USA 46 AIRFOIL (usa46-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 46 AIRFOIL (usa46-il) Reynolds number: 500,000 Max Cl/Cd: 86.39 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa46-il-500000.txt Download as CSV file: xf-usa46-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: USA 46 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5418 0.06789 0.06579 -0.0256 1.0000 0.0168
-7.750 -0.5931 0.02848 0.02525 -0.0570 1.0000 0.0122
-7.500 -0.5766 0.02440 0.02067 -0.0578 1.0000 0.0124
-7.250 -0.5537 0.02386 0.02005 -0.0575 1.0000 0.0134
-7.000 -0.5330 0.02146 0.01729 -0.0573 1.0000 0.0142
-6.750 -0.5119 0.01880 0.01421 -0.0569 1.0000 0.0147
-6.500 -0.4893 0.01699 0.01208 -0.0563 1.0000 0.0154
-6.250 -0.4657 0.01585 0.01070 -0.0556 1.0000 0.0160
-6.000 -0.4438 0.01353 0.00804 -0.0549 1.0000 0.0173
-5.750 -0.4201 0.01274 0.00717 -0.0542 1.0000 0.0190
-5.500 -0.3959 0.01241 0.00678 -0.0535 1.0000 0.0213
-5.250 -0.3716 0.01204 0.00632 -0.0527 1.0000 0.0232
-5.000 -0.3483 0.01091 0.00510 -0.0519 1.0000 0.0274
-4.750 -0.3242 0.01064 0.00478 -0.0511 1.0000 0.0318
-4.500 -0.3007 0.01014 0.00427 -0.0504 1.0000 0.0389
-4.250 -0.2772 0.01007 0.00413 -0.0495 1.0000 0.0436
-4.000 -0.2541 0.00954 0.00360 -0.0487 1.0000 0.0502
-3.750 -0.2238 0.00942 0.00343 -0.0493 0.9986 0.0557
-3.500 -0.1870 0.00901 0.00304 -0.0513 0.9955 0.0647
-3.250 -0.1509 0.00870 0.00271 -0.0531 0.9920 0.0751
-3.000 -0.1152 0.00836 0.00244 -0.0548 0.9880 0.0917
-2.750 -0.0771 0.00811 0.00231 -0.0570 0.9842 0.1237
-2.500 -0.0403 0.00795 0.00219 -0.0589 0.9782 0.1471
-2.250 -0.0017 0.00781 0.00205 -0.0611 0.9724 0.1636
-2.000 0.0349 0.00762 0.00190 -0.0628 0.9659 0.1766
-1.750 0.0712 0.00742 0.00173 -0.0645 0.9579 0.1888
-1.500 0.1060 0.00723 0.00158 -0.0659 0.9470 0.2036
-1.250 0.1408 0.00702 0.00143 -0.0672 0.9342 0.2232
-1.000 0.1736 0.00674 0.00131 -0.0682 0.9182 0.2669
-0.750 0.2018 0.00610 0.00124 -0.0684 0.8995 0.4612
-0.500 0.2251 0.00553 0.00132 -0.0673 0.8795 0.6744
-0.250 0.2496 0.00542 0.00136 -0.0661 0.8603 0.7621
0.000 0.2747 0.00538 0.00135 -0.0651 0.8407 0.8011
0.250 0.2993 0.00529 0.00131 -0.0641 0.8203 0.8362
0.500 0.3274 0.00507 0.00126 -0.0636 0.7990 0.9109
0.750 0.3667 0.00512 0.00123 -0.0659 0.7737 1.0000
1.000 0.3927 0.00525 0.00123 -0.0653 0.7460 1.0000
1.250 0.4185 0.00541 0.00126 -0.0647 0.7161 1.0000
1.500 0.4445 0.00557 0.00129 -0.0641 0.6862 1.0000
1.750 0.4706 0.00574 0.00135 -0.0636 0.6576 1.0000
2.000 0.4965 0.00593 0.00141 -0.0630 0.6267 1.0000
2.250 0.5219 0.00617 0.00151 -0.0624 0.5907 1.0000
2.500 0.5477 0.00640 0.00161 -0.0619 0.5575 1.0000
2.750 0.5736 0.00664 0.00173 -0.0614 0.5253 1.0000
3.000 0.5986 0.00695 0.00186 -0.0608 0.4763 1.0000
3.250 0.6231 0.00736 0.00201 -0.0602 0.4051 1.0000
3.500 0.6477 0.00781 0.00221 -0.0596 0.3491 1.0000
3.750 0.6726 0.00826 0.00245 -0.0591 0.3037 1.0000
4.000 0.6977 0.00868 0.00270 -0.0586 0.2594 1.0000
4.250 0.7206 0.00947 0.00305 -0.0579 0.1583 1.0000
4.500 0.7397 0.01104 0.00393 -0.0567 0.0293 1.0000
4.750 0.7648 0.01159 0.00449 -0.0561 0.0223 1.0000
5.000 0.7895 0.01223 0.00523 -0.0553 0.0201 1.0000
5.250 0.8141 0.01284 0.00593 -0.0546 0.0186 1.0000
5.500 0.8379 0.01358 0.00676 -0.0537 0.0174 1.0000
5.750 0.8614 0.01434 0.00756 -0.0529 0.0159 1.0000
6.000 0.8820 0.01567 0.00897 -0.0517 0.0146 1.0000
6.250 0.9001 0.01800 0.01143 -0.0500 0.0139 1.0000
6.500 0.9245 0.01878 0.01231 -0.0492 0.0135 1.0000
6.750 0.9476 0.02012 0.01379 -0.0482 0.0132 1.0000
7.000 0.9700 0.02205 0.01591 -0.0471 0.0131 1.0000
7.250 0.9907 0.02504 0.01917 -0.0457 0.0134 1.0000
7.500 1.0150 0.02663 0.02087 -0.0447 0.0148 1.0000
7.750 1.0334 0.03363 0.02866 -0.0413 0.0229 1.0000
8.000 1.0470 0.03760 0.03278 -0.0404 0.0216 1.0000
8.250 1.0520 0.04088 0.03668 -0.0377 0.0194 1.0000
8.500 1.0650 0.04321 0.03931 -0.0360 0.0179 1.0000
8.750 1.0731 0.04611 0.04248 -0.0343 0.0168 1.0000
9.000 1.0783 0.04911 0.04569 -0.0328 0.0161 1.0000
9.250 1.0814 0.05205 0.04879 -0.0313 0.0156 1.0000
9.500 1.0826 0.05500 0.05187 -0.0300 0.0152 1.0000
9.750 1.0803 0.05819 0.05517 -0.0286 0.0149 1.0000
10.000 1.0667 0.06151 0.05865 -0.0263 0.0148 1.0000
10.250 1.0476 0.06486 0.06213 -0.0244 0.0147 1.0000
10.500 1.0274 0.06895 0.06636 -0.0247 0.0147 1.0000
10.750 1.0065 0.07418 0.07174 -0.0273 0.0147 1.0000
11.000 0.9607 0.08718 0.08503 -0.0388 0.0154 1.0000
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