NACA 2-H-15 AIRFOIL (n2h15-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: NACA 2-H-15 AIRFOIL (n2h15-il) Reynolds number: 200,000 Max Cl/Cd: 38.08 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n2h15-il-200000-n5.txt Download as CSV file: xf-n2h15-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2-H-15 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.1406 0.11480 0.10989 -0.0807 0.7162 0.0379
-12.000 -0.1443 0.11210 0.10721 -0.0825 0.7150 0.0381
-11.750 -0.1489 0.10922 0.10436 -0.0843 0.7138 0.0382
-11.500 -0.1391 0.10589 0.10105 -0.0842 0.7129 0.0385
-11.250 -0.1248 0.10340 0.09854 -0.0838 0.7119 0.0390
-11.000 -0.1171 0.10102 0.09617 -0.0840 0.7110 0.0395
-10.750 -0.1125 0.09859 0.09373 -0.0844 0.7102 0.0399
-10.500 -0.1089 0.09615 0.09130 -0.0849 0.7093 0.0405
-10.250 -0.1068 0.09363 0.08878 -0.0855 0.7085 0.0410
-10.000 -0.1056 0.09111 0.08627 -0.0861 0.7077 0.0418
-9.750 -0.1059 0.08850 0.08367 -0.0867 0.7069 0.0425
-9.500 -0.1080 0.08576 0.08092 -0.0874 0.7062 0.0431
-9.250 -0.1196 0.08259 0.07777 -0.0892 0.7054 0.0446
-9.000 -0.1329 0.07944 0.07472 -0.0914 0.7031 0.0449
-8.750 -0.1544 0.07595 0.07128 -0.0938 0.7008 0.0451
-8.500 -0.1731 0.07319 0.06851 -0.0931 0.6987 0.0452
-8.250 -0.1953 0.07079 0.06605 -0.0902 0.6969 0.0453
-8.000 -0.2120 0.06887 0.06406 -0.0864 0.6954 0.0454
-7.750 -0.2306 0.06716 0.06224 -0.0817 0.6940 0.0454
-7.500 -0.2366 0.06426 0.05929 -0.0790 0.6929 0.0457
-7.250 -0.2362 0.06180 0.05678 -0.0767 0.6919 0.0459
-7.000 -0.2271 0.05978 0.05480 -0.0754 0.6911 0.0464
-6.750 -0.2230 0.05807 0.05306 -0.0731 0.6903 0.0470
-6.500 -0.2202 0.05644 0.05136 -0.0705 0.6896 0.0477
-6.250 -0.2190 0.05513 0.05006 -0.0684 0.6857 0.0483
-6.000 -0.2167 0.05364 0.04850 -0.0659 0.6831 0.0492
-5.750 -0.2149 0.05192 0.04665 -0.0628 0.6811 0.0501
-5.500 -0.2408 0.04608 0.03991 -0.0523 0.6790 0.0382
-5.250 -0.2282 0.04427 0.03816 -0.0509 0.6779 0.0376
-5.000 -0.2205 0.04257 0.03634 -0.0478 0.6768 0.0370
-4.750 -0.2133 0.04077 0.03434 -0.0443 0.6759 0.0365
-4.500 -0.2051 0.03898 0.03233 -0.0408 0.6751 0.0361
-4.250 -0.1956 0.03720 0.03030 -0.0373 0.6744 0.0356
-4.000 -0.1940 0.03727 0.03027 -0.0344 0.6671 0.0353
-3.750 -0.1839 0.03619 0.02897 -0.0313 0.6647 0.0358
-3.500 -0.1709 0.03495 0.02749 -0.0284 0.6631 0.0359
-3.250 -0.1554 0.03363 0.02591 -0.0259 0.6619 0.0361
-3.000 -0.1368 0.03235 0.02437 -0.0239 0.6610 0.0359
-2.750 -0.1149 0.03113 0.02291 -0.0226 0.6602 0.0357
-2.500 -0.0894 0.02991 0.02145 -0.0219 0.6596 0.0357
-2.250 -0.0961 0.03135 0.02287 -0.0183 0.6507 0.0356
-2.000 -0.0705 0.03060 0.02193 -0.0181 0.6490 0.0357
-1.750 -0.0395 0.02978 0.02095 -0.0189 0.6477 0.0359
-1.500 -0.0054 0.02906 0.02008 -0.0204 0.6468 0.0362
-1.250 0.0318 0.02837 0.01928 -0.0224 0.6461 0.0365
-1.000 0.0694 0.02779 0.01860 -0.0246 0.6455 0.0373
-0.750 0.1063 0.02729 0.01804 -0.0267 0.6449 0.0386
-0.500 0.1536 0.02652 0.01732 -0.0311 0.6446 0.0395
-0.250 0.1370 0.02856 0.01938 -0.0258 0.6353 0.0394
0.000 0.1738 0.02833 0.01919 -0.0283 0.6339 0.0400
0.250 0.2042 0.02820 0.01909 -0.0294 0.6326 0.0408
0.500 0.2331 0.02807 0.01897 -0.0300 0.6315 0.0414
0.750 0.2624 0.02788 0.01879 -0.0306 0.6305 0.0429
1.000 0.2916 0.02767 0.01859 -0.0310 0.6297 0.0439
