N-13 (n13-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-13 (n13-il) Reynolds number: 100,000 Max Cl/Cd: 37.18 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n13-il-100000-n5.txt Download as CSV file: xf-n13-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.7458 0.10147 0.09602 -0.0276 1.0000 0.0267
-13.750 -0.8421 0.07702 0.07109 -0.0435 1.0000 0.0243
-13.500 -0.8700 0.06933 0.06313 -0.0477 1.0000 0.0241
-13.250 -0.8886 0.06384 0.05742 -0.0499 1.0000 0.0240
-13.000 -0.9008 0.05970 0.05313 -0.0509 1.0000 0.0243
-12.750 -0.9115 0.05603 0.04929 -0.0512 1.0000 0.0245
-12.500 -0.9194 0.05303 0.04615 -0.0509 1.0000 0.0250
-12.250 -0.9272 0.05003 0.04297 -0.0499 1.0000 0.0252
-12.000 -0.9322 0.04778 0.04057 -0.0485 1.0000 0.0261
-11.750 -0.9368 0.04556 0.03816 -0.0465 1.0000 0.0270
-11.500 -0.9399 0.04339 0.03576 -0.0441 1.0000 0.0278
-11.250 -0.9416 0.04125 0.03334 -0.0414 1.0000 0.0290
-11.000 -0.9408 0.03932 0.03118 -0.0385 1.0000 0.0302
-10.750 -0.9387 0.03790 0.02972 -0.0356 1.0000 0.0312
-10.500 -0.9359 0.03655 0.02829 -0.0325 1.0000 0.0325
-10.250 -0.9313 0.03515 0.02674 -0.0294 1.0000 0.0341
-10.000 -0.9237 0.03375 0.02509 -0.0265 1.0000 0.0367
-9.750 -0.9171 0.03238 0.02364 -0.0237 1.0000 0.0392
-9.500 -0.9091 0.03117 0.02235 -0.0210 1.0000 0.0426
-9.250 -0.8980 0.02995 0.02087 -0.0184 1.0000 0.0466
-9.000 -0.8917 0.02846 0.01943 -0.0153 1.0000 0.0506
-8.750 -0.8816 0.02739 0.01825 -0.0126 1.0000 0.0562
-8.500 -0.8720 0.02629 0.01712 -0.0098 1.0000 0.0612
-8.250 -0.8606 0.02546 0.01629 -0.0073 1.0000 0.0668
-8.000 -0.8479 0.02477 0.01561 -0.0049 1.0000 0.0728
-7.750 -0.8327 0.02432 0.01509 -0.0028 1.0000 0.0814
-7.500 -0.8173 0.02389 0.01457 -0.0007 1.0000 0.0906
-7.250 -0.8033 0.02330 0.01395 0.0016 1.0000 0.0985
-7.000 -0.7884 0.02267 0.01319 0.0039 1.0000 0.1067
-6.750 -0.7764 0.02189 0.01244 0.0066 1.0000 0.1141
-6.500 -0.7625 0.02127 0.01174 0.0090 1.0000 0.1231
-6.250 -0.7494 0.02064 0.01110 0.0116 1.0000 0.1334
-6.000 -0.7356 0.02008 0.01057 0.0139 1.0000 0.1447
-5.750 -0.7207 0.01960 0.01009 0.0162 1.0000 0.1566
-5.500 -0.7051 0.01916 0.00964 0.0183 1.0000 0.1690
-5.250 -0.6891 0.01874 0.00923 0.0203 1.0000 0.1839
-5.000 -0.6730 0.01832 0.00881 0.0224 1.0000 0.2011
-4.750 -0.6570 0.01789 0.00843 0.0244 1.0000 0.2221
-4.500 -0.6416 0.01741 0.00808 0.0265 1.0000 0.2501
-4.250 -0.6270 0.01689 0.00779 0.0286 1.0000 0.2921
-4.000 -0.6128 0.01639 0.00757 0.0309 1.0000 0.3527
-3.750 -0.5953 0.01602 0.00737 0.0327 0.9995 0.4058
-3.500 -0.5634 0.01576 0.00729 0.0315 0.9944 0.4572
-3.250 -0.5331 0.01548 0.00724 0.0308 0.9888 0.5136
-3.000 -0.5012 0.01534 0.00725 0.0299 0.9835 0.5648
-2.750 -0.4699 0.01522 0.00723 0.0292 0.9774 0.6079
-2.500 -0.4376 0.01513 0.00722 0.0283 0.9715 0.6451
-2.250 -0.4044 0.01505 0.00719 0.0272 0.9654 0.6784
-2.000 -0.3713 0.01499 0.00719 0.0263 0.9592 0.7094
-1.750 -0.3351 0.01495 0.00723 0.0248 0.9535 0.7410
-1.500 -0.2957 0.01498 0.00735 0.0227 0.9488 0.7738
-1.250 -0.2560 0.01507 0.00752 0.0207 0.9432 0.8036
-1.000 -0.2104 0.01522 0.00770 0.0174 0.9392 0.8278
-0.750 -0.1642 0.01534 0.00783 0.0139 0.9333 0.8458
