NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il) Reynolds number: 200,000 Max Cl/Cd: 61.73 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls417-il-200000-n5.txt Download as CSV file: xf-ls417-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0417 (GA(W)-1) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7346 0.08198 0.07668 -0.0772 1.0000 0.0220
-15.250 -0.7717 0.06906 0.06337 -0.0850 1.0000 0.0221
-15.000 -0.7815 0.06464 0.05882 -0.0871 1.0000 0.0222
-14.750 -0.7891 0.06085 0.05491 -0.0886 1.0000 0.0223
-14.500 -0.7945 0.05754 0.05149 -0.0897 1.0000 0.0224
-14.250 -0.7988 0.05459 0.04845 -0.0903 1.0000 0.0226
-14.000 -0.8027 0.05194 0.04570 -0.0905 1.0000 0.0228
-13.750 -0.8076 0.04963 0.04329 -0.0900 1.0000 0.0229
-13.500 -0.8097 0.04743 0.04099 -0.0897 0.9969 0.0231
-13.250 -0.7999 0.04488 0.03827 -0.0916 0.9887 0.0234
-13.000 -0.7878 0.04248 0.03570 -0.0934 0.9812 0.0237
-12.750 -0.7751 0.04032 0.03336 -0.0947 0.9725 0.0240
-12.500 -0.7599 0.03831 0.03117 -0.0958 0.9650 0.0243
-12.250 -0.7447 0.03655 0.02923 -0.0964 0.9563 0.0246
-12.000 -0.7284 0.03494 0.02745 -0.0968 0.9487 0.0249
-11.750 -0.7126 0.03353 0.02586 -0.0967 0.9406 0.0253
-11.500 -0.6949 0.03223 0.02443 -0.0967 0.9344 0.0256
-11.250 -0.6791 0.03110 0.02329 -0.0962 0.9267 0.0259
-11.000 -0.6624 0.03004 0.02218 -0.0958 0.9202 0.0263
-10.750 -0.6460 0.02904 0.02112 -0.0952 0.9141 0.0267
-10.500 -0.6303 0.02810 0.02012 -0.0945 0.9070 0.0272
-10.250 -0.6142 0.02719 0.01913 -0.0936 0.9011 0.0277
-10.000 -0.5985 0.02637 0.01821 -0.0927 0.8959 0.0284
-9.750 -0.5816 0.02560 0.01735 -0.0920 0.8901 0.0292
-9.500 -0.5642 0.02475 0.01650 -0.0915 0.8850 0.0299
-9.250 -0.5450 0.02399 0.01570 -0.0912 0.8806 0.0307
-9.000 -0.5248 0.02327 0.01492 -0.0910 0.8766 0.0317
-8.750 -0.5043 0.02257 0.01417 -0.0907 0.8714 0.0327
-8.500 -0.4834 0.02188 0.01344 -0.0906 0.8668 0.0337
-8.250 -0.4612 0.02125 0.01278 -0.0905 0.8630 0.0348
-8.000 -0.4380 0.02066 0.01214 -0.0905 0.8598 0.0364
-7.750 -0.4141 0.02011 0.01155 -0.0905 0.8568 0.0382
-7.500 -0.3898 0.01963 0.01107 -0.0907 0.8530 0.0409
-7.250 -0.3649 0.01915 0.01059 -0.0909 0.8493 0.0444
-7.000 -0.3395 0.01867 0.01010 -0.0911 0.8460 0.0493
-6.750 -0.3136 0.01817 0.00958 -0.0914 0.8429 0.0556
-6.500 -0.2871 0.01767 0.00908 -0.0918 0.8401 0.0639
-6.250 -0.2599 0.01717 0.00863 -0.0924 0.8376 0.0760
-6.000 -0.2332 0.01672 0.00830 -0.0930 0.8342 0.0950
-5.750 -0.2056 0.01628 0.00798 -0.0937 0.8310 0.1201
-5.500 -0.1775 0.01579 0.00764 -0.0945 0.8280 0.1511
-5.250 -0.1486 0.01519 0.00728 -0.0957 0.8253 0.2020
