N-13 (n13-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-13 (n13-il) Reynolds number: 500,000 Max Cl/Cd: 60.24 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n13-il-500000.txt Download as CSV file: xf-n13-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.8361 0.13406 0.13141 -0.0075 1.0000 0.0134
-17.000 -0.8869 0.11758 0.11475 -0.0164 1.0000 0.0131
-16.750 -0.9187 0.10622 0.10324 -0.0229 1.0000 0.0131
-16.500 -0.9507 0.09548 0.09233 -0.0289 1.0000 0.0128
-16.250 -0.9736 0.08707 0.08376 -0.0338 1.0000 0.0127
-16.000 -0.9966 0.07904 0.07555 -0.0384 1.0000 0.0127
-15.750 -1.0165 0.07207 0.06841 -0.0421 1.0000 0.0126
-15.500 -1.0321 0.06612 0.06230 -0.0453 1.0000 0.0128
-15.250 -1.0471 0.06067 0.05668 -0.0476 1.0000 0.0127
-15.000 -1.0572 0.05622 0.05207 -0.0494 1.0000 0.0128
-14.750 -1.0678 0.05197 0.04764 -0.0507 1.0000 0.0130
-14.500 -1.0778 0.04803 0.04353 -0.0512 1.0000 0.0129
-14.250 -1.0824 0.04498 0.04033 -0.0515 1.0000 0.0131
-14.000 -1.0865 0.04215 0.03733 -0.0512 1.0000 0.0133
-13.750 -1.0881 0.03975 0.03478 -0.0505 1.0000 0.0134
-13.250 -1.0894 0.03549 0.03021 -0.0480 1.0000 0.0136
-13.000 -1.0985 0.03255 0.02713 -0.0456 1.0000 0.0141
-12.750 -1.1000 0.03061 0.02509 -0.0432 1.0000 0.0144
-12.500 -1.0969 0.02925 0.02365 -0.0409 1.0000 0.0147
-12.250 -1.0914 0.02815 0.02248 -0.0385 1.0000 0.0151
-12.000 -1.0861 0.02705 0.02131 -0.0359 1.0000 0.0155
-11.750 -1.0804 0.02604 0.02020 -0.0331 1.0000 0.0160
-11.500 -1.0751 0.02504 0.01910 -0.0300 1.0000 0.0164
-11.250 -1.0692 0.02418 0.01814 -0.0268 1.0000 0.0167
-11.000 -1.0625 0.02346 0.01733 -0.0235 1.0000 0.0171
-10.750 -1.0615 0.02250 0.01628 -0.0190 1.0000 0.0174
-10.500 -1.0619 0.02142 0.01514 -0.0144 1.0000 0.0180
-10.250 -1.0539 0.02061 0.01428 -0.0111 1.0000 0.0188
-10.000 -1.0430 0.01995 0.01358 -0.0082 1.0000 0.0196
-9.750 -1.0314 0.01933 0.01290 -0.0054 1.0000 0.0203
-9.500 -1.0184 0.01880 0.01230 -0.0028 1.0000 0.0213
-9.250 -1.0097 0.01804 0.01150 0.0005 1.0000 0.0226
-9.000 -0.9981 0.01753 0.01098 0.0034 1.0000 0.0241
-8.750 -0.9860 0.01717 0.01058 0.0063 1.0000 0.0257
-8.500 -0.9772 0.01667 0.01005 0.0097 1.0000 0.0280
-8.250 -0.9651 0.01634 0.00973 0.0126 1.0000 0.0308
-8.000 -0.9515 0.01603 0.00937 0.0152 1.0000 0.0343
-7.750 -0.9372 0.01568 0.00905 0.0176 1.0000 0.0389
-7.500 -0.9132 0.01529 0.00861 0.0180 0.9990 0.0441
-7.250 -0.8831 0.01486 0.00815 0.0170 0.9970 0.0490
-7.000 -0.8520 0.01456 0.00778 0.0160 0.9951 0.0523
