USA 45 AIRFOIL (usa45-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 45 AIRFOIL (usa45-il) Reynolds number: 100,000 Max Cl/Cd: 42.27 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa45-il-100000-n5.txt Download as CSV file: xf-usa45-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3298 0.09168 0.08696 -0.0412 1.0000 0.0433
-9.750 -0.3366 0.08726 0.08261 -0.0426 1.0000 0.0431
-9.500 -0.3467 0.08253 0.07796 -0.0444 1.0000 0.0430
-9.250 -0.3618 0.07730 0.07282 -0.0468 1.0000 0.0430
-9.000 -0.3850 0.07157 0.06719 -0.0499 1.0000 0.0427
-8.750 -0.4159 0.06755 0.06323 -0.0489 1.0000 0.0422
-8.500 -0.4439 0.06316 0.05881 -0.0477 0.9970 0.0422
-8.250 -0.4521 0.05432 0.04952 -0.0537 0.9779 0.0429
-8.000 -0.4504 0.04765 0.04227 -0.0564 0.9620 0.0436
-7.750 -0.4405 0.04245 0.03644 -0.0575 0.9476 0.0441
-7.500 -0.4223 0.03895 0.03252 -0.0582 0.9339 0.0452
-7.250 -0.3954 0.03724 0.03072 -0.0593 0.9205 0.0465
-7.000 -0.3700 0.03522 0.02844 -0.0598 0.9056 0.0480
-6.750 -0.3464 0.03278 0.02558 -0.0598 0.8898 0.0490
-6.500 -0.3215 0.03059 0.02296 -0.0597 0.8731 0.0500
-6.250 -0.2955 0.02880 0.02072 -0.0594 0.8551 0.0520
-6.000 -0.2683 0.02725 0.01871 -0.0591 0.8359 0.0534
-5.750 -0.2395 0.02576 0.01708 -0.0593 0.8158 0.0546
-5.500 -0.2126 0.02466 0.01579 -0.0589 0.7927 0.0557
-5.250 -0.1852 0.02367 0.01460 -0.0585 0.7691 0.0571
-5.000 -0.1588 0.02289 0.01360 -0.0579 0.7440 0.0592
-4.750 -0.1325 0.02217 0.01262 -0.0572 0.7188 0.0618
-4.500 -0.1068 0.02150 0.01171 -0.0564 0.6930 0.0635
-4.250 -0.0825 0.02075 0.01087 -0.0556 0.6687 0.0654
-4.000 -0.0588 0.02022 0.01022 -0.0546 0.6441 0.0677
-3.750 -0.0353 0.01977 0.00960 -0.0535 0.6216 0.0707
-3.500 -0.0118 0.01942 0.00905 -0.0524 0.6003 0.0749
-3.250 0.0105 0.01899 0.00856 -0.0513 0.5808 0.0807
-3.000 0.0337 0.01869 0.00809 -0.0502 0.5632 0.0884
-2.750 0.0561 0.01829 0.00764 -0.0490 0.5477 0.1001
-2.500 0.0789 0.01791 0.00727 -0.0480 0.5339 0.1220
-2.250 0.1013 0.01751 0.00703 -0.0469 0.5217 0.1744
-2.000 0.1234 0.01708 0.00683 -0.0460 0.5099 0.2547
-1.750 0.1432 0.01642 0.00671 -0.0446 0.4998 0.4008
-1.500 0.1630 0.01547 0.00689 -0.0423 0.4911 0.6889
-1.250 0.2133 0.01561 0.00725 -0.0451 0.4800 0.8479
-1.000 0.2606 0.01597 0.00740 -0.0479 0.4707 0.9027
-0.750 0.3142 0.01636 0.00754 -0.0522 0.4609 0.9391
-0.500 0.3586 0.01660 0.00754 -0.0553 0.4528 0.9562
-0.250 0.4075 0.01683 0.00753 -0.0594 0.4450 0.9729
0.000 0.4657 0.01698 0.00745 -0.0656 0.4377 0.9898
0.250 0.5114 0.01707 0.00736 -0.0695 0.4305 1.0000
0.500 0.5316 0.01721 0.00734 -0.0683 0.4260 1.0000
0.750 0.5518 0.01736 0.00741 -0.0671 0.4209 1.0000
1.000 0.5720 0.01752 0.00749 -0.0659 0.4160 1.0000
1.250 0.5926 0.01771 0.00756 -0.0648 0.4119 1.0000
1.500 0.6134 0.01793 0.00765 -0.0636 0.4083 1.0000
