NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Reynolds number: 500,000 Max Cl/Cd: 79.89 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls417mod-il-500000.txt Download as CSV file: xf-ls417mod-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0417MOD 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.8663 0.07588 0.07197 -0.0628 1.0000 0.0210
-15.750 -0.8934 0.06823 0.06407 -0.0673 1.0000 0.0210
-15.500 -0.9090 0.06290 0.05857 -0.0700 1.0000 0.0210
-15.250 -0.9201 0.05860 0.05412 -0.0717 1.0000 0.0211
-15.000 -0.9277 0.05494 0.05034 -0.0728 1.0000 0.0212
-14.750 -0.9325 0.05177 0.04705 -0.0734 1.0000 0.0213
-14.500 -0.9357 0.04889 0.04405 -0.0738 1.0000 0.0214
-14.250 -0.9353 0.04647 0.04154 -0.0738 1.0000 0.0215
-14.000 -0.9343 0.04417 0.03915 -0.0736 1.0000 0.0217
-13.750 -0.9326 0.04204 0.03691 -0.0732 1.0000 0.0219
-13.500 -0.9307 0.03999 0.03475 -0.0726 1.0000 0.0221
-13.250 -0.9280 0.03810 0.03275 -0.0717 1.0000 0.0223
-13.000 -0.9250 0.03637 0.03089 -0.0705 1.0000 0.0225
-12.750 -0.9222 0.03477 0.02918 -0.0689 1.0000 0.0227
-12.500 -0.9202 0.03335 0.02764 -0.0668 1.0000 0.0230
-12.250 -0.9201 0.03212 0.02629 -0.0642 1.0000 0.0232
-12.000 -0.9244 0.03113 0.02522 -0.0605 1.0000 0.0234
-11.750 -0.9402 0.03052 0.02454 -0.0546 1.0000 0.0235
-11.500 -0.9366 0.02962 0.02351 -0.0527 0.9987 0.0237
-11.250 -0.9087 0.02799 0.02189 -0.0537 0.9968 0.0243
-11.000 -0.8770 0.02692 0.02082 -0.0558 0.9943 0.0248
-10.750 -0.8441 0.02590 0.01977 -0.0582 0.9921 0.0254
-10.500 -0.8142 0.02489 0.01870 -0.0598 0.9879 0.0261
-10.250 -0.7823 0.02389 0.01760 -0.0616 0.9844 0.0267
-10.000 -0.7486 0.02300 0.01660 -0.0637 0.9818 0.0272
-9.750 -0.7166 0.02177 0.01541 -0.0653 0.9799 0.0279
-9.500 -0.6856 0.02091 0.01457 -0.0668 0.9747 0.0286
-9.250 -0.6519 0.02010 0.01375 -0.0687 0.9699 0.0294
-9.000 -0.6173 0.01932 0.01291 -0.0706 0.9660 0.0303
-8.750 -0.5883 0.01868 0.01220 -0.0714 0.9576 0.0310
-8.500 -0.5588 0.01773 0.01130 -0.0726 0.9516 0.0321
-8.250 -0.5314 0.01717 0.01073 -0.0730 0.9425 0.0332
-8.000 -0.5024 0.01663 0.01013 -0.0736 0.9347 0.0344
-7.750 -0.4775 0.01600 0.00947 -0.0736 0.9251 0.0354
-7.500 -0.4508 0.01543 0.00890 -0.0739 0.9170 0.0366
-7.250 -0.4242 0.01499 0.00843 -0.0740 0.9087 0.0380
-7.000 -0.3973 0.01451 0.00791 -0.0742 0.9005 0.0395
-6.750 -0.3696 0.01406 0.00746 -0.0745 0.8936 0.0416
-6.500 -0.3418 0.01367 0.00705 -0.0748 0.8860 0.0439
-6.250 -0.3135 0.01325 0.00662 -0.0751 0.8787 0.0469
-6.000 -0.2847 0.01284 0.00621 -0.0756 0.8717 0.0509
