NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Reynolds number: 500,000 Max Cl/Cd: 77.12 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf414f-il-500000-n5.txt Download as CSV file: xf-nlf414f-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY NLF 0414F AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4818 0.11163 0.10851 -0.0326 0.7979 0.0098
-11.750 -0.4833 0.10682 0.10371 -0.0350 0.7976 0.0097
-11.500 -0.4873 0.10129 0.09819 -0.0379 0.7973 0.0096
-11.250 -0.4948 0.09480 0.09172 -0.0416 0.7971 0.0096
-11.000 -0.5067 0.08688 0.08382 -0.0467 0.7968 0.0095
-10.750 -0.5398 0.07085 0.06776 -0.0603 0.7965 0.0093
-10.500 -0.5755 0.06090 0.05763 -0.0666 0.7960 0.0092
-10.250 -0.6083 0.05330 0.04979 -0.0688 0.7956 0.0091
-10.000 -0.6461 0.04518 0.04128 -0.0687 0.7950 0.0091
-9.750 -0.6801 0.03511 0.03037 -0.0667 0.7944 0.0092
-9.500 -0.6759 0.03094 0.02569 -0.0657 0.7941 0.0094
-9.250 -0.6617 0.02837 0.02273 -0.0651 0.7937 0.0095
-9.000 -0.6429 0.02648 0.02055 -0.0649 0.7935 0.0096
-8.750 -0.6217 0.02501 0.01884 -0.0647 0.7932 0.0097
-8.500 -0.5989 0.02379 0.01742 -0.0646 0.7929 0.0098
-8.250 -0.5759 0.02255 0.01601 -0.0646 0.7926 0.0099
-8.000 -0.5524 0.02139 0.01474 -0.0646 0.7921 0.0100
-7.750 -0.5278 0.02056 0.01384 -0.0646 0.7916 0.0102
-7.500 -0.5024 0.01994 0.01317 -0.0648 0.7912 0.0105
-7.250 -0.4767 0.01939 0.01257 -0.0650 0.7908 0.0107
-7.000 -0.4509 0.01883 0.01196 -0.0651 0.7904 0.0110
-6.750 -0.4250 0.01826 0.01133 -0.0653 0.7900 0.0113
-6.500 -0.3992 0.01767 0.01068 -0.0654 0.7895 0.0115
-6.250 -0.3733 0.01711 0.01008 -0.0655 0.7891 0.0117
-6.000 -0.3473 0.01661 0.00954 -0.0656 0.7885 0.0120
-5.750 -0.3210 0.01616 0.00904 -0.0657 0.7878 0.0123
-5.500 -0.2944 0.01576 0.00860 -0.0659 0.7872 0.0125
-5.250 -0.2681 0.01531 0.00815 -0.0661 0.7867 0.0129
-5.000 -0.2412 0.01498 0.00781 -0.0664 0.7861 0.0135
-4.750 -0.2139 0.01470 0.00753 -0.0667 0.7856 0.0141
-4.500 -0.1865 0.01445 0.00727 -0.0670 0.7851 0.0148
-4.250 -0.1588 0.01422 0.00701 -0.0673 0.7844 0.0156
-4.000 -0.1313 0.01396 0.00676 -0.0676 0.7838 0.0169
-3.750 -0.1033 0.01378 0.00657 -0.0680 0.7832 0.0190
-3.500 -0.0755 0.01359 0.00640 -0.0683 0.7827 0.0226
-3.250 -0.0475 0.01340 0.00624 -0.0687 0.7822 0.0287
-3.000 -0.0195 0.01319 0.00608 -0.0690 0.7816 0.0399
-2.750 0.0084 0.01297 0.00595 -0.0694 0.7811 0.0602
-2.500 0.0357 0.01260 0.00581 -0.0698 0.7806 0.1175
-2.250 0.0613 0.01173 0.00558 -0.0705 0.7801 0.2907
-2.000 0.0855 0.01026 0.00521 -0.0713 0.7795 0.5831
-1.750 0.1109 0.01068 0.00611 -0.0703 0.7789 0.7048
-1.500 0.1404 0.01116 0.00652 -0.0704 0.7785 0.7366
-1.250 0.1674 0.01183 0.00722 -0.0697 0.7778 0.7544
-1.000 0.1969 0.01205 0.00742 -0.0704 0.7763 0.7600
-0.750 0.2256 0.01218 0.00756 -0.0709 0.7748 0.7614
-0.500 0.2543 0.01230 0.00767 -0.0713 0.7734 0.7628
-0.250 0.2829 0.01240 0.00778 -0.0717 0.7719 0.7648
0.000 0.3116 0.01250 0.00787 -0.0720 0.7706 0.7673
0.250 0.3407 0.01254 0.00791 -0.0725 0.7694 0.7695
0.500 0.3700 0.01255 0.00790 -0.0730 0.7683 0.7710
0.750 0.3996 0.01254 0.00786 -0.0735 0.7673 0.7723
1.000 0.4292 0.01251 0.00782 -0.0741 0.7663 0.7733
1.250 0.4582 0.01242 0.00774 -0.0744 0.7655 0.7741
1.500 0.4875 0.01228 0.00760 -0.0747 0.7645 0.7747
1.750 0.5171 0.01209 0.00740 -0.0750 0.7635 0.7751
2.000 0.5457 0.01207 0.00743 -0.0755 0.7592 0.7756
2.250 0.5751 0.01178 0.00717 -0.0758 0.7542 0.7763
2.500 0.6058 0.01116 0.00653 -0.0759 0.7503 0.7769
2.750 0.6354 0.01083 0.00623 -0.0762 0.7438 0.7773