1.750 0.6337 0.01814 0.00784 -0.0624 0.4037 1.0000
2.000 0.6542 0.01836 0.00801 -0.0612 0.3993 1.0000
2.250 0.6751 0.01860 0.00814 -0.0600 0.3955 1.0000
2.500 0.6964 0.01887 0.00831 -0.0590 0.3921 1.0000
2.750 0.7167 0.01914 0.00860 -0.0577 0.3880 1.0000
3.000 0.7376 0.01943 0.00887 -0.0566 0.3842 1.0000
3.250 0.7588 0.01971 0.00910 -0.0555 0.3808 1.0000
3.500 0.7807 0.02001 0.00931 -0.0545 0.3777 1.0000
3.750 0.8014 0.02034 0.00964 -0.0533 0.3742 1.0000
4.000 0.8217 0.02068 0.01002 -0.0521 0.3703 1.0000
4.250 0.8427 0.02101 0.01035 -0.0510 0.3668 1.0000
4.500 0.8644 0.02135 0.01065 -0.0500 0.3639 1.0000
4.750 0.8871 0.02169 0.01093 -0.0491 0.3612 1.0000
5.000 0.9069 0.02210 0.01140 -0.0479 0.3577 1.0000
5.250 0.9266 0.02252 0.01188 -0.0466 0.3540 1.0000
5.500 0.9473 0.02290 0.01231 -0.0455 0.3507 1.0000
5.750 0.9691 0.02328 0.01267 -0.0446 0.3479 1.0000
6.000 0.9920 0.02365 0.01299 -0.0438 0.3454 1.0000
6.250 1.0107 0.02414 0.01359 -0.0425 0.3420 1.0000
6.500 1.0289 0.02464 0.01421 -0.0411 0.3383 1.0000
6.750 1.0486 0.02509 0.01472 -0.0399 0.3350 1.0000
7.000 1.0699 0.02549 0.01512 -0.0390 0.3321 1.0000
7.250 1.0932 0.02586 0.01547 -0.0383 0.3296 1.0000
7.500 1.1094 0.02646 0.01623 -0.0367 0.3260 1.0000
7.750 1.1255 0.02704 0.01696 -0.0351 0.3222 1.0000
8.000 1.1442 0.02753 0.01751 -0.0339 0.3188 1.0000
8.250 1.1656 0.02788 0.01789 -0.0330 0.3157 1.0000
8.500 1.1873 0.02829 0.01830 -0.0322 0.3128 1.0000
8.750 1.1973 0.02907 0.01932 -0.0299 0.3085 1.0000
9.000 1.2120 0.02964 0.02002 -0.0281 0.3046 1.0000
9.250 1.2313 0.02999 0.02041 -0.0270 0.3011 1.0000
9.500 1.2552 0.03025 0.02064 -0.0265 0.2982 1.0000
9.750 1.2579 0.03125 0.02192 -0.0234 0.2936 1.0000
10.000 1.2677 0.03193 0.02274 -0.0211 0.2895 1.0000
10.250 1.2859 0.03199 0.02281 -0.0198 0.2849 1.0000
10.500 1.2895 0.03263 0.02357 -0.0166 0.2799 1.0000
10.750 1.2879 0.03336 0.02445 -0.0129 0.2743 1.0000
11.000 1.3018 0.03328 0.02431 -0.0110 0.2686 1.0000
11.250 1.2928 0.03472 0.02598 -0.0074 0.2632 1.0000
11.500 1.2932 0.03569 0.02705 -0.0049 0.2574 1.0000
11.750 1.2967 0.03660 0.02802 -0.0030 0.2521 1.0000
12.000 1.2857 0.03884 0.03047 -0.0009 0.2465 1.0000
12.250 1.2869 0.04016 0.03182 0.0005 0.2403 1.0000
12.500 1.2714 0.04338 0.03524 0.0016 0.2350 1.0000
12.750 1.2562 0.04699 0.03901 0.0020 0.2302 1.0000
13.000 1.2521 0.04957 0.04162 0.0022 0.2247 1.0000
13.250 1.2114 0.05704 0.04933 0.0007 0.2212 1.0000
13.500 1.1489 0.06833 0.06082 -0.0025 0.2173 1.0000
13.750 1.1726 0.06766 0.06011 -0.0019 0.2112 1.0000
14.000 1.0130 0.09574 0.08839 -0.0113 0.2036 1.0000
14.250 1.0697 0.08931 0.08201 -0.0088 0.2000 1.0000
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Polar data table (+)
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