N-13 (n13-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-13 (n13-il) Reynolds number: 50,000 Max Cl/Cd: 28.97 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n13-il-50000.txt Download as CSV file: xf-n13-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: N-13
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.7324 0.08406 0.07670 -0.0379 1.0000 0.1412
-10.500 -0.7455 0.07879 0.07142 -0.0381 1.0000 0.1399
-10.250 -0.7687 0.07393 0.06654 -0.0371 1.0000 0.1383
-10.000 -0.7963 0.06978 0.06235 -0.0343 1.0000 0.1366
-9.750 -0.8227 0.06548 0.05790 -0.0312 1.0000 0.1350
-9.500 -0.8452 0.06134 0.05355 -0.0276 1.0000 0.1341
-9.250 -0.8598 0.05754 0.04944 -0.0239 1.0000 0.1346
-9.000 -0.8701 0.05404 0.04561 -0.0200 1.0000 0.1369
-8.750 -0.8794 0.05069 0.04180 -0.0158 1.0000 0.1395
-8.500 -0.8767 0.04752 0.03840 -0.0127 1.0000 0.1446
-8.250 -0.8695 0.04506 0.03573 -0.0098 1.0000 0.1523
-8.000 -0.8629 0.04240 0.03281 -0.0067 1.0000 0.1599
-7.750 -0.8564 0.04028 0.03030 -0.0034 1.0000 0.1695
-7.500 -0.8404 0.03812 0.02813 -0.0015 1.0000 0.1809
-7.250 -0.8263 0.03606 0.02593 0.0008 1.0000 0.1928
-7.000 -0.8104 0.03390 0.02353 0.0030 1.0000 0.2050
-6.750 -0.7930 0.03205 0.02162 0.0049 1.0000 0.2217
-6.500 -0.7741 0.03014 0.01966 0.0067 1.0000 0.2425
-6.250 -0.7540 0.02837 0.01804 0.0084 1.0000 0.2696
-6.000 -0.7378 0.02702 0.01685 0.0107 1.0000 0.3026
-5.750 -0.7215 0.02587 0.01578 0.0131 1.0000 0.3365
-5.500 -0.7051 0.02485 0.01505 0.0156 1.0000 0.3747
-5.250 -0.6921 0.02392 0.01443 0.0187 1.0000 0.4248
-5.000 -0.6801 0.02307 0.01404 0.0225 1.0000 0.4908
-4.750 -0.6686 0.02272 0.01415 0.0273 1.0000 0.5675
-4.500 -0.6530 0.02290 0.01461 0.0322 1.0000 0.6399
-4.250 -0.6312 0.02320 0.01497 0.0360 1.0000 0.6979
-4.000 -0.6001 0.02374 0.01543 0.0381 1.0000 0.7444
-3.750 -0.5573 0.02463 0.01613 0.0382 1.0000 0.7837
-3.500 -0.5040 0.02580 0.01704 0.0363 1.0000 0.8189
-3.250 -0.3777 0.02850 0.01918 0.0235 1.0000 0.8579
-3.000 -0.2954 0.02929 0.01962 0.0152 1.0000 0.8934
-2.750 -0.2109 0.02932 0.01934 0.0052 1.0000 0.9259
-2.500 -0.1392 0.02867 0.01847 -0.0038 1.0000 0.9540
-2.250 -0.0740 0.02755 0.01718 -0.0126 1.0000 0.9757
-2.000 -0.0090 0.02629 0.01578 -0.0219 1.0000 0.9967
-1.750 0.0073 0.02560 0.01507 -0.0221 1.0000 1.0000
-1.500 0.0120 0.02510 0.01459 -0.0199 1.0000 1.0000
-1.250 0.0153 0.02467 0.01418 -0.0174 1.0000 1.0000
-1.000 0.0170 0.02431 0.01385 -0.0146 1.0000 1.0000
