USA 45 AIRFOIL (usa45-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 45 AIRFOIL (usa45-il) Reynolds number: 500,000 Max Cl/Cd: 89.87 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa45-il-500000-n5.txt Download as CSV file: xf-usa45-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 45 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8143 0.04338 0.04037 -0.0775 1.0000 0.0149
-13.500 -0.8415 0.03834 0.03512 -0.0791 1.0000 0.0150
-13.250 -0.8549 0.03570 0.03232 -0.0777 1.0000 0.0152
-13.000 -0.8681 0.03362 0.03008 -0.0746 1.0000 0.0154
-12.750 -0.8791 0.03215 0.02848 -0.0703 1.0000 0.0156
-12.500 -0.8903 0.03072 0.02689 -0.0653 1.0000 0.0159
-12.250 -0.8940 0.02929 0.02530 -0.0613 1.0000 0.0162
-12.000 -0.8953 0.02783 0.02363 -0.0576 0.9998 0.0165
-11.750 -0.8644 0.02680 0.02251 -0.0594 0.9954 0.0170
-11.500 -0.8327 0.02641 0.02211 -0.0607 0.9901 0.0174
-11.250 -0.8001 0.02582 0.02148 -0.0623 0.9845 0.0178
-11.000 -0.7712 0.02517 0.02074 -0.0632 0.9762 0.0183
-10.750 -0.7417 0.02421 0.01964 -0.0644 0.9689 0.0189
-10.500 -0.7115 0.02309 0.01834 -0.0657 0.9615 0.0196
-10.250 -0.6828 0.02193 0.01695 -0.0667 0.9526 0.0202
-10.000 -0.6497 0.02110 0.01599 -0.0683 0.9429 0.0208
-9.750 -0.6172 0.02048 0.01531 -0.0697 0.9298 0.0213
-9.500 -0.5853 0.02006 0.01482 -0.0708 0.9126 0.0218
-9.250 -0.5582 0.01952 0.01415 -0.0709 0.8916 0.0224
-9.000 -0.5339 0.01896 0.01342 -0.0703 0.8673 0.0229
-8.750 -0.5112 0.01850 0.01276 -0.0693 0.8424 0.0236
-8.500 -0.4893 0.01809 0.01214 -0.0681 0.8170 0.0243
-8.250 -0.4674 0.01771 0.01155 -0.0669 0.7921 0.0247
-8.000 -0.4461 0.01726 0.01090 -0.0656 0.7667 0.0251
-7.750 -0.4260 0.01658 0.01007 -0.0643 0.7401 0.0257
-7.500 -0.4041 0.01627 0.00963 -0.0631 0.7141 0.0263
-7.250 -0.3817 0.01596 0.00919 -0.0620 0.6893 0.0269
-7.000 -0.3591 0.01565 0.00873 -0.0609 0.6652 0.0274
-6.750 -0.3365 0.01533 0.00826 -0.0598 0.6398 0.0279
-6.500 -0.3134 0.01508 0.00786 -0.0588 0.6142 0.0286
-6.250 -0.2903 0.01482 0.00743 -0.0578 0.5885 0.0292
-6.000 -0.2669 0.01455 0.00701 -0.0569 0.5647 0.0297
-5.750 -0.2433 0.01431 0.00662 -0.0560 0.5424 0.0301
-5.500 -0.2195 0.01409 0.00627 -0.0551 0.5215 0.0304
-5.250 -0.1969 0.01368 0.00574 -0.0540 0.5022 0.0311
-5.000 -0.1736 0.01339 0.00537 -0.0531 0.4845 0.0318
-4.750 -0.1495 0.01319 0.00508 -0.0523 0.4695 0.0326
-4.500 -0.1250 0.01300 0.00481 -0.0516 0.4574 0.0332
-4.250 -0.1001 0.01281 0.00455 -0.0509 0.4471 0.0338
-4.000 -0.0751 0.01264 0.00430 -0.0502 0.4384 0.0345
-3.750 -0.0499 0.01249 0.00408 -0.0496 0.4296 0.0352
-3.500 -0.0246 0.01235 0.00388 -0.0489 0.4217 0.0359
-3.250 0.0010 0.01224 0.00370 -0.0484 0.4145 0.0366
-3.000 0.0262 0.01211 0.00351 -0.0477 0.4083 0.0379
-2.750 0.0519 0.01196 0.00334 -0.0472 0.4027 0.0397
-2.500 0.0777 0.01186 0.00321 -0.0467 0.3972 0.0417
-2.250 0.1034 0.01179 0.00309 -0.0461 0.3922 0.0439
-2.000 0.1294 0.01168 0.00299 -0.0456 0.3873 0.0493
-1.750 0.1550 0.01157 0.00291 -0.0451 0.3820 0.0624
-1.250 0.2059 0.01136 0.00277 -0.0440 0.3730 0.1015
-1.000 0.2307 0.01116 0.00272 -0.0434 0.3689 0.1459
-0.750 0.2552 0.01099 0.00269 -0.0428 0.3648 0.2000
-0.250 0.3031 0.01057 0.00264 -0.0413 0.3577 0.3310
0.000 0.3258 0.01027 0.00263 -0.0404 0.3539 0.4258
0.250 0.3448 0.00982 0.00262 -0.0387 0.3502 0.5679
