N-13 (n13-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-13 (n13-il) Reynolds number: 200,000 Max Cl/Cd: 45.78 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n13-il-200000-n5.txt Download as CSV file: xf-n13-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.8156 0.12069 0.11655 -0.0153 1.0000 0.0133
-16.000 -0.8432 0.11007 0.10582 -0.0209 1.0000 0.0131
-15.750 -0.8721 0.09946 0.09505 -0.0268 1.0000 0.0131
-15.500 -0.8936 0.09097 0.08641 -0.0316 1.0000 0.0130
-15.250 -0.9154 0.08285 0.07812 -0.0363 1.0000 0.0130
-15.000 -0.9338 0.07585 0.07094 -0.0402 1.0000 0.0129
-14.750 -0.9500 0.06959 0.06450 -0.0435 1.0000 0.0130
-14.500 -0.9633 0.06417 0.05890 -0.0461 1.0000 0.0130
-14.250 -0.9755 0.05927 0.05381 -0.0481 1.0000 0.0131
-14.000 -0.9851 0.05502 0.04936 -0.0494 1.0000 0.0132
-13.750 -0.9934 0.05120 0.04536 -0.0502 1.0000 0.0132
-13.500 -0.9997 0.04783 0.04181 -0.0504 1.0000 0.0134
-13.250 -1.0063 0.04467 0.03850 -0.0501 1.0000 0.0135
-13.000 -1.0121 0.04179 0.03549 -0.0494 1.0000 0.0138
-12.750 -1.0157 0.03934 0.03291 -0.0482 1.0000 0.0140
-12.500 -1.0179 0.03722 0.03068 -0.0466 1.0000 0.0144
-12.250 -1.0172 0.03546 0.02879 -0.0448 1.0000 0.0147
-12.000 -1.0160 0.03385 0.02707 -0.0426 1.0000 0.0152
-11.750 -1.0140 0.03236 0.02546 -0.0402 1.0000 0.0156
-11.500 -1.0089 0.03121 0.02417 -0.0378 1.0000 0.0165
-11.250 -1.0059 0.02992 0.02275 -0.0348 1.0000 0.0170
-11.000 -1.0020 0.02879 0.02148 -0.0317 1.0000 0.0176
-10.750 -0.9995 0.02770 0.02029 -0.0281 1.0000 0.0182
-10.500 -0.9984 0.02666 0.01920 -0.0241 1.0000 0.0190
-10.250 -0.9938 0.02581 0.01828 -0.0205 1.0000 0.0198
-10.000 -0.9854 0.02497 0.01738 -0.0175 1.0000 0.0210
-9.750 -0.9755 0.02418 0.01649 -0.0147 1.0000 0.0225
-9.500 -0.9650 0.02340 0.01566 -0.0119 1.0000 0.0245
-9.250 -0.9522 0.02278 0.01501 -0.0095 1.0000 0.0273
-9.000 -0.9397 0.02212 0.01428 -0.0069 1.0000 0.0305
-8.750 -0.9261 0.02156 0.01369 -0.0045 1.0000 0.0343
-8.500 -0.9123 0.02102 0.01306 -0.0021 1.0000 0.0386
-8.250 -0.8990 0.02048 0.01248 0.0003 1.0000 0.0426
-8.000 -0.8834 0.02011 0.01198 0.0025 1.0000 0.0467
-7.750 -0.8732 0.01941 0.01126 0.0055 1.0000 0.0502
-7.500 -0.8610 0.01887 0.01065 0.0082 1.0000 0.0539
-7.250 -0.8473 0.01845 0.01013 0.0107 1.0000 0.0574
-7.000 -0.8344 0.01795 0.00962 0.0133 1.0000 0.0618
-6.750 -0.8206 0.01749 0.00919 0.0157 1.0000 0.0671
-6.500 -0.7945 0.01706 0.00887 0.0156 0.9980 0.0782
