USA 45 M AIRFOIL (usa45m-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 45 M AIRFOIL (usa45m-il) Reynolds number: 500,000 Max Cl/Cd: 90.37 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa45m-il-500000-n5.txt Download as CSV file: xf-usa45m-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 45 M 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4170 0.11034 0.10794 -0.0181 1.0000 0.0157
-11.000 -0.4176 0.10594 0.10356 -0.0199 1.0000 0.0162
-10.750 -0.4386 0.09641 0.09403 -0.0246 1.0000 0.0174
-10.500 -0.4335 0.09390 0.09155 -0.0256 1.0000 0.0177
-10.250 -0.4261 0.09189 0.08955 -0.0262 1.0000 0.0179
-10.000 -0.4238 0.08873 0.08641 -0.0275 1.0000 0.0181
-9.750 -0.4231 0.08530 0.08300 -0.0289 1.0000 0.0183
-9.500 -0.4246 0.08151 0.07924 -0.0307 1.0000 0.0186
-9.250 -0.4279 0.07758 0.07534 -0.0327 1.0000 0.0190
-9.000 -0.4393 0.07246 0.07026 -0.0358 1.0000 0.0192
-8.750 -0.4655 0.06663 0.06447 -0.0397 1.0000 0.0193
-8.500 -0.4843 0.05939 0.05716 -0.0436 0.9954 0.0196
-8.000 -0.4963 0.03544 0.03210 -0.0551 0.9622 0.0222
-7.750 -0.4684 0.03369 0.03019 -0.0570 0.9502 0.0225
-7.500 -0.4386 0.03213 0.02848 -0.0588 0.9347 0.0229
-7.250 -0.4115 0.03041 0.02657 -0.0600 0.9148 0.0235
-7.000 -0.3927 0.02778 0.02359 -0.0594 0.8896 0.0240
-6.750 -0.3760 0.02519 0.02060 -0.0581 0.8638 0.0246
-6.500 -0.3594 0.02274 0.01770 -0.0564 0.8365 0.0252
-6.250 -0.3403 0.02099 0.01555 -0.0549 0.8094 0.0261
-6.000 -0.3195 0.01974 0.01396 -0.0536 0.7826 0.0264
-5.750 -0.2977 0.01879 0.01271 -0.0524 0.7559 0.0266
-5.500 -0.2751 0.01804 0.01169 -0.0514 0.7278 0.0268
-5.250 -0.2534 0.01678 0.01014 -0.0503 0.6989 0.0271
-5.000 -0.2304 0.01593 0.00907 -0.0494 0.6705 0.0275
-4.750 -0.2065 0.01534 0.00830 -0.0486 0.6435 0.0278
-4.250 -0.1576 0.01459 0.00724 -0.0472 0.5890 0.0285
-4.000 -0.1328 0.01432 0.00683 -0.0466 0.5622 0.0290
-3.750 -0.1079 0.01398 0.00634 -0.0459 0.5381 0.0295
-3.500 -0.0827 0.01361 0.00584 -0.0453 0.5176 0.0299
-3.250 -0.0575 0.01327 0.00538 -0.0447 0.4989 0.0302
-3.000 -0.0323 0.01297 0.00497 -0.0441 0.4819 0.0307
-2.750 -0.0069 0.01270 0.00460 -0.0436 0.4678 0.0311
-2.500 0.0186 0.01244 0.00426 -0.0430 0.4560 0.0316
-2.250 0.0442 0.01222 0.00396 -0.0425 0.4459 0.0320
-2.000 0.0700 0.01200 0.00369 -0.0420 0.4370 0.0324
-1.500 0.1217 0.01167 0.00324 -0.0410 0.4205 0.0331
-1.250 0.1475 0.01152 0.00303 -0.0406 0.4134 0.0337
-1.000 0.1732 0.01128 0.00278 -0.0401 0.4076 0.0351
-0.750 0.1995 0.01117 0.00264 -0.0397 0.4014 0.0362
-0.500 0.2258 0.01110 0.00253 -0.0393 0.3956 0.0372
-0.250 0.2525 0.01102 0.00243 -0.0389 0.3898 0.0384
0.000 0.2790 0.01097 0.00234 -0.0386 0.3841 0.0399
0.250 0.3057 0.01094 0.00228 -0.0383 0.3795 0.0413
0.500 0.3324 0.01087 0.00220 -0.0379 0.3747 0.0443
0.750 0.3590 0.01085 0.00217 -0.0376 0.3695 0.0488
1.000 0.3855 0.01084 0.00215 -0.0373 0.3647 0.0575
1.250 0.4094 0.01038 0.00213 -0.0367 0.3603 0.2205
1.500 0.4230 0.00911 0.00215 -0.0343 0.3566 0.6429