0.500 0.3610 0.00940 0.00268 -0.0362 0.3468 0.7141
0.750 0.3808 0.00916 0.00280 -0.0341 0.3438 0.8243
1.000 0.4103 0.00914 0.00292 -0.0341 0.3407 0.8845
1.250 0.4482 0.00924 0.00305 -0.0360 0.3371 0.9183
1.500 0.4898 0.00942 0.00318 -0.0388 0.3334 0.9419
1.750 0.5301 0.00961 0.00330 -0.0413 0.3298 0.9532
2.000 0.5660 0.00974 0.00340 -0.0430 0.3267 0.9612
2.250 0.6033 0.00989 0.00351 -0.0449 0.3232 0.9680
2.500 0.6394 0.01004 0.00362 -0.0467 0.3201 0.9742
2.750 0.6759 0.01020 0.00373 -0.0485 0.3170 0.9785
3.000 0.7064 0.01036 0.00383 -0.0492 0.3140 0.9828
3.250 0.7402 0.01047 0.00393 -0.0506 0.3114 0.9852
3.500 0.7742 0.01058 0.00402 -0.0520 0.3083 0.9877
3.750 0.8072 0.01070 0.00412 -0.0532 0.3055 0.9906
4.000 0.8391 0.01085 0.00425 -0.0542 0.3028 0.9936
4.250 0.8724 0.01100 0.00436 -0.0556 0.3000 0.9959
4.500 0.9057 0.01115 0.00449 -0.0569 0.2973 0.9983
4.750 0.9384 0.01126 0.00462 -0.0581 0.2947 1.0000
5.000 0.9591 0.01138 0.00474 -0.0568 0.2924 1.0000
5.250 0.9797 0.01152 0.00488 -0.0555 0.2899 1.0000
5.500 1.0000 0.01166 0.00502 -0.0541 0.2873 1.0000
5.750 1.0200 0.01184 0.00517 -0.0527 0.2847 1.0000
6.000 1.0406 0.01200 0.00534 -0.0514 0.2821 1.0000
6.250 1.0620 0.01212 0.00549 -0.0502 0.2789 1.0000
6.500 1.0830 0.01227 0.00565 -0.0490 0.2748 1.0000
6.750 1.1031 0.01246 0.00582 -0.0477 0.2708 1.0000
7.000 1.1234 0.01265 0.00601 -0.0464 0.2669 1.0000
7.250 1.1447 0.01280 0.00618 -0.0452 0.2619 1.0000
7.500 1.1648 0.01300 0.00638 -0.0439 0.2572 1.0000
7.750 1.1843 0.01323 0.00660 -0.0425 0.2531 1.0000
8.000 1.2052 0.01341 0.00681 -0.0413 0.2474 1.0000
8.250 1.2238 0.01367 0.00704 -0.0398 0.2407 1.0000
8.500 1.2435 0.01390 0.00729 -0.0385 0.2345 1.0000
8.750 1.2614 0.01419 0.00757 -0.0369 0.2271 1.0000
9.000 1.2791 0.01449 0.00787 -0.0353 0.2187 1.0000
9.250 1.2946 0.01487 0.00821 -0.0334 0.2090 1.0000
9.500 1.3058 0.01533 0.00861 -0.0307 0.1958 1.0000
9.750 1.3123 0.01598 0.00916 -0.0273 0.1765 1.0000
10.000 1.3157 0.01684 0.00990 -0.0237 0.1561 1.0000
10.250 1.3165 0.01791 0.01084 -0.0200 0.1341 1.0000
10.500 1.3165 0.01910 0.01193 -0.0165 0.1146 1.0000
10.750 1.3129 0.02058 0.01330 -0.0129 0.0947 1.0000
11.000 1.2892 0.02340 0.01592 -0.0081 0.0516 1.0000
11.250 1.2707 0.02641 0.01889 -0.0049 0.0230 1.0000
11.500 1.2719 0.02829 0.02083 -0.0036 0.0186 1.0000
11.750 1.2753 0.03016 0.02278 -0.0028 0.0169 1.0000
12.000 1.2776 0.03227 0.02498 -0.0022 0.0157 1.0000
12.250 1.2790 0.03462 0.02742 -0.0019 0.0149 1.0000
12.500 1.2803 0.03712 0.03003 -0.0019 0.0143 1.0000
12.750 1.2797 0.03994 0.03295 -0.0021 0.0137 1.0000
13.000 1.2756 0.04329 0.03641 -0.0025 0.0132 1.0000
13.250 1.2703 0.04689 0.04011 -0.0031 0.0129 1.0000
13.500 1.2622 0.05090 0.04424 -0.0038 0.0126 1.0000
13.750 1.2536 0.05503 0.04849 -0.0047 0.0124 1.0000
14.000 1.2414 0.05971 0.05328 -0.0057 0.0121 1.0000
14.250 1.2274 0.06463 0.05832 -0.0068 0.0118 1.0000
14.500 1.2193 0.06884 0.06264 -0.0077 0.0115 1.0000
14.750 1.2073 0.07363 0.06753 -0.0089 0.0116 1.0000
15.000 1.1966 0.07829 0.07230 -0.0100 0.0115 1.0000
15.250 1.1884 0.08268 0.07678 -0.0111 0.0112 1.0000
15.500 1.1794 0.08726 0.08145 -0.0124 0.0109 1.0000
15.750 1.1714 0.09170 0.08599 -0.0135 0.0108 1.0000
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