NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Reynolds number: 100,000 Max Cl/Cd: 48.29 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf416-il-100000-n5.txt Download as CSV file: xf-nlf416-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY NLF(1)-0416 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5542 0.08497 0.07921 -0.0583 1.0000 0.0230
-12.500 -0.5774 0.07766 0.07179 -0.0627 1.0000 0.0229
-12.250 -0.6002 0.07139 0.06537 -0.0661 1.0000 0.0228
-12.000 -0.6200 0.06628 0.06012 -0.0683 1.0000 0.0227
-11.750 -0.6379 0.06196 0.05564 -0.0694 1.0000 0.0226
-11.500 -0.6553 0.05811 0.05162 -0.0697 1.0000 0.0226
-11.250 -0.6714 0.05472 0.04805 -0.0691 1.0000 0.0226
-11.000 -0.6855 0.05182 0.04497 -0.0679 1.0000 0.0227
-10.750 -0.6991 0.04927 0.04224 -0.0660 1.0000 0.0228
-10.500 -0.7122 0.04712 0.03991 -0.0633 1.0000 0.0229
-10.250 -0.7241 0.04518 0.03779 -0.0603 1.0000 0.0230
-10.000 -0.7247 0.04340 0.03596 -0.0584 1.0000 0.0235
-9.750 -0.7224 0.04180 0.03431 -0.0565 1.0000 0.0239
-9.500 -0.7185 0.04027 0.03268 -0.0545 1.0000 0.0244
-9.250 -0.7132 0.03885 0.03116 -0.0526 1.0000 0.0254
-9.000 -0.7062 0.03726 0.02940 -0.0507 1.0000 0.0260
-8.750 -0.6971 0.03573 0.02768 -0.0488 1.0000 0.0266
-8.500 -0.6866 0.03427 0.02603 -0.0468 1.0000 0.0272
-8.250 -0.6640 0.03269 0.02436 -0.0469 0.9974 0.0279
-8.000 -0.6295 0.03118 0.02281 -0.0493 0.9911 0.0289
-7.750 -0.5947 0.02977 0.02133 -0.0517 0.9841 0.0303
-7.500 -0.5628 0.02842 0.01987 -0.0534 0.9752 0.0322
-7.250 -0.5321 0.02713 0.01857 -0.0552 0.9649 0.0347
-7.000 -0.5010 0.02599 0.01735 -0.0568 0.9538 0.0383
-6.750 -0.4705 0.02473 0.01610 -0.0585 0.9421 0.0424
-6.500 -0.4382 0.02348 0.01481 -0.0604 0.9308 0.0485
-6.250 -0.4083 0.02231 0.01367 -0.0617 0.9171 0.0600
-6.000 -0.3776 0.02107 0.01260 -0.0631 0.9032 0.0851
-5.750 -0.3451 0.01981 0.01169 -0.0652 0.8892 0.1368
-5.500 -0.3096 0.01866 0.01090 -0.0678 0.8753 0.2085
-5.250 -0.2728 0.01755 0.01020 -0.0706 0.8601 0.2947
-5.000 -0.2359 0.01665 0.00968 -0.0731 0.8434 0.3839
-4.750 -0.2002 0.01628 0.00954 -0.0744 0.8251 0.4556
-4.500 -0.1673 0.01650 0.00989 -0.0740 0.8060 0.5076
-4.250 -0.1356 0.01706 0.01042 -0.0732 0.7868 0.5421
-4.000 -0.1023 0.01747 0.01064 -0.0733 0.7676 0.5704
-3.750 -0.0703 0.01787 0.01081 -0.0734 0.7491 0.5911
-3.500 -0.0389 0.01818 0.01088 -0.0737 0.7317 0.6093
-3.250 -0.0090 0.01849 0.01098 -0.0737 0.7157 0.6237
-3.000 0.0202 0.01877 0.01106 -0.0736 0.7014 0.6367
-2.750 0.0497 0.01897 0.01104 -0.0739 0.6884 0.6496
-2.500 0.0761 0.01933 0.01125 -0.0728 0.6768 0.6567
-2.250 0.1041 0.01945 0.01121 -0.0728 0.6650 0.6671
-2.000 0.1297 0.01971 0.01134 -0.0718 0.6549 0.6739
-1.750 0.1582 0.01979 0.01126 -0.0720 0.6458 0.6833
-1.500 0.1829 0.01999 0.01137 -0.0709 0.6368 0.6889
-1.250 0.2125 0.02001 0.01122 -0.0716 0.6285 0.6983
-1.000 0.2365 0.02017 0.01132 -0.0703 0.6205 0.7025
-0.750 0.2627 0.02027 0.01132 -0.0699 0.6130 0.7086
-0.500 0.2915 0.02029 0.01122 -0.0704 0.6062 0.7156
-0.250 0.3157 0.02039 0.01128 -0.0694 0.5989 0.7197
0.000 0.3429 0.02046 0.01124 -0.0693 0.5929 0.7252
0.250 0.3716 0.02047 0.01119 -0.0699 0.5859 0.7314
0.500 0.3962 0.02055 0.01123 -0.0691 0.5797 0.7348
0.750 0.4230 0.02062 0.01121 -0.0688 0.5743 0.7389
1.000 0.4508 0.02066 0.01124 -0.0692 0.5676 0.7438
1.250 0.4793 0.02071 0.01123 -0.0697 0.5617 0.7479
1.500 0.5051 0.02078 0.01125 -0.0692 0.5566 0.7508
1.750 0.5305 0.02085 0.01136 -0.0689 0.5502 0.7541
2.000 0.5585 0.02092 0.01139 -0.0692 0.5445 0.7577
2.250 0.5888 0.02102 0.01142 -0.0701 0.5393 0.7616