3.000 0.6656 0.01041 0.00584 -0.0766 0.7356 0.7778
3.250 0.6949 0.01025 0.00574 -0.0772 0.7192 0.7782
3.500 0.7257 0.00941 0.00476 -0.0771 0.6760 0.7785
3.750 0.7446 0.00980 0.00449 -0.0754 0.5704 0.7792
4.000 0.7574 0.01106 0.00523 -0.0738 0.4682 0.7800
4.250 0.7693 0.01225 0.00599 -0.0722 0.3795 0.7807
4.500 0.7804 0.01339 0.00673 -0.0706 0.2980 0.7812
4.750 0.7902 0.01444 0.00745 -0.0687 0.2307 0.7817
5.000 0.8033 0.01531 0.00805 -0.0672 0.1797 0.7824
5.250 0.8216 0.01600 0.00856 -0.0663 0.1471 0.7830
5.500 0.8409 0.01660 0.00904 -0.0657 0.1224 0.7834
5.750 0.8608 0.01716 0.00949 -0.0650 0.1022 0.7837
6.000 0.8807 0.01770 0.00995 -0.0643 0.0853 0.7841
6.250 0.9006 0.01824 0.01041 -0.0636 0.0719 0.7846
6.500 0.9206 0.01877 0.01089 -0.0629 0.0615 0.7849
6.750 0.9406 0.01928 0.01136 -0.0623 0.0536 0.7851
7.000 0.9603 0.01982 0.01186 -0.0615 0.0475 0.7852
7.250 0.9804 0.02032 0.01236 -0.0609 0.0433 0.7854
7.500 0.9997 0.02089 0.01291 -0.0601 0.0399 0.7856
7.750 1.0198 0.02138 0.01343 -0.0595 0.0377 0.7857
8.000 1.0391 0.02194 0.01398 -0.0587 0.0355 0.7859
8.250 1.0575 0.02256 0.01461 -0.0578 0.0335 0.7860
8.500 1.0767 0.02312 0.01520 -0.0571 0.0322 0.7862
8.750 1.0955 0.02369 0.01581 -0.0563 0.0307 0.7863
9.000 1.1137 0.02432 0.01645 -0.0555 0.0294 0.7865
9.250 1.1309 0.02502 0.01716 -0.0545 0.0283 0.7868
9.500 1.1473 0.02578 0.01794 -0.0534 0.0274 0.7870
9.750 1.1650 0.02644 0.01866 -0.0526 0.0267 0.7872
10.000 1.1819 0.02716 0.01943 -0.0516 0.0260 0.7873
10.250 1.1984 0.02790 0.02023 -0.0506 0.0252 0.7874
10.500 1.2146 0.02867 0.02103 -0.0497 0.0245 0.7875
10.750 1.2303 0.02947 0.02186 -0.0487 0.0238 0.7876
11.000 1.2446 0.03038 0.02280 -0.0475 0.0231 0.7877
11.250 1.2574 0.03142 0.02388 -0.0462 0.0225 0.7878
11.500 1.2719 0.03231 0.02486 -0.0452 0.0222 0.7880
11.750 1.2858 0.03326 0.02588 -0.0440 0.0218 0.7881
12.000 1.2993 0.03425 0.02694 -0.0429 0.0214 0.7883
12.250 1.3125 0.03528 0.02804 -0.0418 0.0209 0.7884
12.500 1.3246 0.03637 0.02921 -0.0406 0.0206 0.7885
12.750 1.3365 0.03750 0.03041 -0.0395 0.0202 0.7887
13.000 1.3482 0.03867 0.03164 -0.0384 0.0198 0.7888
13.250 1.3594 0.03991 0.03295 -0.0373 0.0195 0.7890
13.500 1.3691 0.04127 0.03438 -0.0362 0.0191 0.7891
13.750 1.3771 0.04282 0.03598 -0.0349 0.0188 0.7893
14.000 1.3838 0.04452 0.03776 -0.0337 0.0184 0.7894
14.250 1.3933 0.04600 0.03935 -0.0327 0.0182 0.7895
14.500 1.4018 0.04760 0.04107 -0.0317 0.0180 0.7897
14.750 1.4090 0.04934 0.04292 -0.0307 0.0178 0.7898
15.000 1.4157 0.05117 0.04486 -0.0298 0.0175 0.7900
15.250 1.4215 0.05314 0.04695 -0.0289 0.0173 0.7901
15.500 1.4266 0.05522 0.04914 -0.0281 0.0171 0.7903
15.750 1.4309 0.05744 0.05147 -0.0274 0.0169 0.7904
16.000 1.4342 0.05980 0.05396 -0.0268 0.0167 0.7906
16.250 1.4368 0.06231 0.05658 -0.0263 0.0165 0.7907
16.500 1.4386 0.06498 0.05936 -0.0260 0.0163 0.7908
16.750 1.4396 0.06783 0.06233 -0.0258 0.0161 0.7910
17.000 1.4395 0.07089 0.06550 -0.0258 0.0160 0.7911
17.250 1.4383 0.07416 0.06889 -0.0259 0.0159 0.7913
17.500 1.4358 0.07769 0.07254 -0.0263 0.0157 0.7914
17.750 1.4321 0.08148 0.07646 -0.0269 0.0156 0.7915
18.000 1.4272 0.08557 0.08068 -0.0277 0.0155 0.7917
18.250 1.4208 0.08998 0.08521 -0.0288 0.0154 0.7918
18.500 1.4128 0.09472 0.09008 -0.0302 0.0153 0.7919
18.750 1.4032 0.09983 0.09532 -0.0319 0.0152 0.7921
19.000 1.3926 0.10527 0.10089 -0.0340 0.0151 0.7923
19.250 1.3799 0.11120 0.10696 -0.0365 0.0150 0.7924
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