NLF(1)-0115 (nlf0115-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NLF(1)-0115 (nlf0115-il) Reynolds number: 100,000 Max Cl/Cd: 41.37 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf0115-il-100000-n5.txt Download as CSV file: xf-nlf0115-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NLF(1)-0115
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4437 0.09678 0.09146 -0.0580 1.0000 0.0317
-11.250 -0.4467 0.09287 0.08759 -0.0590 1.0000 0.0314
-11.000 -0.4579 0.08740 0.08214 -0.0612 1.0000 0.0310
-10.750 -0.4743 0.08214 0.07689 -0.0631 1.0000 0.0306
-10.500 -0.4955 0.07730 0.07203 -0.0642 1.0000 0.0303
-10.250 -0.5185 0.07326 0.06797 -0.0640 1.0000 0.0300
-10.000 -0.5441 0.06982 0.06448 -0.0625 1.0000 0.0297
-9.750 -0.5704 0.06715 0.06178 -0.0596 1.0000 0.0295
-9.500 -0.5996 0.06520 0.05982 -0.0551 1.0000 0.0293
-9.250 -0.6270 0.06369 0.05827 -0.0498 0.9994 0.0292
-9.000 -0.6244 0.05852 0.05274 -0.0522 0.9892 0.0287
-8.750 -0.6190 0.05371 0.04754 -0.0535 0.9794 0.0283
-8.500 -0.6084 0.04945 0.04285 -0.0544 0.9707 0.0280
-8.250 -0.5955 0.04575 0.03872 -0.0546 0.9613 0.0278
-8.000 -0.5810 0.04259 0.03516 -0.0542 0.9515 0.0278
-7.750 -0.5579 0.03956 0.03171 -0.0549 0.9454 0.0279
-7.500 -0.5396 0.03739 0.02923 -0.0542 0.9352 0.0283
-7.250 -0.5111 0.03524 0.02672 -0.0553 0.9299 0.0293
-7.000 -0.4892 0.03341 0.02455 -0.0547 0.9201 0.0305
-6.750 -0.4559 0.03136 0.02215 -0.0559 0.9160 0.0312
-6.500 -0.4304 0.02979 0.02034 -0.0555 0.9069 0.0316
-6.250 -0.3960 0.02811 0.01850 -0.0568 0.9026 0.0322
-6.000 -0.3679 0.02685 0.01722 -0.0570 0.8954 0.0330
-5.750 -0.3370 0.02568 0.01603 -0.0578 0.8897 0.0341
-5.500 -0.3052 0.02460 0.01491 -0.0587 0.8850 0.0355
-5.250 -0.2805 0.02384 0.01406 -0.0582 0.8768 0.0380
-5.000 -0.2514 0.02289 0.01310 -0.0588 0.8718 0.0407
-4.750 -0.2301 0.02220 0.01241 -0.0579 0.8634 0.0433
-4.500 -0.2039 0.02147 0.01157 -0.0577 0.8577 0.0467
-4.250 -0.1822 0.02082 0.01088 -0.0568 0.8509 0.0512
-4.000 -0.1600 0.02022 0.01028 -0.0560 0.8444 0.0617
-3.750 -0.1364 0.01937 0.00959 -0.0555 0.8398 0.0949
-3.500 -0.1308 0.01823 0.00908 -0.0524 0.8310 0.2170
-3.250 -0.1333 0.01728 0.00997 -0.0461 0.8249 0.6348
-3.000 -0.1153 0.01848 0.01117 -0.0423 0.8183 0.6963
-2.750 -0.0912 0.01973 0.01241 -0.0388 0.8135 0.7338
-2.500 -0.0609 0.02062 0.01323 -0.0367 0.8102 0.7575
-2.250 -0.0343 0.02069 0.01315 -0.0362 0.8062 0.7666
-2.000 -0.0147 0.02049 0.01281 -0.0353 0.8000 0.7698
-1.750 0.0139 0.02033 0.01250 -0.0357 0.7958 0.7715
-1.500 0.0449 0.02016 0.01218 -0.0365 0.7926 0.7732
-1.250 0.0656 0.02012 0.01207 -0.0356 0.7871 0.7755
-1.000 0.0897 0.02002 0.01187 -0.0354 0.7826 0.7775
-0.750 0.1172 0.01989 0.01163 -0.0357 0.7790 0.7798
-0.500 0.1473 0.01973 0.01136 -0.0366 0.7761 0.7819
-0.250 0.1643 0.01974 0.01132 -0.0353 0.7702 0.7842
0.000 0.1892 0.01973 0.01125 -0.0352 0.7661 0.7859
0.250 0.2179 0.01968 0.01116 -0.0356 0.7628 0.7874
0.500 0.2487 0.01962 0.01103 -0.0364 0.7602 0.7888
0.750 0.2654 0.01978 0.01121 -0.0349 0.7544 0.7906
1.000 0.2902 0.01982 0.01123 -0.0347 0.7501 0.7923
1.250 0.3190 0.01980 0.01118 -0.0352 0.7467 0.7941
1.500 0.3488 0.01979 0.01113 -0.0358 0.7437 0.7962
1.750 0.3645 0.02000 0.01138 -0.0342 0.7371 0.7989
2.000 0.3919 0.02000 0.01137 -0.0345 0.7325 0.8007
2.250 0.4231 0.01985 0.01120 -0.0350 0.7262 0.8020