-5.750 -0.2557 0.01243 0.00583 -0.0761 0.8642 0.0579
-5.500 -0.2262 0.01191 0.00541 -0.0768 0.8573 0.0758
-5.250 -0.1960 0.01131 0.00503 -0.0778 0.8508 0.1186
-5.000 -0.1652 0.01075 0.00470 -0.0790 0.8434 0.1657
-4.750 -0.1335 0.01016 0.00436 -0.0804 0.8359 0.2282
-4.500 -0.1004 0.00952 0.00405 -0.0821 0.8285 0.3102
-4.250 -0.0664 0.00892 0.00376 -0.0840 0.8203 0.3893
-4.000 -0.0316 0.00836 0.00350 -0.0859 0.8119 0.4746
-3.750 0.0018 0.00805 0.00349 -0.0872 0.8029 0.5557
-3.500 0.0325 0.00806 0.00353 -0.0875 0.7914 0.5945
-3.250 0.0629 0.00814 0.00360 -0.0877 0.7811 0.6173
-3.000 0.0928 0.00827 0.00370 -0.0877 0.7690 0.6369
-2.750 0.1234 0.00844 0.00378 -0.0879 0.7556 0.6512
-2.500 0.1513 0.00857 0.00389 -0.0874 0.7386 0.6596
-2.250 0.1805 0.00871 0.00393 -0.0873 0.7159 0.6671
-2.000 0.2096 0.00887 0.00389 -0.0873 0.6768 0.6733
-1.750 0.2315 0.00943 0.00400 -0.0857 0.5615 0.6793
-1.500 0.2546 0.01017 0.00433 -0.0846 0.4822 0.6863
-1.250 0.2830 0.01055 0.00451 -0.0846 0.4535 0.6925
-1.000 0.3115 0.01076 0.00459 -0.0847 0.4356 0.6966
-0.750 0.3392 0.01094 0.00471 -0.0845 0.4220 0.6996
-0.500 0.3678 0.01111 0.00482 -0.0845 0.4111 0.7023
-0.250 0.3966 0.01127 0.00491 -0.0846 0.4012 0.7051
0.000 0.4253 0.01147 0.00503 -0.0847 0.3924 0.7086
0.250 0.4553 0.01160 0.00512 -0.0850 0.3853 0.7125
0.500 0.4851 0.01180 0.00523 -0.0854 0.3777 0.7159
0.750 0.5127 0.01193 0.00532 -0.0852 0.3704 0.7195
1.000 0.5410 0.01203 0.00544 -0.0851 0.3651 0.7222
1.250 0.5694 0.01217 0.00555 -0.0851 0.3590 0.7248
1.500 0.5975 0.01237 0.00568 -0.0851 0.3525 0.7275
1.750 0.6266 0.01250 0.00580 -0.0853 0.3473 0.7302
2.000 0.6565 0.01258 0.00587 -0.0857 0.3423 0.7326
2.250 0.6861 0.01270 0.00593 -0.0861 0.3368 0.7346
2.500 0.7151 0.01290 0.00605 -0.0864 0.3311 0.7364
2.750 0.7447 0.01304 0.00617 -0.0868 0.3266 0.7381
3.000 0.7739 0.01304 0.00619 -0.0871 0.3220 0.7400
3.250 0.8023 0.01314 0.00627 -0.0872 0.3172 0.7416
3.500 0.8299 0.01333 0.00641 -0.0872 0.3122 0.7431
3.750 0.8578 0.01350 0.00658 -0.0872 0.3076 0.7448
4.000 0.8864 0.01360 0.00671 -0.0873 0.3035 0.7468
4.250 0.9147 0.01373 0.00684 -0.0874 0.2990 0.7487
4.500 0.9425 0.01392 0.00698 -0.0875 0.2943 0.7506
4.750 0.9701 0.01415 0.00718 -0.0876 0.2896 0.7525
5.000 0.9990 0.01425 0.00731 -0.0878 0.2857 0.7544
5.250 1.0275 0.01438 0.00745 -0.0880 0.2813 0.7563
5.500 1.0552 0.01459 0.00761 -0.0881 0.2768 0.7581
5.750 1.0821 0.01487 0.00785 -0.0881 0.2721 0.7599
6.000 1.1098 0.01494 0.00799 -0.0881 0.2684 0.7620
6.250 1.1367 0.01508 0.00815 -0.0880 0.2641 0.7638
