USA 45 AIRFOIL (usa45-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 45 AIRFOIL (usa45-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.91 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa45-il-1000000.txt Download as CSV file: xf-usa45-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.2583 0.14732 0.14575 -0.0210 1.0000 0.0152
-15.000 -0.2553 0.14579 0.14423 -0.0220 1.0000 0.0155
-14.750 -0.9293 0.04003 0.03728 -0.0799 1.0000 0.0151
-14.500 -0.9075 0.03995 0.03727 -0.0797 1.0000 0.0154
-14.250 -0.9055 0.03780 0.03506 -0.0804 1.0000 0.0155
-14.000 -0.9218 0.03443 0.03153 -0.0801 1.0000 0.0156
-13.750 -0.9145 0.03347 0.03053 -0.0789 1.0000 0.0158
-13.500 -0.9121 0.03232 0.02932 -0.0770 1.0000 0.0159
-13.250 -0.9121 0.03125 0.02818 -0.0743 1.0000 0.0161
-13.000 -0.9209 0.03002 0.02684 -0.0699 1.0000 0.0163
-12.750 -0.9283 0.02909 0.02582 -0.0649 1.0000 0.0164
-12.500 -0.9257 0.02827 0.02492 -0.0613 1.0000 0.0167
-12.250 -0.9262 0.02732 0.02386 -0.0572 1.0000 0.0169
-12.000 -0.9239 0.02659 0.02304 -0.0534 1.0000 0.0171
-11.750 -0.8924 0.02553 0.02183 -0.0552 0.9979 0.0175
-11.500 -0.8645 0.02378 0.01986 -0.0568 0.9946 0.0179
-11.250 -0.8379 0.02254 0.01856 -0.0577 0.9909 0.0184
-11.000 -0.8070 0.02203 0.01803 -0.0588 0.9875 0.0187
-10.750 -0.7725 0.02188 0.01789 -0.0603 0.9847 0.0191
-10.500 -0.7402 0.02125 0.01719 -0.0617 0.9820 0.0195
-10.250 -0.7119 0.02081 0.01669 -0.0621 0.9756 0.0201
-10.000 -0.6796 0.02003 0.01581 -0.0634 0.9715 0.0206
-9.750 -0.6467 0.01943 0.01509 -0.0647 0.9661 0.0211
-9.500 -0.6121 0.01905 0.01460 -0.0662 0.9582 0.0214
-9.250 -0.5845 0.01718 0.01259 -0.0672 0.9469 0.0222
-9.000 -0.5528 0.01673 0.01210 -0.0682 0.9335 0.0227
-8.750 -0.5243 0.01644 0.01173 -0.0683 0.9150 0.0232
-8.500 -0.4992 0.01609 0.01127 -0.0678 0.8930 0.0238
-8.250 -0.4761 0.01574 0.01079 -0.0667 0.8689 0.0243
-8.000 -0.4538 0.01539 0.01028 -0.0655 0.8445 0.0249
-7.750 -0.4314 0.01506 0.00979 -0.0643 0.8204 0.0253
-7.500 -0.4085 0.01495 0.00951 -0.0631 0.7946 0.0256
-7.250 -0.3890 0.01389 0.00828 -0.0616 0.7691 0.0264
-7.000 -0.3674 0.01345 0.00773 -0.0603 0.7423 0.0270
-6.750 -0.3446 0.01318 0.00735 -0.0592 0.7154 0.0275
-6.500 -0.3214 0.01292 0.00697 -0.0582 0.6900 0.0280
-6.250 -0.2982 0.01268 0.00661 -0.0571 0.6638 0.0286
-6.000 -0.2745 0.01246 0.00626 -0.0562 0.6372 0.0292
-5.750 -0.2507 0.01231 0.00597 -0.0553 0.6093 0.0299
-5.500 -0.2269 0.01212 0.00565 -0.0543 0.5816 0.0303
-5.250 -0.2023 0.01199 0.00539 -0.0535 0.5550 0.0306
-5.000 -0.1797 0.01163 0.00489 -0.0524 0.5308 0.0312
-4.750 -0.1574 0.01121 0.00437 -0.0513 0.5089 0.0320
-4.500 -0.1333 0.01101 0.00408 -0.0504 0.4889 0.0328
-4.250 -0.1085 0.01088 0.00387 -0.0497 0.4715 0.0336
-4.000 -0.0835 0.01073 0.00364 -0.0490 0.4575 0.0343
-3.750 -0.0582 0.01060 0.00344 -0.0483 0.4461 0.0351
-3.500 -0.0327 0.01050 0.00326 -0.0477 0.4359 0.0358
-3.250 -0.0065 0.01039 0.00310 -0.0472 0.4279 0.0365
-3.000 0.0186 0.01023 0.00287 -0.0465 0.4198 0.0376
-2.750 0.0444 0.01007 0.00269 -0.0460 0.4135 0.0396
-2.500 0.0704 0.00998 0.00257 -0.0455 0.4067 0.0414
-2.250 0.0967 0.00991 0.00246 -0.0450 0.4004 0.0433
-2.000 0.1229 0.00979 0.00234 -0.0445 0.3949 0.0481
-1.750 0.1482 0.00966 0.00226 -0.0439 0.3894 0.0661
-1.500 0.1734 0.00948 0.00218 -0.0433 0.3846 0.1004
-1.250 0.1978 0.00921 0.00212 -0.0426 0.3803 0.1617
-1.000 0.2224 0.00902 0.00208 -0.0419 0.3757 0.2177
-0.750 0.2460 0.00882 0.00206 -0.0411 0.3705 0.2858
