NACA/LANGLEY SYMMETRICAL (n0011sc-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA/LANGLEY SYMMETRICAL (n0011sc-il) Reynolds number: 100,000 Max Cl/Cd: 30.54 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n0011sc-il-100000-n5.txt Download as CSV file: xf-n0011sc-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA/LANGLEY SYMMETRICAL
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6464 0.09955 0.09352 -0.0351 1.0000 0.0410
-11.750 -0.7467 0.07361 0.06740 -0.0519 1.0000 0.0394
-11.500 -0.8094 0.06471 0.05817 -0.0530 1.0000 0.0387
-11.250 -0.8568 0.05942 0.05256 -0.0489 1.0000 0.0384
-11.000 -0.8802 0.05669 0.04964 -0.0442 1.0000 0.0384
-10.750 -0.8951 0.05483 0.04767 -0.0393 1.0000 0.0387
-10.500 -0.9107 0.05308 0.04578 -0.0338 1.0000 0.0390
-10.250 -0.9212 0.05122 0.04377 -0.0289 1.0000 0.0394
-10.000 -0.9288 0.04926 0.04163 -0.0242 1.0000 0.0399
-9.750 -0.9350 0.04724 0.03939 -0.0196 1.0000 0.0405
-9.500 -0.9403 0.04501 0.03688 -0.0149 1.0000 0.0410
-9.250 -0.9435 0.04275 0.03428 -0.0103 1.0000 0.0417
-9.000 -0.9434 0.04052 0.03169 -0.0061 1.0000 0.0423
-8.750 -0.9396 0.03841 0.02920 -0.0023 1.0000 0.0429
-8.500 -0.9327 0.03641 0.02683 0.0012 1.0000 0.0436
-8.250 -0.9199 0.03503 0.02537 0.0035 1.0000 0.0442
-8.000 -0.9067 0.03387 0.02412 0.0059 1.0000 0.0451
-7.750 -0.8930 0.03278 0.02291 0.0082 1.0000 0.0463
-7.500 -0.8784 0.03165 0.02160 0.0105 1.0000 0.0479
-7.250 -0.8624 0.03042 0.02009 0.0127 1.0000 0.0497
-7.000 -0.8453 0.02932 0.01893 0.0145 1.0000 0.0511
-6.750 -0.8283 0.02842 0.01801 0.0163 1.0000 0.0525
-6.500 -0.8105 0.02752 0.01703 0.0182 1.0000 0.0543
-6.250 -0.7925 0.02670 0.01605 0.0200 1.0000 0.0570
-6.000 -0.7751 0.02587 0.01522 0.0219 1.0000 0.0593
-5.750 -0.7580 0.02518 0.01454 0.0238 1.0000 0.0620
-5.500 -0.7403 0.02448 0.01375 0.0257 1.0000 0.0650
-5.250 -0.7234 0.02380 0.01306 0.0277 1.0000 0.0686
-5.000 -0.7068 0.02321 0.01249 0.0298 1.0000 0.0727
-4.750 -0.6898 0.02262 0.01185 0.0319 1.0000 0.0774
-4.500 -0.6738 0.02206 0.01133 0.0341 1.0000 0.0826
-4.250 -0.6572 0.02154 0.01080 0.0362 1.0000 0.0895
-4.000 -0.6409 0.02105 0.01035 0.0383 1.0000 0.0974
-3.750 -0.6246 0.02056 0.00992 0.0405 1.0000 0.1075
-3.500 -0.6081 0.02010 0.00953 0.0426 1.0000 0.1210
-3.250 -0.5914 0.01966 0.00918 0.0447 1.0000 0.1388
-3.000 -0.5748 0.01922 0.00889 0.0467 1.0000 0.1634
-2.750 -0.5583 0.01874 0.00863 0.0487 1.0000 0.2009
-2.500 -0.5333 0.01821 0.00848 0.0488 0.9975 0.2688
-2.250 -0.5074 0.01749 0.00843 0.0487 0.9943 0.3930
-2.000 -0.3926 0.01698 0.00994 0.0329 1.0000 0.8201
-1.750 -0.3415 0.01785 0.01077 0.0293 1.0000 0.8779
-1.500 -0.3097 0.01848 0.01132 0.0290 1.0000 0.9081
-1.250 -0.2759 0.01912 0.01188 0.0283 1.0000 0.9326
-1.000 -0.2242 0.01981 0.01247 0.0238 1.0000 0.9498