2.500 0.6146 0.02110 0.01155 -0.0699 0.5329 0.7643
2.750 0.6405 0.02119 0.01163 -0.0696 0.5274 0.7669
3.000 0.6676 0.02129 0.01172 -0.0696 0.5222 0.7694
3.250 0.6936 0.02141 0.01190 -0.0696 0.5156 0.7723
3.500 0.7224 0.02153 0.01199 -0.0701 0.5099 0.7752
3.750 0.7517 0.02167 0.01214 -0.0708 0.5042 0.7779
4.000 0.7772 0.02180 0.01235 -0.0706 0.4974 0.7800
4.250 0.8038 0.02190 0.01244 -0.0705 0.4918 0.7820
4.500 0.8291 0.02206 0.01268 -0.0703 0.4854 0.7840
4.750 0.8551 0.02220 0.01289 -0.0702 0.4786 0.7862
5.250 0.9081 0.02253 0.01334 -0.0703 0.4652 0.7905
5.500 0.9362 0.02267 0.01348 -0.0707 0.4585 0.7923
5.750 0.9628 0.02288 0.01378 -0.0709 0.4511 0.7944
6.000 0.9871 0.02302 0.01401 -0.0704 0.4436 0.7962
6.250 1.0115 0.02318 0.01423 -0.0700 0.4364 0.7979
6.500 1.0353 0.02336 0.01453 -0.0696 0.4279 0.7996
6.750 1.0602 0.02353 0.01476 -0.0693 0.4201 0.8012
7.000 1.0837 0.02373 0.01507 -0.0689 0.4108 0.8029
7.250 1.1075 0.02394 0.01538 -0.0685 0.4020 0.8049
7.500 1.1314 0.02413 0.01565 -0.0681 0.3927 0.8071
7.750 1.1543 0.02443 0.01608 -0.0677 0.3823 0.8093
8.000 1.1769 0.02465 0.01635 -0.0671 0.3727 0.8111
8.250 1.1969 0.02492 0.01675 -0.0661 0.3617 0.8127
8.500 1.2164 0.02526 0.01719 -0.0651 0.3504 0.8144
8.750 1.2357 0.02560 0.01758 -0.0640 0.3394 0.8163
9.000 1.2541 0.02597 0.01798 -0.0628 0.3282 0.8183
9.250 1.2708 0.02648 0.01859 -0.0616 0.3158 0.8205
9.500 1.2865 0.02704 0.01921 -0.0602 0.3038 0.8229
9.750 1.3000 0.02766 0.01986 -0.0585 0.2924 0.8256
10.000 1.3101 0.02831 0.02052 -0.0562 0.2816 0.8280
10.250 1.3197 0.02911 0.02143 -0.0541 0.2702 0.8306
10.500 1.3289 0.03001 0.02240 -0.0521 0.2595 0.8332
10.750 1.3368 0.03103 0.02343 -0.0502 0.2496 0.8359
11.000 1.3438 0.03221 0.02470 -0.0485 0.2390 0.8388
11.500 1.3530 0.03495 0.02753 -0.0450 0.2206 0.8444
11.750 1.3562 0.03655 0.02929 -0.0435 0.2114 0.8476
12.000 1.3581 0.03835 0.03112 -0.0422 0.2034 0.8511
12.250 1.3597 0.04036 0.03326 -0.0413 0.1949 0.8550
12.500 1.3599 0.04251 0.03547 -0.0404 0.1874 0.8590
12.750 1.3592 0.04487 0.03795 -0.0397 0.1797 0.8635
13.000 1.3586 0.04737 0.04052 -0.0393 0.1728 0.8686
13.250 1.3569 0.05011 0.04340 -0.0392 0.1656 0.8738
13.500 1.3548 0.05289 0.04625 -0.0390 0.1594 0.8796
13.750 1.3524 0.05592 0.04944 -0.0392 0.1526 0.8865
14.250 1.3450 0.06209 0.05585 -0.0395 0.1409 0.9092
14.500 1.3375 0.06524 0.05911 -0.0396 0.1358 1.0000
14.750 1.3362 0.06884 0.06278 -0.0407 0.1303 1.0000
15.000 1.3335 0.07275 0.06681 -0.0421 0.1246 1.0000
15.250 1.3317 0.07644 0.07046 -0.0434 0.1197 1.0000
15.500 1.3281 0.08072 0.07495 -0.0451 0.1143 1.0000
15.750 1.3244 0.08494 0.07923 -0.0468 0.1095 1.0000
16.000 1.3215 0.08911 0.08347 -0.0484 0.1050 1.0000
16.250 1.3163 0.09382 0.08833 -0.0505 0.1003 1.0000
16.500 1.3130 0.09817 0.09270 -0.0524 0.0962 1.0000
16.750 1.3084 0.10289 0.09754 -0.0546 0.0920 1.0000
17.000 1.3022 0.10797 0.10276 -0.0570 0.0879 1.0000
17.250 1.2993 0.11239 0.10718 -0.0592 0.0843 1.0000
17.500 1.2933 0.11760 0.11252 -0.0618 0.0807 1.0000
17.750 1.2863 0.12309 0.11815 -0.0648 0.0770 1.0000
18.000 1.2833 0.12771 0.12278 -0.0674 0.0737 1.0000
18.250 1.2776 0.13300 0.12818 -0.0704 0.0706 1.0000
18.500 1.2686 0.13910 0.13444 -0.0740 0.0674 1.0000
18.750 1.2650 0.14407 0.13945 -0.0771 0.0644 1.0000
19.000 1.2630 0.14870 0.14409 -0.0800 0.0617 1.0000
19.250 1.2507 0.15582 0.15142 -0.0845 0.0591 1.0000
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Polar data table (+)
Polar graphs
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