2.500 0.4502 0.01959 0.01092 -0.0346 0.7147 0.8035
2.750 0.4750 0.01934 0.01067 -0.0337 0.7016 0.8052
3.000 0.5018 0.01915 0.01047 -0.0333 0.6909 0.8071
3.250 0.5301 0.01901 0.01033 -0.0333 0.6824 0.8093
3.500 0.5517 0.01900 0.01039 -0.0322 0.6727 0.8121
3.750 0.5831 0.01882 0.01018 -0.0328 0.6643 0.8145
4.000 0.6027 0.01883 0.01027 -0.0314 0.6529 0.8171
4.250 0.6254 0.01877 0.01029 -0.0304 0.6418 0.8192
4.500 0.6501 0.01866 0.01021 -0.0297 0.6300 0.8215
4.750 0.6736 0.01855 0.01015 -0.0288 0.6167 0.8242
5.000 0.6938 0.01851 0.01018 -0.0274 0.6012 0.8272
5.250 0.7109 0.01853 0.01029 -0.0256 0.5829 0.8308
5.500 0.7262 0.01855 0.01039 -0.0233 0.5603 0.8343
5.750 0.7414 0.01856 0.01045 -0.0209 0.5306 0.8382
6.000 0.7593 0.01852 0.01031 -0.0189 0.4850 0.8426
6.250 0.7736 0.01870 0.01011 -0.0163 0.4251 0.8474
6.500 0.7794 0.01924 0.01035 -0.0125 0.3761 0.8522
6.750 0.7854 0.01993 0.01082 -0.0092 0.3385 0.8581
7.000 0.7937 0.02066 0.01140 -0.0064 0.3083 0.8646
7.250 0.8041 0.02135 0.01203 -0.0040 0.2837 0.8717
7.500 0.8159 0.02205 0.01265 -0.0020 0.2640 0.8804
7.750 0.8296 0.02271 0.01330 -0.0003 0.2475 0.8910
8.000 0.8461 0.02337 0.01396 0.0008 0.2326 0.9052
8.500 0.8930 0.02473 0.01542 -0.0001 0.2057 1.0000
8.750 0.9099 0.02549 0.01614 0.0006 0.1962 1.0000
9.000 0.9262 0.02630 0.01689 0.0014 0.1874 1.0000
9.250 0.9439 0.02706 0.01769 0.0021 0.1790 1.0000
9.500 0.9598 0.02792 0.01849 0.0030 0.1720 1.0000
9.750 0.9776 0.02871 0.01934 0.0037 0.1650 1.0000
10.000 0.9931 0.02959 0.02021 0.0045 0.1584 1.0000
10.250 1.0099 0.03048 0.02113 0.0053 0.1525 1.0000
10.500 1.0262 0.03137 0.02209 0.0060 0.1466 1.0000
10.750 1.0410 0.03237 0.02303 0.0069 0.1417 1.0000
11.000 1.0571 0.03331 0.02412 0.0076 0.1360 1.0000
11.250 1.0714 0.03431 0.02518 0.0085 0.1311 1.0000
11.500 1.0861 0.03541 0.02625 0.0093 0.1269 1.0000
11.750 1.1005 0.03649 0.02752 0.0100 0.1221 1.0000
12.000 1.1133 0.03764 0.02874 0.0109 0.1177 1.0000
12.250 1.1261 0.03883 0.02991 0.0117 0.1141 1.0000
12.500 1.1389 0.04013 0.03141 0.0125 0.1101 1.0000
12.750 1.1498 0.04147 0.03291 0.0133 0.1062 1.0000
13.000 1.1598 0.04283 0.03432 0.0141 0.1028 1.0000
13.250 1.1707 0.04427 0.03578 0.0148 0.0998 1.0000
13.500 1.1788 0.04597 0.03774 0.0156 0.0964 1.0000
13.750 1.1861 0.04767 0.03959 0.0163 0.0932 1.0000
14.000 1.1929 0.04934 0.04134 0.0170 0.0905 1.0000
14.250 1.2015 0.05097 0.04298 0.0175 0.0880 1.0000
14.500 1.2037 0.05329 0.04558 0.0181 0.0855 1.0000
14.750 1.2055 0.05567 0.04820 0.0186 0.0830 1.0000
15.000 1.2069 0.05802 0.05071 0.0190 0.0806 1.0000
15.250 1.2088 0.06029 0.05306 0.0192 0.0784 1.0000
15.500 1.2134 0.06242 0.05521 0.0193 0.0765 1.0000
15.750 1.2074 0.06581 0.05886 0.0192 0.0747 1.0000
16.000 1.1986 0.06970 0.06303 0.0188 0.0730 1.0000
16.250 1.1889 0.07380 0.06737 0.0181 0.0713 1.0000
16.500 1.1789 0.07807 0.07184 0.0171 0.0697 1.0000
16.750 1.1703 0.08228 0.07619 0.0158 0.0682 1.0000
17.000 1.1665 0.08590 0.07989 0.0146 0.0667 1.0000
17.250 1.1683 0.08879 0.08279 0.0136 0.0650 1.0000
17.500 1.1400 0.09672 0.09104 0.0100 0.0643 1.0000
17.750 1.1052 0.10651 0.10109 0.0048 0.0639 1.0000
18.000 1.0499 0.12147 0.11632 -0.0040 0.0641 1.0000
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Polar data table (+)
Polar graphs
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