-0.750 -0.1589 0.02055 0.01314 0.0165 1.0000 0.9690
-0.500 -0.0836 0.02107 0.01361 0.0069 1.0000 0.9866
-0.250 -0.0362 0.02120 0.01370 0.0024 1.0000 0.9949
0.000 0.0000 0.02126 0.01375 0.0000 1.0000 1.0000
0.250 0.0360 0.02119 0.01370 -0.0024 0.9950 1.0000
0.500 0.0845 0.02107 0.01360 -0.0071 0.9864 1.0000
0.750 0.1591 0.02054 0.01313 -0.0165 0.9689 1.0000
1.000 0.2248 0.01979 0.01246 -0.0239 0.9497 1.0000
1.250 0.2757 0.01912 0.01187 -0.0282 0.9324 1.0000
1.500 0.3097 0.01847 0.01131 -0.0290 0.9081 1.0000
1.750 0.3415 0.01785 0.01077 -0.0293 0.8781 1.0000
2.000 0.3869 0.01706 0.01003 -0.0319 0.8256 1.0000
2.250 0.5074 0.01747 0.00843 -0.0487 0.3956 0.9943
2.500 0.5334 0.01821 0.00848 -0.0489 0.2693 0.9975
2.750 0.5583 0.01874 0.00863 -0.0487 0.2010 1.0000
3.000 0.5747 0.01921 0.00888 -0.0467 0.1642 1.0000
3.250 0.5914 0.01966 0.00918 -0.0447 0.1388 1.0000
3.500 0.6080 0.02009 0.00952 -0.0426 0.1210 1.0000
3.750 0.6245 0.02056 0.00992 -0.0405 0.1075 1.0000
4.000 0.6408 0.02104 0.01034 -0.0384 0.0974 1.0000
4.250 0.6571 0.02154 0.01080 -0.0362 0.0892 1.0000
4.500 0.6737 0.02206 0.01133 -0.0340 0.0826 1.0000
4.750 0.6896 0.02263 0.01185 -0.0319 0.0773 1.0000
5.000 0.7067 0.02321 0.01249 -0.0298 0.0728 1.0000
5.250 0.7233 0.02379 0.01305 -0.0277 0.0685 1.0000
5.500 0.7402 0.02448 0.01375 -0.0257 0.0652 1.0000
5.750 0.7579 0.02518 0.01453 -0.0238 0.0619 1.0000
6.000 0.7750 0.02588 0.01522 -0.0219 0.0593 1.0000
6.250 0.7924 0.02668 0.01605 -0.0200 0.0568 1.0000
6.500 0.8105 0.02753 0.01703 -0.0182 0.0542 1.0000
6.750 0.8280 0.02840 0.01799 -0.0163 0.0524 1.0000
7.000 0.8451 0.02931 0.01890 -0.0145 0.0510 1.0000
7.250 0.8622 0.03043 0.02013 -0.0126 0.0494 1.0000
7.500 0.8781 0.03162 0.02158 -0.0105 0.0477 1.0000
7.750 0.8928 0.03274 0.02287 -0.0082 0.0462 1.0000
8.000 0.9065 0.03382 0.02405 -0.0058 0.0449 1.0000
8.250 0.9198 0.03502 0.02534 -0.0035 0.0441 1.0000
8.500 0.9326 0.03643 0.02683 -0.0012 0.0435 1.0000
8.750 0.9389 0.03848 0.02930 0.0024 0.0427 1.0000
9.000 0.9429 0.04057 0.03176 0.0062 0.0422 1.0000
9.250 0.9432 0.04280 0.03434 0.0104 0.0417 1.0000
9.500 0.9403 0.04503 0.03691 0.0149 0.0410 1.0000
9.750 0.9347 0.04730 0.03945 0.0196 0.0405 1.0000
10.000 0.9277 0.04940 0.04179 0.0243 0.0399 1.0000
10.250 0.9175 0.05162 0.04422 0.0293 0.0396 1.0000
10.500 0.9043 0.05360 0.04637 0.0346 0.0392 1.0000
10.750 0.8929 0.05502 0.04788 0.0396 0.0387 1.0000
11.000 0.8736 0.05718 0.05019 0.0448 0.0386 1.0000
11.250 0.8456 0.06033 0.05356 0.0496 0.0386 1.0000
11.500 0.8154 0.06417 0.05759 0.0528 0.0386 1.0000
11.750 0.7381 0.07500 0.06883 0.0510 0.0395 1.0000
12.000 0.6477 0.09944 0.09341 0.0352 0.0416 1.0000
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Polar data table (+)
Polar graphs
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