-0.750 0.0169 0.02401 0.01357 -0.0115 1.0000 1.0000
-0.500 0.0150 0.02377 0.01335 -0.0080 1.0000 1.0000
-0.250 0.0115 0.02357 0.01317 -0.0043 1.0000 1.0000
0.000 0.0066 0.02343 0.01305 -0.0003 1.0000 1.0000
0.250 0.0009 0.02336 0.01298 0.0038 1.0000 1.0000
0.500 -0.0043 0.02336 0.01298 0.0078 1.0000 1.0000
0.750 -0.0076 0.02345 0.01305 0.0116 1.0000 1.0000
1.000 -0.0086 0.02362 0.01320 0.0150 1.0000 1.0000
1.250 -0.0072 0.02387 0.01342 0.0180 1.0000 1.0000
1.500 -0.0038 0.02418 0.01372 0.0207 1.0000 1.0000
1.750 0.0011 0.02456 0.01410 0.0231 1.0000 1.0000
2.000 0.0070 0.02501 0.01454 0.0252 1.0000 1.0000
2.250 0.0136 0.02554 0.01508 0.0271 1.0000 1.0000
2.500 0.0559 0.02659 0.01625 0.0220 0.9880 1.0000
2.750 0.1420 0.02783 0.01777 0.0092 0.9579 1.0000
3.000 0.2259 0.02841 0.01866 -0.0020 0.9236 1.0000
3.250 0.3284 0.02826 0.01894 -0.0149 0.8868 1.0000
3.500 0.4416 0.02686 0.01811 -0.0277 0.8448 1.0000
3.750 0.5247 0.02488 0.01658 -0.0336 0.7949 1.0000
4.000 0.5889 0.02268 0.01458 -0.0350 0.7307 1.0000
4.250 0.6245 0.02197 0.01370 -0.0326 0.6525 1.0000
4.500 0.6408 0.02212 0.01354 -0.0283 0.5743 1.0000
4.750 0.6531 0.02257 0.01355 -0.0239 0.4969 1.0000
5.000 0.6668 0.02360 0.01399 -0.0202 0.4222 1.0000
5.250 0.6817 0.02499 0.01495 -0.0173 0.3589 1.0000
5.500 0.6977 0.02636 0.01604 -0.0148 0.3112 1.0000
5.750 0.7155 0.02770 0.01716 -0.0126 0.2757 1.0000
6.000 0.7348 0.02919 0.01860 -0.0108 0.2495 1.0000
6.250 0.7548 0.03068 0.01997 -0.0092 0.2283 1.0000
6.500 0.7752 0.03245 0.02177 -0.0077 0.2127 1.0000
6.750 0.7918 0.03414 0.02362 -0.0056 0.1987 1.0000
7.000 0.8060 0.03622 0.02601 -0.0031 0.1885 1.0000
7.250 0.8218 0.03836 0.02826 -0.0011 0.1792 1.0000
7.500 0.8333 0.04041 0.03060 0.0016 0.1704 1.0000
7.750 0.8438 0.04312 0.03354 0.0042 0.1648 1.0000
8.000 0.8445 0.04583 0.03674 0.0082 0.1600 1.0000
8.250 0.8640 0.04830 0.03905 0.0092 0.1522 1.0000
8.500 0.8568 0.05152 0.04279 0.0138 0.1505 1.0000
8.750 0.8463 0.05497 0.04667 0.0182 0.1492 1.0000
9.000 0.8327 0.05858 0.05062 0.0223 0.1483 1.0000
9.250 0.8149 0.06235 0.05466 0.0262 0.1478 1.0000
9.500 0.7955 0.06638 0.05887 0.0296 0.1486 1.0000
9.750 0.7742 0.07051 0.06311 0.0326 0.1496 1.0000
10.000 0.7544 0.07470 0.06733 0.0351 0.1508 1.0000
10.250 0.7360 0.07917 0.07185 0.0367 0.1527 1.0000
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Polar data table (+)
Polar graphs
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