-0.500 -0.1139 0.01540 0.00790 0.0098 0.9263 0.8619
-0.250 -0.0633 0.01541 0.00790 0.0056 0.9184 0.8763
0.000 -0.0133 0.01540 0.00788 0.0015 0.9113 0.8884
0.250 0.0308 0.01542 0.00791 -0.0016 0.9031 0.9003
0.500 0.0837 0.01540 0.00791 -0.0065 0.8964 0.9060
0.750 0.1240 0.01538 0.00791 -0.0088 0.8849 0.9159
1.000 0.1719 0.01535 0.00791 -0.0127 0.8730 0.9214
1.250 0.2104 0.01532 0.00792 -0.0145 0.8566 0.9314
1.500 0.2567 0.01524 0.00789 -0.0179 0.8361 0.9377
1.750 0.2922 0.01519 0.00787 -0.0191 0.8083 0.9478
2.000 0.3363 0.01504 0.00773 -0.0220 0.7763 0.9539
2.250 0.3772 0.01493 0.00757 -0.0242 0.7439 0.9605
2.500 0.4223 0.01487 0.00741 -0.0273 0.7087 0.9642
2.750 0.4600 0.01495 0.00739 -0.0291 0.6703 0.9703
3.000 0.4943 0.01508 0.00742 -0.0303 0.6184 0.9766
3.250 0.5253 0.01529 0.00742 -0.0309 0.5491 0.9840
3.500 0.5569 0.01562 0.00735 -0.0317 0.4631 0.9901
3.750 0.5880 0.01607 0.00747 -0.0328 0.3986 0.9967
4.000 0.6123 0.01649 0.00767 -0.0325 0.3482 1.0000
4.250 0.6269 0.01686 0.00790 -0.0302 0.3080 1.0000
4.500 0.6411 0.01728 0.00818 -0.0279 0.2690 1.0000
4.750 0.6556 0.01773 0.00848 -0.0256 0.2334 1.0000
5.000 0.6702 0.01822 0.00883 -0.0233 0.2034 1.0000
5.250 0.6847 0.01874 0.00924 -0.0210 0.1777 1.0000
5.500 0.6995 0.01927 0.00969 -0.0187 0.1555 1.0000
5.750 0.7141 0.01983 0.01022 -0.0164 0.1390 1.0000
6.000 0.7288 0.02041 0.01077 -0.0141 0.1259 1.0000
6.250 0.7433 0.02101 0.01136 -0.0117 0.1152 1.0000
6.750 0.7718 0.02229 0.01266 -0.0070 0.0998 1.0000
7.000 0.7854 0.02300 0.01340 -0.0045 0.0947 1.0000
7.250 0.7996 0.02378 0.01423 -0.0021 0.0898 1.0000
7.500 0.8143 0.02449 0.01501 0.0002 0.0843 1.0000
7.750 0.8270 0.02538 0.01586 0.0026 0.0798 1.0000
8.000 0.8427 0.02621 0.01685 0.0047 0.0757 1.0000
8.250 0.8570 0.02700 0.01774 0.0069 0.0709 1.0000
8.500 0.8690 0.02796 0.01864 0.0093 0.0666 1.0000
8.750 0.8833 0.02885 0.01979 0.0115 0.0623 1.0000
9.000 0.8954 0.02969 0.02075 0.0139 0.0579 1.0000
9.250 0.9059 0.03070 0.02174 0.0164 0.0546 1.0000
9.500 0.9173 0.03186 0.02315 0.0190 0.0508 1.0000
9.750 0.9272 0.03296 0.02442 0.0216 0.0474 1.0000
10.000 0.9351 0.03395 0.02544 0.0244 0.0447 1.0000
10.250 0.9420 0.03537 0.02695 0.0271 0.0424 1.0000
10.500 0.9470 0.03684 0.02873 0.0303 0.0397 1.0000
10.750 0.9487 0.03819 0.03027 0.0338 0.0376 1.0000
11.000 0.9497 0.03943 0.03160 0.0373 0.0361 1.0000
11.250 0.9506 0.04068 0.03286 0.0403 0.0348 1.0000
11.500 0.9476 0.04266 0.03505 0.0436 0.0336 1.0000
11.750 0.9404 0.04501 0.03773 0.0467 0.0324 1.0000
12.000 0.9320 0.04738 0.04036 0.0493 0.0312 1.0000
12.250 0.9226 0.04994 0.04314 0.0514 0.0302 1.0000
12.500 0.9119 0.05282 0.04621 0.0528 0.0296 1.0000
12.750 0.8984 0.05629 0.04989 0.0534 0.0293 1.0000
13.000 0.8832 0.06023 0.05400 0.0530 0.0289 1.0000
13.250 0.8603 0.06575 0.05976 0.0513 0.0290 1.0000
13.500 0.8347 0.07233 0.06655 0.0479 0.0289 1.0000
13.750 0.7768 0.08659 0.08113 0.0384 0.0303 1.0000
14.000 0.6990 0.10907 0.10366 0.0250 0.0329 1.0000
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Polar data table (+)
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