-5.000 -0.1184 0.01441 0.00689 -0.0975 0.8228 0.2837
-4.750 -0.0866 0.01369 0.00656 -0.0994 0.8207 0.3712
-4.500 -0.0547 0.01313 0.00638 -0.1009 0.8187 0.4564
-4.250 -0.0253 0.01299 0.00656 -0.1013 0.8163 0.5239
-4.000 0.0029 0.01313 0.00685 -0.1012 0.8130 0.5707
-3.750 0.0323 0.01329 0.00703 -0.1014 0.8101 0.5994
-3.500 0.0624 0.01344 0.00714 -0.1019 0.8075 0.6189
-3.250 0.0918 0.01361 0.00728 -0.1020 0.8050 0.6339
-3.000 0.1219 0.01375 0.00737 -0.1023 0.8025 0.6470
-2.750 0.1518 0.01393 0.00749 -0.1025 0.8002 0.6593
-2.500 0.1800 0.01416 0.00770 -0.1022 0.7982 0.6687
-2.250 0.2088 0.01435 0.00788 -0.1023 0.7956 0.6774
-2.000 0.2390 0.01444 0.00793 -0.1030 0.7922 0.6834
-1.750 0.2663 0.01457 0.00807 -0.1028 0.7891 0.6866
-1.500 0.2949 0.01467 0.00816 -0.1029 0.7862 0.6904
-1.250 0.3250 0.01472 0.00818 -0.1033 0.7835 0.6950
-1.000 0.3580 0.01473 0.00811 -0.1046 0.7812 0.7013
-0.750 0.3856 0.01483 0.00823 -0.1042 0.7790 0.7047
-0.500 0.4131 0.01498 0.00840 -0.1040 0.7762 0.7084
-0.250 0.4404 0.01513 0.00858 -0.1040 0.7720 0.7122
0.000 0.4703 0.01514 0.00858 -0.1045 0.7672 0.7163
0.250 0.5033 0.01503 0.00841 -0.1057 0.7627 0.7205
0.500 0.5327 0.01497 0.00834 -0.1057 0.7589 0.7225
0.750 0.5590 0.01502 0.00843 -0.1054 0.7521 0.7245
1.000 0.5875 0.01488 0.00828 -0.1052 0.7435 0.7268
1.250 0.6168 0.01473 0.00811 -0.1053 0.7346 0.7292
1.500 0.6454 0.01464 0.00802 -0.1054 0.7250 0.7319
1.750 0.6762 0.01451 0.00787 -0.1059 0.7169 0.7347
2.000 0.7057 0.01446 0.00783 -0.1064 0.7066 0.7374
2.250 0.7358 0.01438 0.00773 -0.1068 0.6985 0.7394
2.500 0.7621 0.01440 0.00781 -0.1064 0.6879 0.7411
2.750 0.7892 0.01437 0.00781 -0.1062 0.6754 0.7429
3.000 0.8161 0.01434 0.00776 -0.1059 0.6586 0.7447
3.250 0.8427 0.01433 0.00773 -0.1055 0.6371 0.7466
3.500 0.8692 0.01435 0.00767 -0.1052 0.6090 0.7487
3.750 0.8938 0.01448 0.00760 -0.1045 0.5644 0.7509
4.000 0.9134 0.01492 0.00768 -0.1030 0.5062 0.7537
4.250 0.9291 0.01562 0.00803 -0.1010 0.4488 0.7564
4.500 0.9415 0.01637 0.00851 -0.0984 0.4006 0.7581
4.750 0.9540 0.01710 0.00904 -0.0959 0.3574 0.7598
5.000 0.9664 0.01783 0.00958 -0.0934 0.3205 0.7618
5.250 0.9787 0.01855 0.01015 -0.0910 0.2897 0.7639
5.500 0.9902 0.01918 0.01067 -0.0885 0.2639 0.7663
5.750 1.0023 0.01986 0.01124 -0.0862 0.2414 0.7688
6.000 1.0175 0.02060 0.01187 -0.0846 0.2213 0.7714
6.250 1.0339 0.02133 0.01253 -0.0832 0.2037 0.7739
6.500 1.0493 0.02203 0.01320 -0.0816 0.1888 0.7759
6.750 1.0650 0.02275 0.01389 -0.0801 0.1762 0.7783
7.000 1.0806 0.02352 0.01463 -0.0787 0.1657 0.7809