-6.250 -0.7627 0.01676 0.00856 0.0144 0.9950 0.0939
-6.000 -0.7319 0.01643 0.00815 0.0135 0.9917 0.1049
-5.750 -0.7030 0.01602 0.00772 0.0129 0.9882 0.1133
-5.500 -0.6722 0.01575 0.00736 0.0120 0.9854 0.1210
-5.250 -0.6456 0.01534 0.00696 0.0119 0.9814 0.1300
-5.000 -0.6170 0.01501 0.00663 0.0114 0.9776 0.1396
-4.750 -0.5862 0.01467 0.00633 0.0105 0.9746 0.1521
-4.500 -0.5614 0.01433 0.00604 0.0108 0.9694 0.1670
-4.250 -0.5319 0.01400 0.00575 0.0102 0.9655 0.1879
-4.000 -0.5030 0.01364 0.00547 0.0097 0.9615 0.2138
-3.750 -0.4782 0.01321 0.00520 0.0100 0.9561 0.2495
-3.500 -0.4498 0.01267 0.00493 0.0095 0.9521 0.3085
-3.250 -0.4246 0.01224 0.00474 0.0098 0.9468 0.3691
-3.000 -0.3966 0.01189 0.00455 0.0096 0.9418 0.4136
-2.750 -0.3651 0.01155 0.00436 0.0088 0.9385 0.4535
-2.500 -0.3381 0.01125 0.00422 0.0089 0.9332 0.4928
-2.250 -0.3098 0.01093 0.00411 0.0089 0.9282 0.5428
-2.000 -0.2767 0.01066 0.00400 0.0078 0.9248 0.5872
-1.750 -0.2449 0.01046 0.00392 0.0071 0.9195 0.6236
-1.500 -0.2091 0.01025 0.00380 0.0057 0.9133 0.6547
-1.250 -0.1652 0.01003 0.00365 0.0024 0.9087 0.6803
-1.000 -0.1336 0.00989 0.00358 0.0019 0.8991 0.7024
-0.750 -0.0954 0.00973 0.00350 -0.0001 0.8912 0.7249
-0.500 -0.0600 0.00961 0.00346 -0.0014 0.8813 0.7493
-0.250 -0.0287 0.00953 0.00349 -0.0018 0.8699 0.7728
0.000 0.0039 0.00949 0.00354 -0.0025 0.8584 0.7943
0.250 0.0382 0.00947 0.00360 -0.0036 0.8454 0.8127
0.500 0.0731 0.00949 0.00367 -0.0048 0.8294 0.8299
0.750 0.1098 0.00951 0.00373 -0.0063 0.8087 0.8449
1.250 0.1905 0.00961 0.00368 -0.0106 0.7448 0.8722
1.500 0.2262 0.00980 0.00374 -0.0119 0.7168 0.8856
1.750 0.2616 0.01002 0.00387 -0.0132 0.6921 0.8954
2.000 0.2935 0.01023 0.00402 -0.0138 0.6682 0.9047
2.250 0.3206 0.01045 0.00418 -0.0134 0.6428 0.9164
2.500 0.3539 0.01074 0.00438 -0.0143 0.6047 0.9242
2.750 0.3799 0.01106 0.00452 -0.0136 0.5497 0.9335
3.000 0.4052 0.01153 0.00464 -0.0130 0.4711 0.9407
3.250 0.4288 0.01200 0.00484 -0.0122 0.4136 0.9482
3.500 0.4592 0.01242 0.00507 -0.0129 0.3691 0.9535
3.750 0.4841 0.01280 0.00530 -0.0125 0.3295 0.9609
4.000 0.5169 0.01320 0.00555 -0.0138 0.2857 0.9650
4.250 0.5450 0.01361 0.00580 -0.0142 0.2452 0.9709
4.500 0.5752 0.01406 0.00608 -0.0150 0.2077 0.9755
4.750 0.6062 0.01448 0.00639 -0.0161 0.1758 0.9800
5.000 0.6352 0.01492 0.00672 -0.0167 0.1500 0.9850
5.250 0.6677 0.01533 0.00705 -0.0181 0.1245 0.9885