-0.500 0.2692 0.00848 0.00203 -0.0402 0.3675 0.3876
-0.250 0.2892 0.00800 0.00200 -0.0387 0.3634 0.5328
0.000 0.3081 0.00762 0.00200 -0.0368 0.3595 0.6641
0.250 0.3275 0.00741 0.00205 -0.0349 0.3552 0.7570
0.500 0.3492 0.00725 0.00212 -0.0333 0.3525 0.8285
0.750 0.3742 0.00719 0.00219 -0.0324 0.3493 0.8771
1.000 0.4030 0.00722 0.00227 -0.0323 0.3457 0.9135
1.250 0.4349 0.00733 0.00237 -0.0330 0.3417 0.9384
1.500 0.4712 0.00747 0.00249 -0.0347 0.3377 0.9526
1.750 0.5120 0.00760 0.00259 -0.0373 0.3346 0.9618
2.000 0.5478 0.00775 0.00271 -0.0389 0.3312 0.9702
2.250 0.5884 0.00792 0.00282 -0.0415 0.3276 0.9729
2.500 0.6262 0.00814 0.00296 -0.0436 0.3233 0.9765
2.750 0.6597 0.00824 0.00306 -0.0448 0.3212 0.9811
3.000 0.6987 0.00835 0.00315 -0.0471 0.3182 0.9836
3.250 0.7392 0.00848 0.00324 -0.0499 0.3150 0.9856
3.500 0.7755 0.00862 0.00333 -0.0518 0.3117 0.9878
3.750 0.8090 0.00878 0.00345 -0.0531 0.3078 0.9901
4.000 0.8423 0.00886 0.00353 -0.0543 0.3059 0.9924
4.250 0.8764 0.00894 0.00361 -0.0557 0.3034 0.9942
4.500 0.9119 0.00902 0.00367 -0.0575 0.3004 0.9956
4.750 0.9467 0.00914 0.00375 -0.0592 0.2971 0.9973
5.000 0.9806 0.00931 0.00389 -0.0607 0.2929 0.9990
5.250 1.0139 0.00935 0.00394 -0.0620 0.2904 1.0000
5.500 1.0351 0.00941 0.00402 -0.0608 0.2875 1.0000
5.750 1.0557 0.00951 0.00411 -0.0594 0.2842 1.0000
6.000 1.0755 0.00966 0.00423 -0.0580 0.2805 1.0000
6.250 1.0959 0.00979 0.00436 -0.0566 0.2770 1.0000
6.500 1.1177 0.00986 0.00444 -0.0555 0.2736 1.0000
6.750 1.1386 0.00998 0.00456 -0.0542 0.2703 1.0000
7.000 1.1588 0.01014 0.00471 -0.0528 0.2666 1.0000
7.250 1.1790 0.01031 0.00488 -0.0514 0.2629 1.0000
7.500 1.2010 0.01040 0.00500 -0.0504 0.2596 1.0000
7.750 1.2220 0.01055 0.00514 -0.0492 0.2549 1.0000
8.000 1.2416 0.01077 0.00533 -0.0478 0.2496 1.0000
8.250 1.2634 0.01090 0.00548 -0.0467 0.2445 1.0000
8.500 1.2836 0.01109 0.00566 -0.0454 0.2388 1.0000
8.750 1.3036 0.01131 0.00587 -0.0441 0.2319 1.0000
9.000 1.3226 0.01158 0.00610 -0.0426 0.2233 1.0000
9.250 1.3398 0.01193 0.00639 -0.0409 0.2095 1.0000
9.500 1.3522 0.01252 0.00683 -0.0384 0.1859 1.0000
9.750 1.3576 0.01344 0.00754 -0.0349 0.1558 1.0000
10.000 1.3536 0.01458 0.00845 -0.0297 0.1231 1.0000
10.500 1.3198 0.01801 0.01141 -0.0165 0.0427 1.0000
10.750 1.3122 0.01965 0.01301 -0.0122 0.0204 1.0000
11.000 1.3205 0.02058 0.01398 -0.0102 0.0179 1.0000
11.250 1.3283 0.02162 0.01506 -0.0084 0.0167 1.0000
11.500 1.3359 0.02275 0.01626 -0.0068 0.0156 1.0000
11.750 1.3442 0.02393 0.01750 -0.0055 0.0150 1.0000
12.000 1.3511 0.02531 0.01894 -0.0044 0.0145 1.0000
12.250 1.3554 0.02699 0.02070 -0.0034 0.0139 1.0000
12.500 1.3588 0.02890 0.02268 -0.0026 0.0135 1.0000
12.750 1.3552 0.03163 0.02552 -0.0020 0.0129 1.0000
13.000 1.3539 0.03435 0.02834 -0.0019 0.0127 1.0000
13.250 1.3555 0.03689 0.03097 -0.0020 0.0125 1.0000
13.500 1.3529 0.04003 0.03420 -0.0024 0.0122 1.0000
13.750 1.3477 0.04357 0.03785 -0.0029 0.0122 1.0000
14.000 1.3393 0.04761 0.04199 -0.0037 0.0119 1.0000
14.250 1.3323 0.05153 0.04601 -0.0045 0.0116 1.0000
14.500 1.3186 0.05636 0.05096 -0.0055 0.0116 1.0000
14.750 1.3069 0.06099 0.05568 -0.0066 0.0114 1.0000
15.000 1.2933 0.06589 0.06068 -0.0077 0.0112 1.0000
15.250 1.2782 0.07104 0.06595 -0.0089 0.0113 1.0000
15.500 1.2646 0.07608 0.07108 -0.0102 0.0112 1.0000
15.750 1.2508 0.08120 0.07629 -0.0115 0.0111 1.0000
16.000 1.2385 0.08620 0.08138 -0.0129 0.0110 1.0000
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