USA 45 M AIRFOIL (usa45m-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 45 M AIRFOIL (usa45m-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.3 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa45m-il-1000000.txt Download as CSV file: xf-usa45m-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4070 0.09743 0.09578 -0.0241 1.0000 0.0211
-10.000 -0.4086 0.09260 0.09096 -0.0265 1.0000 0.0212
-9.750 -0.4237 0.08540 0.08379 -0.0296 1.0000 0.0214
-9.500 -0.4237 0.08187 0.08027 -0.0310 1.0000 0.0216
-9.250 -0.4214 0.07910 0.07752 -0.0320 1.0000 0.0217
-9.000 -0.4185 0.07662 0.07506 -0.0327 1.0000 0.0219
-8.750 -0.4185 0.07378 0.07224 -0.0340 1.0000 0.0221
-8.500 -0.4377 0.06894 0.06744 -0.0375 1.0000 0.0221
-8.250 -0.4538 0.06474 0.06322 -0.0381 1.0000 0.0222
-8.000 -0.4453 0.06053 0.05897 -0.0418 0.9978 0.0226
-7.750 -0.4274 0.05610 0.05446 -0.0466 0.9895 0.0235
-7.500 -0.4168 0.04431 0.04212 -0.0539 0.9773 0.0257
-7.250 -0.4125 0.03447 0.03180 -0.0575 0.9671 0.0264
-7.000 -0.3808 0.03303 0.03031 -0.0599 0.9563 0.0267
-6.750 -0.3507 0.03179 0.02899 -0.0618 0.9399 0.0272
-6.500 -0.3268 0.03062 0.02769 -0.0620 0.9156 0.0278
-6.250 -0.3079 0.02903 0.02587 -0.0610 0.8873 0.0289
-6.000 -0.2851 0.02872 0.02511 -0.0588 0.8576 0.0312
-5.750 -0.2697 0.02682 0.02286 -0.0569 0.8288 0.0312
-5.500 -0.2666 0.00897 0.00464 -0.0504 0.7698 0.0321
-5.250 -0.2448 0.00831 0.00388 -0.0498 0.7444 0.0326
-5.000 -0.2226 0.01829 0.01334 -0.0516 0.7500 0.0300
-4.750 -0.2022 0.01637 0.01109 -0.0501 0.7210 0.0294
-4.500 -0.1797 0.01501 0.00943 -0.0489 0.6917 0.0293
-4.250 -0.1559 0.01404 0.00822 -0.0480 0.6627 0.0295
-4.000 -0.1311 0.01358 0.00757 -0.0472 0.6339 0.0301
-3.750 -0.1062 0.01307 0.00687 -0.0465 0.6045 0.0304
-3.500 -0.0812 0.01261 0.00624 -0.0458 0.5752 0.0307
-3.250 -0.0559 0.01230 0.00577 -0.0452 0.5462 0.0309
-3.000 -0.0303 0.01200 0.00533 -0.0446 0.5209 0.0311
-2.750 -0.0044 0.01183 0.00504 -0.0441 0.4995 0.0313
-2.500 0.0197 0.01101 0.00412 -0.0433 0.4824 0.0316
-2.000 0.0692 0.01021 0.00319 -0.0419 0.4543 0.0329
-1.750 0.0954 0.01007 0.00302 -0.0415 0.4435 0.0338
-1.500 0.1214 0.00993 0.00283 -0.0410 0.4342 0.0346
-1.250 0.1478 0.00978 0.00264 -0.0406 0.4260 0.0353
-1.000 0.1741 0.00967 0.00248 -0.0402 0.4183 0.0361
-0.750 0.2008 0.00955 0.00233 -0.0398 0.4111 0.0369
-0.500 0.2272 0.00949 0.00222 -0.0394 0.4040 0.0375
-0.250 0.2542 0.00939 0.00210 -0.0391 0.3986 0.0382
0.000 0.2804 0.00923 0.00189 -0.0387 0.3928 0.0407
0.250 0.3072 0.00919 0.00183 -0.0384 0.3871 0.0430
0.500 0.3345 0.00915 0.00179 -0.0381 0.3818 0.0456
0.750 0.3612 0.00910 0.00171 -0.0378 0.3763 0.0510
1.000 0.3879 0.00904 0.00168 -0.0375 0.3715 0.0657
1.250 0.4021 0.00759 0.00164 -0.0354 0.3677 0.5682
1.500 0.4138 0.00675 0.00172 -0.0318 0.3635 0.8516
1.750 0.4482 0.00675 0.00190 -0.0327 0.3577 0.9531
2.000 0.4959 0.00687 0.00200 -0.0368 0.3527 0.9735
2.250 0.5371 0.00703 0.00210 -0.0395 0.3473 0.9830