5.500 0.6982 0.01579 0.00742 -0.0191 0.1064 0.9927
5.750 0.7297 0.01622 0.00784 -0.0202 0.0942 0.9963
6.000 0.7617 0.01664 0.00829 -0.0215 0.0856 0.9997
6.250 0.7783 0.01712 0.00874 -0.0195 0.0800 1.0000
6.500 0.7946 0.01748 0.00917 -0.0174 0.0756 1.0000
6.750 0.8104 0.01789 0.00963 -0.0152 0.0710 1.0000
7.000 0.8243 0.01843 0.01017 -0.0127 0.0673 1.0000
7.250 0.8397 0.01886 0.01067 -0.0105 0.0638 1.0000
7.500 0.8556 0.01925 0.01113 -0.0084 0.0596 1.0000
7.750 0.8696 0.01975 0.01163 -0.0060 0.0557 1.0000
8.000 0.8830 0.02032 0.01225 -0.0034 0.0528 1.0000
8.250 0.8983 0.02073 0.01276 -0.0012 0.0494 1.0000
8.500 0.9125 0.02119 0.01329 0.0012 0.0462 1.0000
8.750 0.9231 0.02187 0.01395 0.0040 0.0431 1.0000
9.000 0.9377 0.02231 0.01454 0.0064 0.0402 1.0000
9.250 0.9505 0.02283 0.01513 0.0089 0.0373 1.0000
9.500 0.9604 0.02349 0.01579 0.0118 0.0347 1.0000
9.750 0.9716 0.02413 0.01655 0.0146 0.0322 1.0000
10.000 0.9825 0.02474 0.01725 0.0173 0.0296 1.0000
10.250 0.9900 0.02541 0.01796 0.0206 0.0277 1.0000
10.500 0.9942 0.02623 0.01886 0.0244 0.0262 1.0000
10.750 0.9998 0.02703 0.01980 0.0279 0.0244 1.0000
11.000 1.0055 0.02785 0.02071 0.0312 0.0230 1.0000
11.250 1.0107 0.02873 0.02165 0.0343 0.0219 1.0000
11.500 1.0133 0.02981 0.02277 0.0375 0.0207 1.0000
11.750 1.0177 0.03099 0.02412 0.0403 0.0198 1.0000
12.000 1.0212 0.03226 0.02553 0.0429 0.0189 1.0000
12.250 1.0233 0.03367 0.02708 0.0454 0.0180 1.0000
12.500 1.0243 0.03522 0.02878 0.0477 0.0175 1.0000
12.750 1.0243 0.03694 0.03062 0.0497 0.0171 1.0000
13.000 1.0227 0.03886 0.03266 0.0514 0.0165 1.0000
13.250 1.0206 0.04097 0.03489 0.0526 0.0163 1.0000
13.500 1.0131 0.04377 0.03781 0.0535 0.0158 1.0000
13.750 1.0062 0.04681 0.04099 0.0538 0.0155 1.0000
14.000 0.9986 0.05023 0.04461 0.0536 0.0153 1.0000
14.250 0.9889 0.05415 0.04872 0.0527 0.0151 1.0000
14.500 0.9788 0.05843 0.05319 0.0512 0.0149 1.0000
14.750 0.9632 0.06386 0.05882 0.0488 0.0148 1.0000
15.000 0.9491 0.06949 0.06461 0.0459 0.0149 1.0000
15.250 0.9285 0.07673 0.07206 0.0417 0.0147 1.0000
15.500 0.9047 0.08495 0.08046 0.0369 0.0147 1.0000
15.750 0.8810 0.09355 0.08922 0.0319 0.0148 1.0000
16.000 0.8500 0.10393 0.09974 0.0263 0.0151 1.0000
16.250 0.8138 0.11600 0.11194 0.0198 0.0154 1.0000
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Polar data table (+)
Polar graphs
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