1.250 0.3207 0.02751 0.01841 -0.0313 0.6291 0.0456
1.500 0.3515 0.02728 0.01821 -0.0320 0.6285 0.0486
1.750 0.3809 0.02715 0.01807 -0.0325 0.6280 0.0522
2.250 0.3645 0.02986 0.02078 -0.0230 0.6149 0.0548
3.250 0.7648 0.03009 0.02376 -0.0861 0.6163 1.0000
3.500 0.7878 0.03012 0.02378 -0.0853 0.6152 1.0000
3.750 0.8112 0.03014 0.02380 -0.0846 0.6143 1.0000
4.000 0.8351 0.03017 0.02384 -0.0840 0.6135 1.0000
4.250 0.8600 0.03012 0.02380 -0.0835 0.6129 1.0000
4.750 0.8402 0.03342 0.02712 -0.0741 0.5993 1.0000
5.000 0.8658 0.03337 0.02710 -0.0737 0.5985 1.0000
5.250 0.8921 0.03328 0.02704 -0.0734 0.5979 1.0000
6.250 0.9022 0.03849 0.03240 -0.0628 0.5724 1.0000
6.500 0.9378 0.03730 0.03126 -0.0630 0.5706 1.0000
6.750 0.9798 0.03542 0.02944 -0.0637 0.5690 1.0000
8.000 1.0618 0.03547 0.02968 -0.0562 0.5074 1.0000
8.250 1.1368 0.02985 0.02338 -0.0579 0.4107 1.0000
8.500 1.1146 0.03248 0.02541 -0.0526 0.3314 1.0000
8.750 1.0883 0.03607 0.02851 -0.0479 0.2615 1.0000
9.000 1.0630 0.03993 0.03182 -0.0437 0.1799 1.0000
9.250 1.0556 0.04259 0.03417 -0.0412 0.1325 1.0000
9.500 1.0545 0.04481 0.03616 -0.0393 0.0959 1.0000
9.750 1.0586 0.04666 0.03789 -0.0378 0.0745 1.0000
10.000 1.0640 0.04844 0.03957 -0.0364 0.0607 1.0000
10.250 1.0725 0.04998 0.04110 -0.0352 0.0540 1.0000
10.500 1.0806 0.05159 0.04270 -0.0341 0.0497 1.0000
10.750 1.0897 0.05312 0.04428 -0.0331 0.0468 1.0000
11.000 1.0992 0.05464 0.04584 -0.0321 0.0437 1.0000
11.250 1.1074 0.05629 0.04750 -0.0311 0.0415 1.0000
11.500 1.1153 0.05800 0.04925 -0.0301 0.0394 1.0000
11.750 1.1248 0.05956 0.05088 -0.0292 0.0376 1.0000
12.000 1.1338 0.06119 0.05256 -0.0284 0.0359 1.0000
12.250 1.1419 0.06290 0.05430 -0.0275 0.0347 1.0000
12.500 1.1482 0.06479 0.05619 -0.0266 0.0334 1.0000
12.750 1.1584 0.06632 0.05781 -0.0258 0.0322 1.0000
13.000 1.1679 0.06792 0.05948 -0.0250 0.0308 1.0000
13.250 1.1774 0.06953 0.06114 -0.0243 0.0298 1.0000
13.500 1.1859 0.07122 0.06286 -0.0235 0.0288 1.0000
13.750 1.1945 0.07287 0.06453 -0.0227 0.0281 1.0000
14.000 1.2040 0.07438 0.06607 -0.0219 0.0274 1.0000
14.250 1.2149 0.07585 0.06765 -0.0212 0.0265 1.0000
14.500 1.2254 0.07736 0.06926 -0.0205 0.0255 1.0000
14.750 1.2352 0.07896 0.07093 -0.0199 0.0246 1.0000
15.000 1.2442 0.08064 0.07266 -0.0194 0.0238 1.0000
15.250 1.2534 0.08227 0.07431 -0.0188 0.0233 1.0000
15.500 1.2641 0.08362 0.07566 -0.0180 0.0228 1.0000
15.750 1.2738 0.08528 0.07748 -0.0173 0.0223 1.0000
16.000 1.2834 0.08692 0.07927 -0.0166 0.0217 1.0000
16.250 1.2909 0.08890 0.08140 -0.0161 0.0211 1.0000
16.500 1.2975 0.09099 0.08362 -0.0157 0.0205 1.0000
16.750 1.3025 0.09333 0.08607 -0.0155 0.0199 1.0000
17.000 1.3077 0.09565 0.08849 -0.0153 0.0195 1.0000
17.250 1.3126 0.09800 0.09093 -0.0151 0.0191 1.0000
17.500 1.3171 0.10039 0.09339 -0.0150 0.0188 1.0000
17.750 1.3218 0.10273 0.09580 -0.0148 0.0185 1.0000
18.000 1.3213 0.10600 0.09929 -0.0148 0.0182 1.0000
18.250 1.3193 0.10955 0.10307 -0.0149 0.0180 1.0000
18.500 1.3147 0.11359 0.10736 -0.0153 0.0177 1.0000
18.750 1.3086 0.11794 0.11195 -0.0160 0.0174 1.0000
19.000 1.3007 0.12268 0.11692 -0.0170 0.0172 1.0000
19.250 1.2913 0.12779 0.12226 -0.0184 0.0170 1.0000
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