0573 0.05563 0.04826 0.0142 0.1213 1.0000
12.000 1.0396 0.06083 0.05366 0.0121 0.1175 1.0000
12.250 1.0276 0.06552 0.05844 0.0099 0.1135 1.0000
12.500 0.9997 0.07364 0.06669 0.0057 0.1131 1.0000
12.750 0.9609 0.08457 0.07764 -0.0002 0.1128 1.0000
13.000 0.9153 0.09787 0.09082 -0.0071 0.1123 1.0000
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Polar data table (+)
Polar graphs
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