2.500 0.5865 0.00720 0.00220 -0.0442 0.3414 0.9876
2.750 0.6425 0.00733 0.00229 -0.0501 0.3357 0.9947
3.000 0.6804 0.00741 0.00231 -0.0523 0.3300 0.9968
3.250 0.7187 0.00749 0.00235 -0.0547 0.3243 0.9990
3.500 0.7505 0.00755 0.00238 -0.0556 0.3187 1.0000
3.750 0.7736 0.00765 0.00244 -0.0546 0.3141 1.0000
4.000 0.7969 0.00773 0.00252 -0.0537 0.3104 1.0000
4.250 0.8204 0.00780 0.00259 -0.0528 0.3065 1.0000
4.500 0.8437 0.00790 0.00267 -0.0519 0.3019 1.0000
4.750 0.8664 0.00804 0.00278 -0.0509 0.2969 1.0000
5.000 0.8902 0.00811 0.00285 -0.0501 0.2921 1.0000
5.250 0.9133 0.00823 0.00296 -0.0491 0.2857 1.0000
5.500 0.9364 0.00836 0.00307 -0.0482 0.2804 1.0000
5.750 0.9597 0.00847 0.00318 -0.0473 0.2738 1.0000
6.000 0.9824 0.00865 0.00331 -0.0463 0.2669 1.0000
6.250 1.0059 0.00876 0.00344 -0.0455 0.2612 1.0000
6.500 1.0284 0.00896 0.00360 -0.0445 0.2530 1.0000
6.750 1.0515 0.00912 0.00374 -0.0436 0.2435 1.0000
7.000 1.0738 0.00934 0.00392 -0.0426 0.2317 1.0000
7.250 1.0958 0.00960 0.00413 -0.0416 0.2188 1.0000
7.500 1.1168 0.00994 0.00438 -0.0404 0.2015 1.0000
7.750 1.1351 0.01049 0.00476 -0.0388 0.1731 1.0000
8.000 1.1498 0.01131 0.00533 -0.0368 0.1346 1.0000
8.250 1.1509 0.01314 0.00662 -0.0327 0.0518 1.0000
8.500 1.1620 0.01419 0.00754 -0.0300 0.0214 1.0000
8.750 1.1810 0.01465 0.00802 -0.0286 0.0188 1.0000
9.000 1.2004 0.01506 0.00847 -0.0272 0.0177 1.0000
9.250 1.2183 0.01556 0.00901 -0.0257 0.0165 1.0000
9.500 1.2339 0.01619 0.00970 -0.0238 0.0153 1.0000
9.750 1.2524 0.01661 0.01016 -0.0224 0.0148 1.0000
10.000 1.2692 0.01711 0.01069 -0.0207 0.0142 1.0000
10.250 1.2843 0.01767 0.01130 -0.0189 0.0136 1.0000
10.500 1.2972 0.01826 0.01194 -0.0166 0.0131 1.0000
10.750 1.3038 0.01898 0.01272 -0.0134 0.0126 1.0000
11.000 1.3041 0.02006 0.01391 -0.0094 0.0121 1.0000
11.250 1.3125 0.02084 0.01475 -0.0070 0.0119 1.0000
11.500 1.3214 0.02166 0.01563 -0.0048 0.0117 1.0000
11.750 1.3288 0.02264 0.01668 -0.0027 0.0115 1.0000
12.000 1.3363 0.02369 0.01780 -0.0010 0.0112 1.0000
12.250 1.3402 0.02511 0.01930 0.0008 0.0109 1.0000
12.500 1.3466 0.02650 0.02075 0.0019 0.0105 1.0000
12.750 1.3470 0.02855 0.02289 0.0030 0.0104 1.0000
13.000 1.3506 0.03056 0.02497 0.0034 0.0101 1.0000
13.250 1.3481 0.03342 0.02794 0.0033 0.0100 1.0000
13.500 1.3445 0.03672 0.03133 0.0027 0.0098 1.0000
13.750 1.3362 0.04084 0.03558 0.0016 0.0098 1.0000
14.000 1.3263 0.04537 0.04023 0.0002 0.0096 1.0000
14.250 1.3102 0.05080 0.04578 -0.0016 0.0095 1.0000
14.500 1.2881 0.05700 0.05211 -0.0035 0.0094 1.0000
14.750 1.2727 0.06224 0.05746 -0.0050 0.0094 1.0000
15.000 1.2525 0.06803 0.06335 -0.0066 0.0093 1.0000
15.250 1.2469 0.07208 0.06749 -0.0078 0.0092 1.0000
15.500 1.2380 0.07658 0.07205 -0.0091 0.0093 1.0000
15.750 1.2344 0.08047 0.07602 -0.0103 0.0091 1.0000
16.000 1.2263 0.08495 0.08058 -0.0116 0.0091 1.0000
16.250 1.2206 0.08917 0.08486 -0.0129 0.0090 1.0000
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