-6.750 -0.8234 0.01397 0.00719 0.0154 0.9929 0.0572
-6.500 -0.7943 0.01357 0.00674 0.0148 0.9901 0.0614
-6.250 -0.7640 0.01318 0.00637 0.0140 0.9876 0.0672
-6.000 -0.7330 0.01281 0.00612 0.0130 0.9856 0.0797
-5.750 -0.6993 0.01261 0.00597 0.0115 0.9842 0.0992
-5.500 -0.6730 0.01236 0.00573 0.0117 0.9811 0.1118
-5.250 -0.6448 0.01203 0.00545 0.0114 0.9780 0.1221
-5.000 -0.6128 0.01180 0.00520 0.0103 0.9755 0.1300
-4.750 -0.5794 0.01153 0.00495 0.0089 0.9736 0.1386
-4.500 -0.5460 0.01123 0.00472 0.0075 0.9719 0.1514
-4.250 -0.5233 0.01095 0.00451 0.0085 0.9669 0.1680
-4.000 -0.4927 0.01060 0.00428 0.0077 0.9639 0.1965
-3.750 -0.4602 0.01014 0.00401 0.0064 0.9615 0.2386
-3.500 -0.4280 0.00951 0.00373 0.0051 0.9597 0.3167
-3.250 -0.4077 0.00912 0.00357 0.0065 0.9535 0.3749
-3.000 -0.3756 0.00875 0.00337 0.0055 0.9504 0.4206
-2.750 -0.3395 0.00829 0.00311 0.0037 0.9479 0.4708
-2.500 -0.3086 0.00790 0.00290 0.0031 0.9432 0.5172
-2.250 -0.2765 0.00754 0.00272 0.0022 0.9383 0.5614
-2.000 -0.2379 0.00723 0.00255 0.0000 0.9351 0.6040
-1.750 -0.1959 0.00699 0.00241 -0.0030 0.9319 0.6356
-1.500 -0.1635 0.00683 0.00232 -0.0038 0.9244 0.6623
-1.250 -0.1213 0.00663 0.00220 -0.0068 0.9189 0.6897
-0.750 -0.0548 0.00644 0.00210 -0.0088 0.9019 0.7289
-0.500 -0.0277 0.00638 0.00210 -0.0084 0.8910 0.7478
-0.250 -0.0020 0.00631 0.00209 -0.0077 0.8794 0.7666
0.000 0.0233 0.00624 0.00208 -0.0069 0.8661 0.7856
0.250 0.0478 0.00615 0.00206 -0.0058 0.8496 0.8063
0.500 0.0736 0.00607 0.00205 -0.0050 0.8306 0.8285
0.750 0.1008 0.00604 0.00207 -0.0045 0.8069 0.8511
1.000 0.1319 0.00608 0.00209 -0.0048 0.7787 0.8697
1.250 0.1630 0.00622 0.00214 -0.0052 0.7507 0.8856
1.500 0.1930 0.00643 0.00226 -0.0054 0.7261 0.8994
2.000 0.2444 0.00688 0.00255 -0.0039 0.6804 0.9247
2.250 0.2791 0.00715 0.00273 -0.0052 0.6494 0.9295
2.500 0.3001 0.00736 0.00286 -0.0034 0.6210 0.9399
2.750 0.3367 0.00764 0.00302 -0.0052 0.5786 0.9426
3.000 0.3732 0.00807 0.00324 -0.0069 0.5144 0.9466
3.250 0.3967 0.00861 0.00348 -0.0059 0.4479 0.9556
3.500 0.4377 0.00917 0.00380 -0.0089 0.3909 0.9582
3.750 0.4753 0.00962 0.00407 -0.0111 0.3433 0.9618
4.250 0.5378 0.01044 0.00452 -0.0129 0.2533 0.9713
4.500 0.5728 0.01087 0.00476 -0.0147 0.2084 0.9739
4.750 0.6061 0.01128 0.00500 -0.0161 0.1728 0.9775
5.000 0.6329 0.01173 0.00530 -0.0162 0.1398 0.9828
5.250 0.6688 0.01216 0.00557 -0.0182 0.1089 0.9848
5.500 0.7036 0.01254 0.00587 -0.0200 0.0913 0.9875
