USA 50 AIRFOIL (usa50-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: USA 50 AIRFOIL (usa50-il) Reynolds number: 100,000 Max Cl/Cd: 49.17 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa50-il-100000-n5.txt Download as CSV file: xf-usa50-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 50 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3805 0.09677 0.09207 -0.0207 1.0000 0.0437
-9.000 -0.3819 0.09314 0.08847 -0.0216 1.0000 0.0447
-8.500 -0.4783 0.09791 0.09300 -0.0183 1.0000 0.0401
-8.250 -0.4780 0.09449 0.08964 -0.0192 1.0000 0.0406
-8.000 -0.4778 0.09144 0.08665 -0.0198 1.0000 0.0430
-7.750 -0.4806 0.08815 0.08342 -0.0208 1.0000 0.0429
-7.500 -0.4855 0.08487 0.08023 -0.0218 1.0000 0.0433
-7.250 -0.4860 0.08114 0.07654 -0.0239 1.0000 0.0437
-7.000 -0.4849 0.07715 0.07258 -0.0259 1.0000 0.0431
-6.500 -0.4783 0.06630 0.06163 -0.0307 1.0000 0.0260
-6.250 -0.4728 0.06193 0.05721 -0.0317 1.0000 0.0243
-6.000 -0.4656 0.05703 0.05217 -0.0328 1.0000 0.0225
-5.500 -0.4393 0.04686 0.04137 -0.0331 1.0000 0.0186
-5.250 -0.4287 0.04291 0.03719 -0.0322 1.0000 0.0182
-5.000 -0.4155 0.03915 0.03312 -0.0312 1.0000 0.0179
-4.750 -0.4004 0.03555 0.02916 -0.0299 1.0000 0.0177
-4.500 -0.3835 0.03195 0.02509 -0.0284 1.0000 0.0176
-4.250 -0.3648 0.02881 0.02146 -0.0268 1.0000 0.0176
-4.000 -0.3444 0.02600 0.01812 -0.0252 1.0000 0.0178
-3.750 -0.3222 0.02363 0.01518 -0.0236 1.0000 0.0192
-3.500 -0.3006 0.02157 0.01282 -0.0225 1.0000 0.0213
-3.250 -0.2774 0.01988 0.01087 -0.0212 1.0000 0.0226
-2.750 -0.2325 0.01742 0.00803 -0.0185 1.0000 0.0294
-2.500 -0.2106 0.01663 0.00715 -0.0173 1.0000 0.0366
-2.250 -0.1885 0.01593 0.00646 -0.0161 1.0000 0.0585
-2.000 -0.1668 0.01532 0.00588 -0.0151 1.0000 0.0992
-1.750 -0.1443 0.01477 0.00548 -0.0143 0.9997 0.1452
-1.500 -0.1102 0.01346 0.00520 -0.0165 0.9951 0.4101
-1.250 -0.0476 0.01188 0.00505 -0.0226 1.0000 1.0000
-1.000 -0.0086 0.01200 0.00487 -0.0252 0.9935 1.0000
-0.750 0.0318 0.01210 0.00470 -0.0282 0.9857 1.0000
-0.500 0.0710 0.01216 0.00458 -0.0309 0.9768 1.0000
-0.250 0.1095 0.01220 0.00447 -0.0333 0.9672 1.0000
0.000 0.1465 0.01220 0.00434 -0.0354 0.9562 1.0000
0.250 0.1823 0.01217 0.00424 -0.0372 0.9437 1.0000
0.500 0.2186 0.01212 0.00414 -0.0390 0.9309 1.0000
0.750 0.2559 0.01205 0.00404 -0.0409 0.9177 1.0000
1.000 0.2974 0.01194 0.00393 -0.0436 0.9021 1.0000
1.250 0.3381 0.01180 0.00381 -0.0460 0.8788 1.0000
1.500 0.3792 0.01169 0.00369 -0.0485 0.8516 1.0000
1.750 0.4184 0.01163 0.00364 -0.0506 0.8227 1.0000
2.000 0.4570 0.01163 0.00366 -0.0525 0.7910 1.0000
2.250 0.4925 0.01169 0.00370 -0.0537 0.7580 1.0000
2.500 0.5244 0.01184 0.00382 -0.0543 0.7259 1.0000
2.750 0.5536 0.01204 0.00406 -0.0543 0.6965 1.0000
3.000 0.5807 0.01227 0.00432 -0.0540 0.6692 1.0000
3.250 0.6063 0.01253 0.00463 -0.0533 0.6422 1.0000
3.500 0.6304 0.01282 0.00495 -0.0522 0.6111 1.0000
3.750 0.6484 0.01332 0.00517 -0.0497 0.5414 1.0000
4.000 0.6654 0.01385 0.00546 -0.0472 0.4640 1.0000
4.250 0.6782 0.01478 0.00570 -0.0442 0.3171 1.0000
4.500 0.6844 0.01719 0.00664 -0.0411 0.0729 1.0000
4.750 0.7010 0.01854 0.00768 -0.0390 0.0269 1.0000
5.000 0.7210 0.01944 0.00877 -0.0372 0.0234 1.0000
5.250 0.7390 0.02056 0.01013 -0.0353 0.0197 1.0000
5.500 0.7545 0.02194 0.01172 -0.0330 0.0178 1.0000
5.750 0.7714 0.02322 0.01319 -0.0308 0.0172 1.0000
6.000 0.7887 0.02472 0.01485 -0.0288 0.0167 1.0000
6.250 0.8082 0.02652 0.01680 -0.0270 0.0163 1.0000
6.500 0.8299 0.02856 0.01905 -0.0256 0.0157 1.0000
6.750 0.8514 0.03066 0.02145 -0.0241 0.0144 1.0000
7.000 0.8714 0.03298 0.02410 -0.0226 0.0136 1.0000
7.250 0.8892 0.03579 0.02733 -0.0207 0.0135 1.0000
7.500 0.9038 0.03880 0.03089 -0.0184 0.0137 1.0000
7.750 0.9147 0.04212 0.03468 -0.0159 0.0139 1.0000
8.000 0.9219 0.04557 0.03858 -0.0132 0.0142 1.0000
8.250 0.9256 0.04916 0.04258 -0.0105 0.0146 1.0000
8.500 0.9257 0.05278 0.04657 -0.0078 0.0149 1.0000
8.750 0.9215 0.05655 0.05066 -0.0051 0.0152 1.0000
9.000 0.9143 0.06014 0.05451 -0.0027 0.0155 1.0000
9.250 0.9024 0.06352 0.05810 -0.0001 0.0157 1.0000
9.500 0.8856 0.06709 0.06184 0.0021 0.0158 1.0000
9.750 0.8696 0.07084 0.06574 0.0026 0.0160 1.0000
10.000 0.8515 0.07557 0.07059 0.0011 0.0160 1.0000
10.250 0.8357 0.08097 0.07610 -0.0023 0.0161 1.0000
10.500 0.8202 0.08780 0.08300 -0.0074 0.0162 1.0000
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Polar data table (+)
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