N-13 (n13-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-13 (n13-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.98 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n13-il-1000000-n5.txt Download as CSV file: xf-n13-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -1.0384 0.11417 0.11144 -0.0156 1.0000 0.0045
-18.250 -1.0816 0.10212 0.09924 -0.0216 1.0000 0.0044
-18.000 -1.1260 0.09007 0.08701 -0.0277 1.0000 0.0043
-17.750 -1.1691 0.07861 0.07535 -0.0337 1.0000 0.0043
-17.500 -1.1951 0.07061 0.06720 -0.0378 1.0000 0.0042
-17.250 -1.2118 0.06438 0.06083 -0.0409 1.0000 0.0043
-17.000 -1.2327 0.05782 0.05412 -0.0441 1.0000 0.0042
-16.750 -1.2477 0.05252 0.04867 -0.0464 1.0000 0.0043
-16.500 -1.2530 0.04882 0.04487 -0.0476 1.0000 0.0044
-16.250 -1.2604 0.04507 0.04100 -0.0486 1.0000 0.0044
-16.000 -1.2670 0.04164 0.03745 -0.0491 1.0000 0.0044
-15.750 -1.2661 0.03922 0.03495 -0.0492 1.0000 0.0046
-15.500 -1.2664 0.03682 0.03244 -0.0489 1.0000 0.0046
-15.250 -1.2729 0.03400 0.02949 -0.0482 1.0000 0.0046
-15.000 -1.2708 0.03217 0.02756 -0.0472 1.0000 0.0047
-14.750 -1.2663 0.03064 0.02595 -0.0460 1.0000 0.0048
-14.500 -1.2617 0.02923 0.02445 -0.0445 1.0000 0.0049
-14.250 -1.2578 0.02787 0.02299 -0.0427 1.0000 0.0049
-14.000 -1.2547 0.02655 0.02158 -0.0405 1.0000 0.0050
-13.750 -1.2488 0.02549 0.02044 -0.0383 1.0000 0.0050
-13.500 -1.2441 0.02442 0.01929 -0.0357 1.0000 0.0051
-13.250 -1.2397 0.02340 0.01819 -0.0329 1.0000 0.0053
-13.000 -1.2340 0.02252 0.01723 -0.0300 1.0000 0.0054
-12.750 -1.2275 0.02175 0.01639 -0.0269 1.0000 0.0055
-12.500 -1.2197 0.02111 0.01571 -0.0239 1.0000 0.0058
-12.250 -1.2126 0.02053 0.01506 -0.0206 1.0000 0.0058
-12.000 -1.2067 0.01997 0.01444 -0.0169 1.0000 0.0060
-11.750 -1.1992 0.01946 0.01388 -0.0134 1.0000 0.0061
-11.500 -1.1868 0.01895 0.01333 -0.0108 1.0000 0.0063
-11.250 -1.1741 0.01842 0.01274 -0.0083 1.0000 0.0065
-11.000 -1.1604 0.01793 0.01220 -0.0059 1.0000 0.0067
-10.750 -1.1360 0.01741 0.01163 -0.0058 0.9993 0.0069
-10.500 -1.1078 0.01688 0.01105 -0.0065 0.9980 0.0071
-10.250 -1.0803 0.01620 0.01031 -0.0071 0.9962 0.0077
-10.000 -1.0512 0.01566 0.00974 -0.0080 0.9945 0.0083
-9.750 -1.0253 0.01517 0.00922 -0.0080 0.9923 0.0087
-9.500 -0.9989 0.01471 0.00872 -0.0081 0.9898 0.0092
-9.250 -0.9711 0.01431 0.00828 -0.0085 0.9874 0.0097
-8.750 -0.9226 0.01340 0.00731 -0.0077 0.9794 0.0115
-8.250 -0.8792 0.01268 0.00654 -0.0056 0.9618 0.0134
-8.000 -0.8538 0.01224 0.00610 -0.0053 0.9536 0.0165
-7.750 -0.8248 0.01174 0.00566 -0.0060 0.9486 0.0243
-7.500 -0.7934 0.01136 0.00534 -0.0071 0.9449 0.0320
-7.250 -0.7598 0.01107 0.00506 -0.0085 0.9419 0.0359
