NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Reynolds number: 200,000 Max Cl/Cd: 65.32 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf416-il-200000.txt Download as CSV file: xf-nlf416-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3964 0.11265 0.10901 -0.0384 1.0000 0.0690
-11.250 -0.3998 0.07705 0.07371 -0.0564 1.0000 0.0479
-11.000 -0.4788 0.05968 0.05612 -0.0653 1.0000 0.0418
-10.750 -0.4390 0.09342 0.08996 -0.0486 1.0000 0.0763
-10.500 -0.4373 0.09020 0.08677 -0.0486 1.0000 0.0772
-10.250 -0.4434 0.08555 0.08216 -0.0502 1.0000 0.0783
-10.000 -0.4680 0.07756 0.07422 -0.0551 1.0000 0.0798
-9.750 -0.7563 0.04691 0.04149 -0.0546 1.0000 0.0329
-9.500 -0.7479 0.04335 0.03791 -0.0531 1.0000 0.0322
-9.250 -0.7463 0.04041 0.03481 -0.0511 1.0000 0.0317
-9.000 -0.7426 0.03776 0.03194 -0.0491 1.0000 0.0312
-8.750 -0.7363 0.03530 0.02922 -0.0472 1.0000 0.0307
-8.500 -0.7273 0.03302 0.02667 -0.0454 1.0000 0.0303
-8.250 -0.7024 0.03068 0.02401 -0.0462 0.9977 0.0303
-8.000 -0.6629 0.02854 0.02159 -0.0491 0.9933 0.0306
-7.750 -0.6242 0.02678 0.01962 -0.0516 0.9877 0.0313
-7.500 -0.5825 0.02531 0.01798 -0.0544 0.9833 0.0323
-7.250 -0.5473 0.02378 0.01647 -0.0562 0.9763 0.0340
-7.000 -0.5055 0.02267 0.01539 -0.0594 0.9714 0.0364
-6.750 -0.4695 0.02160 0.01425 -0.0611 0.9620 0.0388
-6.500 -0.4346 0.02009 0.01287 -0.0633 0.9528 0.0420
-6.250 -0.3933 0.01872 0.01150 -0.0667 0.9458 0.0477
-6.000 -0.3579 0.01739 0.01026 -0.0690 0.9342 0.0609
-5.750 -0.3217 0.01522 0.00867 -0.0724 0.9233 0.1424
-5.500 -0.2768 0.01369 0.00768 -0.0773 0.9154 0.2470
-5.250 -0.2332 0.01250 0.00693 -0.0815 0.9014 0.3494
-5.000 -0.1878 0.01155 0.00644 -0.0856 0.8854 0.4563
-4.750 -0.1446 0.01143 0.00667 -0.0878 0.8658 0.5398
-4.500 -0.1061 0.01194 0.00716 -0.0886 0.8393 0.5816
-4.250 -0.0696 0.01246 0.00744 -0.0894 0.8123 0.6054
-4.000 -0.0389 0.01305 0.00781 -0.0890 0.7854 0.6214
-3.750 -0.0103 0.01363 0.00815 -0.0883 0.7618 0.6349
-3.500 0.0164 0.01419 0.00851 -0.0873 0.7406 0.6465
-3.250 0.0410 0.01479 0.00897 -0.0856 0.7227 0.6531
-3.000 0.0686 0.01515 0.00913 -0.0853 0.7072 0.6651
-2.750 0.0920 0.01572 0.00958 -0.0832 0.6942 0.6694
-2.500 0.1172 0.01610 0.00985 -0.0820 0.6812 0.6778
-2.250 0.1420 0.01641 0.01007 -0.0809 0.6697 0.6849
-2.000 0.1665 0.01681 0.01034 -0.0794 0.6605 0.6907
-1.750 0.1932 0.01692 0.01036 -0.0792 0.6504 0.6999
-1.500 0.2167 0.01725 0.01059 -0.0774 0.6425 0.7044
-1.250 0.2455 0.01729 0.01054 -0.0780 0.6335 0.7148
-1.000 0.2680 0.01755 0.01072 -0.0760 0.6269 0.7183
-0.750 0.2920 0.01769 0.01085 -0.0749 0.6192 0.7244
-0.500 0.3204 0.01771 0.01076 -0.0753 0.6123 0.7322
-0.250 0.3433 0.01786 0.01087 -0.0737 0.6062 0.7364
0.000 0.3699 0.01791 0.01089 -0.0736 0.5994 0.7431
0.250 0.3974 0.01793 0.01082 -0.0736 0.5937 0.7489
0.500 0.4205 0.01801 0.01090 -0.0723 0.5879 0.7531
0.750 0.4479 0.01804 0.01090 -0.0724 0.5816 0.7592
1.000 0.4769 0.01806 0.01082 -0.0729 0.5764 0.7644
1.250 0.4996 0.01810 0.01088 -0.0716 0.5708 0.7682
1.500 0.5257 0.01812 0.01090 -0.0714 0.5649 0.7728
1.750 0.5591 0.01819 0.01087 -0.0731 0.5596 0.7781
2.000 0.5826 0.01817 0.01088 -0.0722 0.5542 0.7811
2.250 0.6070 0.01817 0.01091 -0.0715 0.5484 0.7843
2.500 0.6350 0.01822 0.01089 -0.0716 0.5431 0.7878
2.750 0.6643 0.01830 0.01098 -0.0724 0.5376 0.7914
