N-13 (n13-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-13 (n13-il) Reynolds number: 500,000 Max Cl/Cd: 60.75 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n13-il-500000-n5.txt Download as CSV file: xf-n13-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.9714 0.10566 0.10227 -0.0204 1.0000 0.0067
-17.000 -0.9933 0.09750 0.09400 -0.0245 1.0000 0.0066
-16.750 -1.0171 0.08912 0.08548 -0.0287 1.0000 0.0066
-16.500 -1.0369 0.08155 0.07777 -0.0327 1.0000 0.0067
-16.250 -1.0574 0.07429 0.07036 -0.0364 1.0000 0.0066
-16.000 -1.0736 0.06794 0.06388 -0.0396 1.0000 0.0066
-15.750 -1.0869 0.06228 0.05807 -0.0424 1.0000 0.0067
-15.500 -1.0986 0.05718 0.05283 -0.0448 1.0000 0.0067
-15.250 -1.1113 0.05225 0.04774 -0.0467 1.0000 0.0067
-15.000 -1.1179 0.04843 0.04379 -0.0479 1.0000 0.0068
-14.750 -1.1229 0.04501 0.04023 -0.0486 1.0000 0.0069
-14.500 -1.1255 0.04209 0.03717 -0.0489 1.0000 0.0069
-14.250 -1.1292 0.03925 0.03420 -0.0488 1.0000 0.0070
-14.000 -1.1319 0.03672 0.03154 -0.0482 1.0000 0.0070
-13.750 -1.1326 0.03457 0.02927 -0.0472 1.0000 0.0071
-13.500 -1.1384 0.03220 0.02679 -0.0455 1.0000 0.0073
-13.250 -1.1387 0.03046 0.02494 -0.0436 1.0000 0.0074
-13.000 -1.1375 0.02894 0.02332 -0.0413 1.0000 0.0076
-12.750 -1.1345 0.02765 0.02193 -0.0389 1.0000 0.0077
-12.500 -1.1281 0.02665 0.02086 -0.0366 1.0000 0.0081
-12.250 -1.1222 0.02569 0.01982 -0.0340 1.0000 0.0082
-12.000 -1.1180 0.02469 0.01873 -0.0309 1.0000 0.0084
-11.750 -1.1114 0.02390 0.01786 -0.0279 1.0000 0.0087
-11.500 -1.1046 0.02319 0.01707 -0.0248 1.0000 0.0090
-11.250 -1.0986 0.02253 0.01633 -0.0213 1.0000 0.0093
-11.000 -1.0928 0.02192 0.01564 -0.0176 1.0000 0.0095
-10.750 -1.0835 0.02135 0.01497 -0.0145 1.0000 0.0097
-10.500 -1.0754 0.02054 0.01409 -0.0113 1.0000 0.0100
-10.250 -1.0657 0.01979 0.01327 -0.0083 1.0000 0.0105
-10.000 -1.0539 0.01915 0.01258 -0.0056 1.0000 0.0111
-9.750 -1.0411 0.01859 0.01197 -0.0030 1.0000 0.0116
-9.500 -1.0281 0.01807 0.01138 -0.0004 1.0000 0.0122
-9.000 -0.9816 0.01696 0.01012 0.0004 0.9976 0.0141
-8.750 -0.9528 0.01631 0.00945 -0.0004 0.9951 0.0161
-8.500 -0.9252 0.01575 0.00886 -0.0008 0.9926 0.0187
-8.250 -0.8983 0.01521 0.00837 -0.0011 0.9895 0.0239
-8.000 -0.8695 0.01478 0.00800 -0.0017 0.9868 0.0321
-7.750 -0.8396 0.01450 0.00768 -0.0025 0.9843 0.0370
-7.500 -0.8151 0.01410 0.00727 -0.0021 0.9795 0.0401
-7.000 -0.7612 0.01348 0.00658 -0.0022 0.9713 0.0452
-6.750 -0.7344 0.01324 0.00629 -0.0022 0.9663 0.0470
-6.500 -0.7074 0.01283 0.00585 -0.0023 0.9621 0.0506