5.750 0.7362 0.01294 0.00622 -0.0213 0.0803 0.9908
6.000 0.7675 0.01334 0.00658 -0.0223 0.0716 0.9941
6.250 0.8028 0.01361 0.00688 -0.0242 0.0655 0.9964
6.500 0.8359 0.01405 0.00728 -0.0256 0.0591 0.9991
6.750 0.8609 0.01431 0.00760 -0.0253 0.0553 1.0000
7.000 0.8783 0.01458 0.00789 -0.0234 0.0520 1.0000
7.250 0.8922 0.01510 0.00840 -0.0208 0.0482 1.0000
7.500 0.9094 0.01538 0.00874 -0.0188 0.0457 1.0000
7.750 0.9269 0.01563 0.00902 -0.0169 0.0427 1.0000
8.000 0.9407 0.01614 0.00951 -0.0144 0.0396 1.0000
8.250 0.9553 0.01658 0.01002 -0.0119 0.0372 1.0000
8.500 0.9716 0.01688 0.01035 -0.0098 0.0345 1.0000
8.750 0.9835 0.01745 0.01092 -0.0070 0.0320 1.0000
9.000 0.9970 0.01791 0.01144 -0.0044 0.0299 1.0000
9.250 1.0108 0.01832 0.01190 -0.0018 0.0280 1.0000
9.500 1.0225 0.01882 0.01242 0.0011 0.0265 1.0000
9.750 1.0269 0.01975 0.01339 0.0052 0.0250 1.0000
10.000 1.0386 0.02020 0.01393 0.0081 0.0240 1.0000
10.250 1.0483 0.02073 0.01453 0.0113 0.0230 1.0000
10.500 1.0570 0.02127 0.01512 0.0146 0.0221 1.0000
10.750 1.0625 0.02173 0.01559 0.0185 0.0211 1.0000
11.000 1.0592 0.02265 0.01656 0.0238 0.0204 1.0000
11.250 1.0616 0.02347 0.01748 0.0279 0.0197 1.0000
11.500 1.0690 0.02408 0.01819 0.0311 0.0191 1.0000
11.750 1.0753 0.02485 0.01904 0.0343 0.0185 1.0000
12.000 1.0802 0.02582 0.02011 0.0375 0.0181 1.0000
12.250 1.0867 0.02667 0.02102 0.0401 0.0174 1.0000
12.500 1.0916 0.02773 0.02216 0.0428 0.0170 1.0000
12.750 1.0954 0.02893 0.02341 0.0452 0.0166 1.0000
13.000 1.0943 0.03071 0.02530 0.0479 0.0163 1.0000
13.250 1.0883 0.03310 0.02784 0.0506 0.0159 1.0000
13.500 1.0905 0.03470 0.02959 0.0523 0.0157 1.0000
13.750 1.0916 0.03649 0.03153 0.0537 0.0154 1.0000
14.000 1.0902 0.03866 0.03385 0.0549 0.0151 1.0000
14.250 1.0864 0.04127 0.03662 0.0556 0.0150 1.0000
14.500 1.0841 0.04383 0.03932 0.0558 0.0147 1.0000
14.750 1.0798 0.04685 0.04247 0.0555 0.0144 1.0000
15.000 1.0731 0.05033 0.04610 0.0547 0.0142 1.0000
15.250 1.0624 0.05461 0.05053 0.0534 0.0141 1.0000
15.500 1.0588 0.05815 0.05417 0.0517 0.0138 1.0000
15.750 1.0446 0.06349 0.05967 0.0492 0.0137 1.0000
16.000 1.0390 0.06785 0.06409 0.0467 0.0134 1.0000
16.250 1.0177 0.07501 0.07145 0.0427 0.0135 1.0000
16.500 0.9813 0.08532 0.08205 0.0369 0.0138 1.0000
16.750 0.9411 0.09701 0.09398 0.0302 0.0141 1.0000
17.000 0.9155 0.10643 0.10353 0.0247 0.0140 1.0000
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Polar data table (+)
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