7.250 1.0968 0.02429 0.01538 -0.0774 0.1562 0.7836
7.500 1.1138 0.02506 0.01614 -0.0764 0.1483 0.7864
7.750 1.1302 0.02591 0.01695 -0.0753 0.1409 0.7893
8.000 1.1471 0.02669 0.01777 -0.0743 0.1348 0.7917
8.250 1.1624 0.02751 0.01861 -0.0730 0.1292 0.7940
8.500 1.1772 0.02841 0.01952 -0.0717 0.1247 0.7965
8.750 1.1938 0.02922 0.02039 -0.0706 0.1199 0.7993
9.000 1.2086 0.03018 0.02135 -0.0695 0.1158 0.8024
9.250 1.2242 0.03114 0.02233 -0.0686 0.1122 0.8058
9.500 1.2402 0.03204 0.02329 -0.0676 0.1086 0.8090
9.750 1.2538 0.03303 0.02433 -0.0663 0.1054 0.8118
10.000 1.2666 0.03413 0.02544 -0.0650 0.1025 0.8149
10.250 1.2822 0.03506 0.02646 -0.0641 0.0993 0.8182
10.500 1.2966 0.03613 0.02757 -0.0632 0.0963 0.8216
10.750 1.3094 0.03736 0.02880 -0.0622 0.0937 0.8251
11.000 1.3222 0.03846 0.02998 -0.0610 0.0914 0.8279
11.250 1.3355 0.03955 0.03117 -0.0600 0.0889 0.8312
11.500 1.3480 0.04075 0.03244 -0.0589 0.0867 0.8348
11.750 1.3589 0.04213 0.03384 -0.0579 0.0847 0.8388
12.000 1.3704 0.04347 0.03524 -0.0569 0.0829 0.8427
12.250 1.3820 0.04469 0.03658 -0.0558 0.0809 0.8465
12.500 1.3928 0.04605 0.03804 -0.0548 0.0789 0.8509
12.750 1.4029 0.04755 0.03959 -0.0539 0.0771 0.8555
13.000 1.4108 0.04923 0.04129 -0.0529 0.0756 0.8598
13.250 1.4210 0.05067 0.04286 -0.0519 0.0739 0.8641
13.500 1.4307 0.05223 0.04455 -0.0511 0.0721 0.8689
13.750 1.4394 0.05396 0.04636 -0.0504 0.0703 0.8740
14.000 1.4461 0.05577 0.04825 -0.0495 0.0689 0.8789
14.250 1.4518 0.05775 0.05027 -0.0486 0.0676 0.8846
14.500 1.4601 0.05959 0.05228 -0.0480 0.0659 0.8907
14.750 1.4658 0.06155 0.05437 -0.0472 0.0643 0.8972
15.000 1.4710 0.06368 0.05660 -0.0467 0.0629 0.9049
15.250 1.4736 0.06593 0.05894 -0.0459 0.0617 0.9143
15.500 1.4751 0.06822 0.06131 -0.0450 0.0606 0.9281
16.000 1.4786 0.07299 0.06641 -0.0440 0.0579 1.0000
16.250 1.4818 0.07588 0.06939 -0.0443 0.0566 1.0000
16.500 1.4837 0.07898 0.07256 -0.0448 0.0556 1.0000
16.750 1.4842 0.08227 0.07589 -0.0454 0.0546 1.0000
17.000 1.4852 0.08560 0.07940 -0.0460 0.0533 1.0000
17.250 1.4851 0.08912 0.08307 -0.0468 0.0521 1.0000
17.500 1.4839 0.09283 0.08690 -0.0478 0.0511 1.0000
17.750 1.4818 0.09673 0.09089 -0.0490 0.0502 1.0000
18.000 1.4791 0.10075 0.09499 -0.0504 0.0494 1.0000
18.250 1.4760 0.10484 0.09915 -0.0519 0.0487 1.0000
18.500 1.4711 0.10937 0.10388 -0.0536 0.0478 1.0000
18.750 1.4654 0.11409 0.10876 -0.0557 0.0470 1.0000
19.000 1.4592 0.11896 0.11378 -0.0580 0.0462 1.0000
19.250 1.4529 0.12393 0.11887 -0.0605 0.0454 1.0000
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