1.750 0.4391 0.00851 0.00229 -0.0314 0.3526 0.8631
2.000 0.4858 0.00859 0.00246 -0.0351 0.3473 0.9458
2.250 0.5399 0.00876 0.00259 -0.0406 0.3414 0.9748
2.500 0.5988 0.00897 0.00271 -0.0471 0.3353 0.9907
2.750 0.6355 0.00906 0.00277 -0.0491 0.3307 0.9947
3.000 0.6723 0.00914 0.00282 -0.0510 0.3257 0.9979
3.250 0.7056 0.00927 0.00289 -0.0523 0.3206 1.0000
3.500 0.7288 0.00936 0.00296 -0.0514 0.3166 1.0000
3.750 0.7521 0.00946 0.00305 -0.0505 0.3122 1.0000
4.000 0.7749 0.00959 0.00315 -0.0495 0.3069 1.0000
4.250 0.7980 0.00971 0.00325 -0.0485 0.3016 1.0000
4.500 0.8213 0.00983 0.00336 -0.0476 0.2961 1.0000
4.750 0.8442 0.00997 0.00348 -0.0467 0.2913 1.0000
5.000 0.8674 0.01011 0.00362 -0.0458 0.2873 1.0000
5.250 0.8909 0.01024 0.00376 -0.0449 0.2825 1.0000
5.500 0.9140 0.01040 0.00391 -0.0440 0.2775 1.0000
5.750 0.9371 0.01057 0.00406 -0.0431 0.2718 1.0000
6.000 0.9600 0.01075 0.00423 -0.0422 0.2623 1.0000
6.250 0.9830 0.01094 0.00440 -0.0413 0.2543 1.0000
6.500 1.0055 0.01117 0.00459 -0.0404 0.2456 1.0000
6.750 1.0284 0.01138 0.00480 -0.0395 0.2357 1.0000
7.000 1.0505 0.01164 0.00503 -0.0385 0.2240 1.0000
7.250 1.0716 0.01198 0.00530 -0.0375 0.2078 1.0000
7.500 1.0917 0.01241 0.00563 -0.0362 0.1894 1.0000
7.750 1.1115 0.01286 0.00599 -0.0350 0.1718 1.0000
8.000 1.1291 0.01348 0.00649 -0.0334 0.1482 1.0000
8.250 1.1442 0.01429 0.00711 -0.0315 0.1184 1.0000
8.500 1.1472 0.01597 0.00836 -0.0280 0.0496 1.0000
8.750 1.1569 0.01708 0.00938 -0.0254 0.0216 1.0000
9.000 1.1740 0.01764 0.00996 -0.0238 0.0182 1.0000
9.250 1.1916 0.01813 0.01052 -0.0223 0.0167 1.0000
9.500 1.2078 0.01869 0.01113 -0.0206 0.0154 1.0000
9.750 1.2217 0.01934 0.01184 -0.0186 0.0142 1.0000
10.000 1.2343 0.01993 0.01250 -0.0164 0.0135 1.0000
10.250 1.2453 0.02053 0.01317 -0.0139 0.0129 1.0000
10.500 1.2552 0.02121 0.01393 -0.0115 0.0125 1.0000
10.750 1.2640 0.02199 0.01478 -0.0090 0.0119 1.0000
11.000 1.2716 0.02289 0.01575 -0.0067 0.0115 1.0000
11.250 1.2779 0.02393 0.01686 -0.0045 0.0111 1.0000
11.500 1.2815 0.02523 0.01824 -0.0023 0.0108 1.0000
11.750 1.2803 0.02700 0.02011 -0.0002 0.0104 1.0000
12.000 1.2857 0.02845 0.02166 0.0010 0.0100 1.0000
12.250 1.2868 0.03043 0.02375 0.0020 0.0100 1.0000
12.500 1.2891 0.03249 0.02591 0.0026 0.0096 1.0000
12.750 1.2875 0.03518 0.02872 0.0027 0.0095 1.0000
13.000 1.2860 0.03810 0.03174 0.0025 0.0092 1.0000
13.250 1.2827 0.04145 0.03521 0.0018 0.0090 1.0000
13.500 1.2757 0.04545 0.03933 0.0007 0.0089 1.0000
13.750 1.2679 0.04968 0.04368 -0.0006 0.0087 1.0000
14.000 1.2584 0.05422 0.04833 -0.0020 0.0087 1.0000
14.250 1.2463 0.05909 0.05332 -0.0034 0.0086 1.0000
14.500 1.2352 0.06384 0.05818 -0.0049 0.0085 1.0000
14.750 1.2221 0.06890 0.06334 -0.0064 0.0085 1.0000
15.000 1.2107 0.07381 0.06835 -0.0080 0.0084 1.0000
15.250 1.2004 0.07866 0.07328 -0.0096 0.0083 1.0000
15.500 1.1893 0.08375 0.07846 -0.0113 0.0083 1.0000
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