6.500 1.1628 0.01530 0.00835 -0.0878 0.2597 0.7656
6.750 1.1882 0.01560 0.00864 -0.0875 0.2551 0.7676
7.000 1.2153 0.01573 0.00884 -0.0874 0.2513 0.7696
7.250 1.2417 0.01592 0.00904 -0.0872 0.2468 0.7718
7.500 1.2670 0.01619 0.00929 -0.0869 0.2424 0.7741
7.750 1.2924 0.01648 0.00958 -0.0867 0.2380 0.7764
8.000 1.3189 0.01667 0.00981 -0.0866 0.2338 0.7786
8.250 1.3439 0.01691 0.01006 -0.0862 0.2293 0.7810
8.500 1.3661 0.01729 0.01040 -0.0854 0.2245 0.7834
8.750 1.3911 0.01746 0.01067 -0.0850 0.2206 0.7858
9.000 1.4148 0.01771 0.01096 -0.0844 0.2161 0.7882
9.250 1.4364 0.01809 0.01132 -0.0835 0.2115 0.7909
9.500 1.4592 0.01840 0.01168 -0.0828 0.2072 0.7937
9.750 1.4818 0.01869 0.01201 -0.0821 0.2025 0.7966
10.000 1.5017 0.01912 0.01241 -0.0810 0.1979 0.7992
10.250 1.5207 0.01946 0.01281 -0.0796 0.1937 0.8021
10.500 1.5379 0.01979 0.01320 -0.0779 0.1893 0.8049
10.750 1.5540 0.02029 0.01371 -0.0762 0.1848 0.8080
11.000 1.5725 0.02076 0.01424 -0.0749 0.1805 0.8114
11.250 1.5912 0.02124 0.01476 -0.0738 0.1757 0.8149
11.500 1.6065 0.02194 0.01544 -0.0723 0.1712 0.8184
11.750 1.6248 0.02242 0.01601 -0.0711 0.1669 0.8220
12.000 1.6403 0.02307 0.01670 -0.0696 0.1623 0.8257
12.250 1.6536 0.02389 0.01754 -0.0680 0.1581 0.8297
12.500 1.6706 0.02454 0.01826 -0.0669 0.1536 0.8338
12.750 1.6833 0.02546 0.01920 -0.0654 0.1493 0.8376
13.000 1.6965 0.02632 0.02013 -0.0640 0.1452 0.8415
13.250 1.7094 0.02724 0.02112 -0.0626 0.1409 0.8456
13.500 1.7177 0.02853 0.02242 -0.0610 0.1370 0.8502
13.750 1.7318 0.02948 0.02345 -0.0600 0.1329 0.8547
14.000 1.7397 0.03081 0.02483 -0.0584 0.1289 0.8590
14.250 1.7488 0.03213 0.02623 -0.0572 0.1248 0.8639
14.500 1.7568 0.03362 0.02776 -0.0560 0.1205 0.8691
14.750 1.7618 0.03534 0.02953 -0.0547 0.1165 0.8740
15.000 1.7686 0.03695 0.03122 -0.0536 0.1124 0.8797
15.500 1.7742 0.04102 0.03546 -0.0514 0.1059 0.8921
15.750 1.7748 0.04338 0.03790 -0.0505 0.1030 0.8994
16.000 1.7700 0.04630 0.04090 -0.0496 0.1006 0.9068
16.250 1.7717 0.04869 0.04342 -0.0490 0.0980 0.9162
16.500 1.7667 0.05173 0.04657 -0.0484 0.0956 0.9289
16.750 1.7521 0.05530 0.05026 -0.0472 0.0938 1.0000
17.000 1.7473 0.05919 0.05427 -0.0479 0.0916 1.0000
17.250 1.7403 0.06349 0.05868 -0.0489 0.0894 1.0000
17.500 1.7275 0.06874 0.06402 -0.0504 0.0875 1.0000
17.750 1.7078 0.07510 0.07047 -0.0523 0.0859 1.0000
18.000 1.6960 0.08042 0.07594 -0.0541 0.0841 1.0000
18.250 1.6804 0.08628 0.08191 -0.0561 0.0823 1.0000
18.500 1.6606 0.09276 0.08849 -0.0583 0.0807 1.0000
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