-6.750 -0.6866 0.01048 0.00444 -0.0129 0.9360 0.0413
-6.500 -0.6490 0.01021 0.00417 -0.0153 0.9333 0.0439
-6.250 -0.6108 0.00999 0.00392 -0.0178 0.9311 0.0456
-6.000 -0.5728 0.00978 0.00369 -0.0203 0.9282 0.0468
-5.750 -0.5354 0.00954 0.00341 -0.0226 0.9246 0.0499
-5.500 -0.5008 0.00928 0.00316 -0.0243 0.9203 0.0541
-5.250 -0.4680 0.00909 0.00295 -0.0256 0.9154 0.0568
-5.000 -0.4372 0.00890 0.00275 -0.0264 0.9109 0.0640
-4.750 -0.4105 0.00864 0.00261 -0.0264 0.9067 0.0896
-4.500 -0.3836 0.00853 0.00250 -0.0262 0.9026 0.0945
-4.250 -0.3562 0.00841 0.00238 -0.0262 0.8979 0.0991
-4.000 -0.3291 0.00833 0.00228 -0.0261 0.8924 0.1029
-3.750 -0.3038 0.00826 0.00219 -0.0255 0.8855 0.1055
-3.500 -0.2769 0.00820 0.00210 -0.0253 0.8796 0.1072
-3.250 -0.2528 0.00810 0.00201 -0.0245 0.8730 0.1110
-3.000 -0.2272 0.00802 0.00192 -0.0239 0.8668 0.1133
-2.750 -0.2025 0.00793 0.00184 -0.0232 0.8596 0.1159
-2.500 -0.1774 0.00785 0.00175 -0.0226 0.8513 0.1185
-2.250 -0.1531 0.00777 0.00167 -0.0218 0.8400 0.1213
-2.000 -0.1299 0.00767 0.00158 -0.0207 0.8208 0.1296
-1.750 -0.1119 0.00762 0.00144 -0.0184 0.7669 0.1500
-1.500 -0.0954 0.00749 0.00133 -0.0160 0.7280 0.2039
-1.250 -0.0748 0.00738 0.00127 -0.0145 0.7064 0.2398
-1.000 -0.0545 0.00714 0.00119 -0.0130 0.6907 0.2976
-0.750 -0.0327 0.00700 0.00115 -0.0117 0.6748 0.3420
-0.500 -0.0118 0.00687 0.00111 -0.0103 0.6548 0.3891
-0.250 0.0100 0.00673 0.00108 -0.0090 0.6359 0.4300
0.000 0.0319 0.00660 0.00105 -0.0077 0.6186 0.4715
0.250 0.0541 0.00648 0.00104 -0.0066 0.6038 0.5120
0.500 0.0764 0.00640 0.00104 -0.0053 0.5858 0.5494
0.750 0.0981 0.00635 0.00105 -0.0040 0.5640 0.5853
1.000 0.1199 0.00640 0.00107 -0.0027 0.5294 0.6086
1.250 0.1406 0.00654 0.00111 -0.0011 0.4817 0.6277
1.500 0.1609 0.00676 0.00118 0.0004 0.4300 0.6440
1.750 0.1823 0.00691 0.00126 0.0018 0.3934 0.6625
2.000 0.2040 0.00705 0.00133 0.0031 0.3564 0.6818
2.250 0.2264 0.00718 0.00140 0.0042 0.3254 0.6976
2.500 0.2490 0.00730 0.00147 0.0053 0.2961 0.7123
2.750 0.2713 0.00744 0.00155 0.0065 0.2677 0.7276
3.000 0.2935 0.00755 0.00164 0.0077 0.2427 0.7443
3.500 0.3354 0.00778 0.00185 0.0106 0.1925 0.7914
3.750 0.3560 0.00784 0.00198 0.0122 0.1727 0.8241
4.000 0.3779 0.00793 0.00216 0.0135 0.1533 0.8716
4.250 0.4064 0.00812 0.00240 0.0134 0.1360 0.9108
4.500 0.4342 0.00835 0.00261 0.0134 0.1190 0.9314
4.750 0.4627 0.00862 0.00282 0.0132 0.1014 0.9440
5.000 0.4946 0.00890 0.00305 0.0122 0.0880 0.9501
5.250 0.5231 0.00916 0.00327 0.0120 0.0780 0.9565
5.500 0.5483 0.00936 0.00346 0.0125 0.0714 0.9609
5.750 0.5808 0.00961 0.00369 0.0113 0.0649 0.9627
6.000 0.6118 0.00986 0.00392 0.0104 0.0595 0.9647