3.000 0.6957 0.01835 0.01103 -0.0737 0.5312 0.7948
3.250 0.7208 0.01833 0.01098 -0.0731 0.5261 0.7970
3.500 0.7460 0.01838 0.01108 -0.0727 0.5204 0.7995
3.750 0.7723 0.01841 0.01115 -0.0726 0.5141 0.8021
4.000 0.8021 0.01848 0.01115 -0.0732 0.5086 0.8047
4.250 0.8307 0.01858 0.01132 -0.0738 0.5023 0.8073
4.500 0.8611 0.01864 0.01139 -0.0748 0.4955 0.8095
4.750 0.8910 0.01874 0.01140 -0.0754 0.4900 0.8114
5.000 0.9137 0.01872 0.01155 -0.0745 0.4828 0.8132
5.250 0.9411 0.01874 0.01155 -0.0746 0.4762 0.8148
5.500 0.9676 0.01883 0.01168 -0.0746 0.4695 0.8167
5.750 0.9940 0.01885 0.01176 -0.0745 0.4617 0.8187
6.000 1.0233 0.01894 0.01182 -0.0751 0.4550 0.8201
6.250 1.0491 0.01898 0.01197 -0.0751 0.4464 0.8219
6.500 1.0792 0.01908 0.01200 -0.0758 0.4394 0.8237
6.750 1.1046 0.01912 0.01219 -0.0757 0.4299 0.8251
7.000 1.1334 0.01920 0.01223 -0.0762 0.4221 0.8262
7.250 1.1560 0.01919 0.01236 -0.0755 0.4122 0.8274
7.500 1.1800 0.01924 0.01244 -0.0749 0.4032 0.8290
7.750 1.2032 0.01927 0.01252 -0.0742 0.3931 0.8307
8.000 1.2260 0.01936 0.01272 -0.0736 0.3820 0.8321
8.250 1.2493 0.01948 0.01285 -0.0731 0.3710 0.8334
8.500 1.2721 0.01963 0.01300 -0.0725 0.3595 0.8348
8.750 1.2934 0.01984 0.01329 -0.0717 0.3463 0.8363
9.000 1.3143 0.02012 0.01361 -0.0709 0.3330 0.8379
9.250 1.3344 0.02048 0.01399 -0.0700 0.3195 0.8398
9.500 1.3534 0.02093 0.01443 -0.0690 0.3061 0.8416
9.750 1.3691 0.02139 0.01489 -0.0674 0.2934 0.8431
10.000 1.3832 0.02193 0.01540 -0.0655 0.2809 0.8447
10.250 1.3951 0.02246 0.01598 -0.0633 0.2684 0.8465
10.500 1.4067 0.02309 0.01666 -0.0612 0.2562 0.8484
10.750 1.4176 0.02384 0.01744 -0.0592 0.2448 0.8505
11.000 1.4268 0.02473 0.01830 -0.0571 0.2339 0.8526
11.250 1.4360 0.02564 0.01926 -0.0551 0.2228 0.8548
11.500 1.4444 0.02665 0.02034 -0.0532 0.2123 0.8571
11.750 1.4486 0.02782 0.02150 -0.0509 0.2032 0.8597
12.000 1.4536 0.02904 0.02280 -0.0489 0.1937 0.8627
12.250 1.4580 0.03046 0.02429 -0.0472 0.1848 0.8658
12.500 1.4599 0.03218 0.02600 -0.0457 0.1766 0.8687
12.750 1.4642 0.03389 0.02784 -0.0446 0.1679 0.8717
13.000 1.4634 0.03598 0.02988 -0.0433 0.1608 0.8748
13.250 1.4653 0.03800 0.03207 -0.0425 0.1529 0.8784
13.500 1.4639 0.04047 0.03451 -0.0418 0.1462 0.8824
13.750 1.4649 0.04293 0.03713 -0.0417 0.1389 0.8867
14.000 1.4617 0.04570 0.03986 -0.0412 0.1329 0.8912
14.250 1.4611 0.04845 0.04280 -0.0413 0.1262 0.8970
14.500 1.4572 0.05154 0.04587 -0.0413 0.1206 0.9034
14.750 1.4550 0.05448 0.04901 -0.0415 0.1149 0.9133
15.000 1.4489 0.05750 0.05213 -0.0413 0.1101 0.9427
15.250 1.4459 0.06088 0.05556 -0.0420 0.1050 1.0000
15.500 1.4446 0.06459 0.05939 -0.0434 0.0997 1.0000
15.750 1.4422 0.06828 0.06298 -0.0445 0.0949 1.0000
16.000 1.4405 0.07226 0.06716 -0.0461 0.0903 1.0000
16.250 1.4374 0.07634 0.07130 -0.0477 0.0860 1.0000
16.500 1.4351 0.08030 0.07526 -0.0491 0.0819 1.0000
16.750 1.4318 0.08465 0.07976 -0.0510 0.0777 1.0000
17.000 1.4282 0.08893 0.08404 -0.0527 0.0740 1.0000
17.250 1.4252 0.09320 0.08839 -0.0544 0.0703 1.0000
17.500 1.4208 0.09789 0.09320 -0.0566 0.0667 1.0000
17.750 1.4180 0.10210 0.09736 -0.0584 0.0633 1.0000
18.000 1.4131 0.10691 0.10231 -0.0606 0.0601 1.0000
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Polar data table (+)
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