-6.250 -0.6831 0.01248 0.00549 -0.0017 0.9563 0.0534
-6.000 -0.6552 0.01215 0.00514 -0.0019 0.9528 0.0569
-5.750 -0.6262 0.01182 0.00480 -0.0023 0.9496 0.0628
-5.500 -0.5996 0.01140 0.00452 -0.0024 0.9454 0.0790
-5.250 -0.5689 0.01116 0.00430 -0.0031 0.9424 0.0943
-5.000 -0.5363 0.01092 0.00406 -0.0042 0.9397 0.1020
-4.750 -0.5015 0.01074 0.00383 -0.0058 0.9375 0.1058
-4.500 -0.4688 0.01051 0.00361 -0.0070 0.9342 0.1106
-4.250 -0.4344 0.01029 0.00339 -0.0086 0.9312 0.1153
-4.000 -0.3983 0.01009 0.00318 -0.0106 0.9287 0.1203
-3.750 -0.3618 0.00987 0.00298 -0.0126 0.9262 0.1269
-3.500 -0.3242 0.00966 0.00279 -0.0149 0.9234 0.1334
-3.250 -0.2909 0.00942 0.00261 -0.0163 0.9185 0.1482
-3.000 -0.2555 0.00909 0.00242 -0.0182 0.9124 0.1855
-2.750 -0.2228 0.00883 0.00226 -0.0194 0.9053 0.2173
-2.500 -0.1944 0.00852 0.00210 -0.0197 0.8973 0.2614
-2.250 -0.1713 0.00814 0.00198 -0.0189 0.8890 0.3322
-2.000 -0.1458 0.00790 0.00189 -0.0185 0.8810 0.3800
-1.750 -0.1234 0.00772 0.00183 -0.0174 0.8717 0.4118
-1.500 -0.1005 0.00753 0.00176 -0.0163 0.8614 0.4471
-1.250 -0.0789 0.00733 0.00170 -0.0149 0.8490 0.4858
-1.000 -0.0593 0.00710 0.00164 -0.0131 0.8335 0.5331
-0.750 -0.0390 0.00692 0.00160 -0.0113 0.8118 0.5743
-0.500 -0.0168 0.00684 0.00151 -0.0099 0.7773 0.6010
-0.250 0.0053 0.00686 0.00144 -0.0084 0.7438 0.6235
0.000 0.0270 0.00693 0.00142 -0.0069 0.7165 0.6421
0.250 0.0486 0.00699 0.00144 -0.0055 0.6911 0.6622
0.500 0.0708 0.00703 0.00146 -0.0041 0.6712 0.6822
0.750 0.0941 0.00704 0.00149 -0.0030 0.6550 0.6996
1.000 0.1173 0.00704 0.00152 -0.0019 0.6387 0.7170
1.250 0.1405 0.00704 0.00155 -0.0008 0.6220 0.7347
1.500 0.1637 0.00705 0.00159 0.0003 0.6028 0.7509
1.750 0.1858 0.00709 0.00163 0.0016 0.5766 0.7692
2.000 0.2073 0.00715 0.00168 0.0031 0.5410 0.7910
2.250 0.2257 0.00740 0.00177 0.0052 0.4751 0.8149
2.500 0.2471 0.00772 0.00195 0.0066 0.4153 0.8432
2.750 0.2761 0.00803 0.00218 0.0063 0.3721 0.8731
3.000 0.3080 0.00831 0.00241 0.0054 0.3395 0.8946
3.250 0.3368 0.00864 0.00263 0.0052 0.3035 0.9156
3.500 0.3667 0.00900 0.00287 0.0048 0.2691 0.9318
3.750 0.3988 0.00939 0.00313 0.0037 0.2320 0.9398
4.000 0.4245 0.00972 0.00334 0.0041 0.2030 0.9476
4.250 0.4580 0.01008 0.00359 0.0027 0.1753 0.9508
4.500 0.4876 0.01041 0.00383 0.0022 0.1520 0.9547
4.750 0.5102 0.01069 0.00404 0.0032 0.1331 0.9606
5.000 0.5435 0.01104 0.00430 0.0018 0.1124 0.9623
5.250 0.5750 0.01140 0.00459 0.0008 0.0953 0.9644
5.500 0.6051 0.01171 0.00487 0.0002 0.0843 0.9672