6.250 0.6418 0.01013 0.00417 0.0098 0.0537 0.9668
6.500 0.6703 0.01035 0.00439 0.0095 0.0500 0.9693
6.750 0.6930 0.01060 0.00462 0.0105 0.0458 0.9731
7.000 0.7244 0.01087 0.00489 0.0095 0.0425 0.9741
7.250 0.7550 0.01113 0.00515 0.0087 0.0394 0.9751
7.500 0.7846 0.01143 0.00544 0.0081 0.0365 0.9764
7.750 0.8133 0.01173 0.00574 0.0077 0.0338 0.9779
8.000 0.8418 0.01201 0.00602 0.0073 0.0313 0.9798
8.250 0.8676 0.01234 0.00634 0.0075 0.0282 0.9826
8.500 0.8944 0.01265 0.00667 0.0075 0.0260 0.9848
8.750 0.9242 0.01302 0.00703 0.0067 0.0222 0.9859
9.000 0.9526 0.01343 0.00742 0.0062 0.0183 0.9871
9.250 0.9798 0.01389 0.00787 0.0059 0.0149 0.9887
9.500 1.0064 0.01434 0.00833 0.0057 0.0130 0.9904
9.750 1.0316 0.01481 0.00883 0.0058 0.0115 0.9923
10.000 1.0559 0.01523 0.00929 0.0062 0.0108 0.9940
10.250 1.0831 0.01571 0.00980 0.0058 0.0099 0.9954
10.500 1.1102 0.01623 0.01036 0.0054 0.0093 0.9969
10.750 1.1366 0.01687 0.01104 0.0051 0.0085 0.9984
11.000 1.1638 0.01738 0.01161 0.0047 0.0082 0.9996
11.250 1.1814 0.01784 0.01212 0.0062 0.0078 1.0000
11.500 1.1907 0.01827 0.01260 0.0095 0.0075 1.0000
11.750 1.1970 0.01871 0.01309 0.0134 0.0073 1.0000
12.000 1.2001 0.01911 0.01353 0.0178 0.0069 1.0000
12.250 1.2040 0.01962 0.01409 0.0220 0.0067 1.0000
12.500 1.2099 0.02017 0.01470 0.0257 0.0065 1.0000
12.750 1.2162 0.02083 0.01541 0.0290 0.0062 1.0000
13.000 1.2236 0.02151 0.01617 0.0321 0.0061 1.0000
13.250 1.2333 0.02213 0.01686 0.0346 0.0060 1.0000
13.500 1.2415 0.02290 0.01769 0.0371 0.0058 1.0000
13.750 1.2496 0.02371 0.01859 0.0395 0.0057 1.0000
14.000 1.2567 0.02465 0.01961 0.0418 0.0056 1.0000
14.250 1.2632 0.02569 0.02073 0.0439 0.0055 1.0000
14.500 1.2699 0.02677 0.02188 0.0458 0.0054 1.0000
14.750 1.2747 0.02804 0.02324 0.0477 0.0052 1.0000
15.000 1.2800 0.02934 0.02462 0.0492 0.0052 1.0000
15.250 1.2820 0.03098 0.02636 0.0508 0.0051 1.0000
15.500 1.2832 0.03281 0.02828 0.0520 0.0049 1.0000
15.750 1.2853 0.03469 0.03025 0.0528 0.0048 1.0000
16.000 1.2835 0.03712 0.03279 0.0532 0.0047 1.0000
16.250 1.2800 0.03991 0.03568 0.0532 0.0046 1.0000
16.500 1.2741 0.04319 0.03908 0.0528 0.0047 1.0000
16.750 1.2654 0.04702 0.04303 0.0517 0.0045 1.0000
17.000 1.2528 0.05166 0.04782 0.0500 0.0046 1.0000
17.250 1.2385 0.05693 0.05322 0.0475 0.0045 1.0000
17.500 1.2175 0.06369 0.06014 0.0439 0.0044 1.0000
17.750 1.1923 0.07162 0.06824 0.0395 0.0045 1.0000
18.000 1.1609 0.08073 0.07752 0.0346 0.0045 1.0000
18.250 1.1261 0.09066 0.08762 0.0294 0.0046 1.0000
18.500 1.0756 0.10368 0.10083 0.0226 0.0046 1.0000
18.750 1.0233 0.11736 0.11469 0.0156 0.0048 1.0000
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