5.750 0.6313 0.01201 0.00514 0.0004 0.0767 0.9711
6.000 0.6590 0.01232 0.00545 0.0002 0.0698 0.9740
6.250 0.6908 0.01263 0.00577 -0.0008 0.0644 0.9757
6.500 0.7212 0.01295 0.00608 -0.0016 0.0592 0.9777
6.750 0.7492 0.01332 0.00643 -0.0019 0.0538 0.9804
7.000 0.7752 0.01358 0.00674 -0.0017 0.0506 0.9836
7.250 0.8046 0.01391 0.00707 -0.0023 0.0469 0.9853
7.500 0.8342 0.01431 0.00746 -0.0030 0.0429 0.9870
7.750 0.8638 0.01460 0.00781 -0.0037 0.0403 0.9889
8.000 0.8916 0.01495 0.00816 -0.0040 0.0372 0.9910
8.250 0.9181 0.01536 0.00859 -0.0041 0.0340 0.9932
8.500 0.9473 0.01571 0.00900 -0.0048 0.0312 0.9951
8.750 0.9774 0.01617 0.00944 -0.0057 0.0274 0.9972
9.000 1.0079 0.01659 0.00990 -0.0067 0.0237 0.9992
9.250 1.0299 0.01708 0.01039 -0.0060 0.0205 1.0000
9.500 1.0435 0.01750 0.01085 -0.0034 0.0184 1.0000
9.750 1.0558 0.01798 0.01136 -0.0007 0.0167 1.0000
10.000 1.0672 0.01849 0.01191 0.0023 0.0153 1.0000
10.250 1.0786 0.01896 0.01244 0.0052 0.0142 1.0000
10.500 1.0887 0.01947 0.01302 0.0083 0.0135 1.0000
10.750 1.0971 0.02007 0.01365 0.0116 0.0126 1.0000
11.000 1.1029 0.02069 0.01432 0.0155 0.0117 1.0000
11.250 1.1067 0.02123 0.01493 0.0197 0.0114 1.0000
11.500 1.1122 0.02176 0.01556 0.0234 0.0110 1.0000
11.750 1.1185 0.02236 0.01624 0.0269 0.0106 1.0000
12.000 1.1248 0.02306 0.01702 0.0302 0.0102 1.0000
12.250 1.1314 0.02382 0.01786 0.0333 0.0097 1.0000
12.500 1.1374 0.02469 0.01881 0.0362 0.0095 1.0000
12.750 1.1431 0.02563 0.01984 0.0389 0.0093 1.0000
13.000 1.1461 0.02681 0.02111 0.0417 0.0089 1.0000
13.250 1.1496 0.02803 0.02242 0.0441 0.0087 1.0000
13.500 1.1490 0.02961 0.02411 0.0466 0.0084 1.0000
13.750 1.1529 0.03098 0.02560 0.0484 0.0082 1.0000
14.000 1.1551 0.03257 0.02731 0.0501 0.0081 1.0000
14.250 1.1552 0.03445 0.02932 0.0515 0.0079 1.0000
14.500 1.1545 0.03655 0.03155 0.0525 0.0079 1.0000
14.750 1.1530 0.03894 0.03406 0.0530 0.0076 1.0000
15.000 1.1524 0.04142 0.03666 0.0531 0.0075 1.0000
15.250 1.1446 0.04492 0.04031 0.0526 0.0074 1.0000
15.500 1.1388 0.04844 0.04395 0.0517 0.0072 1.0000
15.750 1.1282 0.05285 0.04851 0.0500 0.0072 1.0000
16.000 1.1189 0.05748 0.05327 0.0479 0.0071 1.0000
16.250 1.0999 0.06395 0.05992 0.0445 0.0071 1.0000
16.500 1.0778 0.07139 0.06753 0.0403 0.0072 1.0000
16.750 1.0570 0.07878 0.07506 0.0363 0.0072 1.0000
17.000 1.0265 0.08802 0.08448 0.0314 0.0073 1.0000
17.250 0.9989 0.09695 0.09354 0.0268 0.0073 1.0000
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Polar data table (+)
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