USA 45 M AIRFOIL (usa45m-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: USA 45 M AIRFOIL (usa45m-il) Reynolds number: 200,000 Max Cl/Cd: 66.28 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa45m-il-200000-n5.txt Download as CSV file: xf-usa45m-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4125 0.07607 0.07264 -0.0397 1.0000 0.0331
-8.500 -0.4173 0.07311 0.06972 -0.0398 1.0000 0.0328
-8.250 -0.4281 0.06957 0.06620 -0.0398 1.0000 0.0326
-8.000 -0.4365 0.06566 0.06228 -0.0401 1.0000 0.0323
-7.750 -0.4461 0.06149 0.05806 -0.0398 1.0000 0.0322
-7.500 -0.4513 0.05716 0.05362 -0.0397 0.9986 0.0322
-7.250 -0.4408 0.04829 0.04405 -0.0454 0.9839 0.0335
-7.000 -0.4219 0.04361 0.03906 -0.0476 0.9733 0.0336
-6.750 -0.4018 0.03949 0.03462 -0.0491 0.9620 0.0337
-6.500 -0.3793 0.03615 0.03101 -0.0503 0.9499 0.0340
-6.250 -0.3515 0.03441 0.02920 -0.0517 0.9375 0.0348
-6.000 -0.3232 0.03270 0.02734 -0.0529 0.9237 0.0357
-5.500 -0.2697 0.02808 0.02206 -0.0540 0.8887 0.0365
-5.250 -0.2428 0.02608 0.01970 -0.0541 0.8684 0.0367
-5.000 -0.2172 0.02441 0.01770 -0.0537 0.8450 0.0370
-4.750 -0.1917 0.02299 0.01594 -0.0531 0.8202 0.0373
-4.500 -0.1670 0.02193 0.01458 -0.0523 0.7932 0.0382
-4.250 -0.1425 0.02100 0.01334 -0.0514 0.7657 0.0391
-4.000 -0.1181 0.02005 0.01208 -0.0505 0.7373 0.0395
-3.750 -0.0937 0.01919 0.01092 -0.0495 0.7082 0.0398
-3.500 -0.0693 0.01847 0.00992 -0.0485 0.6790 0.0402
-3.250 -0.0446 0.01784 0.00905 -0.0476 0.6510 0.0405
-3.000 -0.0199 0.01730 0.00828 -0.0468 0.6239 0.0410
-2.750 0.0048 0.01686 0.00763 -0.0460 0.5976 0.0414
-2.500 0.0296 0.01647 0.00706 -0.0452 0.5732 0.0418
-2.250 0.0537 0.01584 0.00633 -0.0444 0.5521 0.0429
-2.000 0.0781 0.01546 0.00589 -0.0437 0.5332 0.0444
-1.750 0.1027 0.01518 0.00552 -0.0430 0.5162 0.0455
-1.500 0.1272 0.01490 0.00515 -0.0423 0.5011 0.0464
-1.250 0.1517 0.01465 0.00482 -0.0415 0.4880 0.0474
-1.000 0.1763 0.01443 0.00453 -0.0408 0.4766 0.0487
-0.750 0.2013 0.01425 0.00427 -0.0402 0.4666 0.0501
-0.500 0.2264 0.01414 0.00406 -0.0396 0.4574 0.0516
-0.250 0.2517 0.01400 0.00384 -0.0390 0.4483 0.0536
0.000 0.2770 0.01389 0.00368 -0.0384 0.4406 0.0580
0.250 0.3029 0.01384 0.00357 -0.0380 0.4333 0.0638
0.500 0.3282 0.01376 0.00344 -0.0374 0.4270 0.0740
0.750 0.3478 0.01283 0.00337 -0.0362 0.4207 0.3359
1.000 0.3872 0.01136 0.00370 -0.0378 0.4137 0.9160
1.250 0.4752 0.01163 0.00384 -0.0499 0.4040 0.9900
1.500 0.5219 0.01177 0.00383 -0.0540 0.3977 1.0000
1.750 0.5446 0.01188 0.00388 -0.0530 0.3924 1.0000
2.000 0.5673 0.01200 0.00394 -0.0520 0.3869 1.0000
2.250 0.5898 0.01215 0.00400 -0.0510 0.3824 1.0000
2.500 0.6128 0.01229 0.00410 -0.0501 0.3778 1.0000
2.750 0.6359 0.01242 0.00420 -0.0491 0.3727 1.0000
3.000 0.6587 0.01259 0.00431 -0.0482 0.3680 1.0000
3.250 0.6817 0.01277 0.00443 -0.0472 0.3637 1.0000
3.500 0.7051 0.01291 0.00458 -0.0464 0.3588 1.0000
3.750 0.7282 0.01308 0.00472 -0.0454 0.3540 1.0000
4.000 0.7510 0.01330 0.00487 -0.0445 0.3499 1.0000
4.250 0.7746 0.01345 0.00506 -0.0437 0.3448 1.0000
4.500 0.7978 0.01363 0.00524 -0.0428 0.3397 1.0000
4.750 0.8207 0.01384 0.00541 -0.0419 0.3354 1.0000
5.000 0.8442 0.01402 0.00563 -0.0411 0.3302 1.0000
5.250 0.8674 0.01421 0.00583 -0.0402 0.3248 1.0000
5.500 0.8900 0.01444 0.00603 -0.0393 0.3199 1.0000
5.750 0.9134 0.01462 0.00628 -0.0385 0.3142 1.0000
6.000 0.9363 0.01483 0.00651 -0.0376 0.3087 1.0000
6.250 0.9588 0.01508 0.00675 -0.0367 0.3042 1.0000
6.500 0.9823 0.01529 0.00705 -0.0359 0.2989 1.0000
6.750 1.0051 0.01553 0.00734 -0.0350 0.2939 1.0000
7.000 1.0273 0.01578 0.00759 -0.0341 0.2877 1.0000
7.250 1.0495 0.01598 0.00786 -0.0331 0.2782 1.0000
7.500 1.0712 0.01621 0.00812 -0.0321 0.2682 1.0000
7.750 1.0923 0.01649 0.00840 -0.0311 0.2578 1.0000
8.000 1.1128 0.01679 0.00871 -0.0300 0.2456 1.0000
8.250 1.1338 0.01711 0.00907 -0.0289 0.2333 1.0000
8.500 1.1534 0.01750 0.00946 -0.0277 0.2190 1.0000
8.750 1.1715 0.01800 0.00991 -0.0264 0.2008 1.0000
9.000 1.1875 0.01863 0.01046 -0.0248 0.1789 1.0000
9.250 1.1996 0.01953 0.01122 -0.0227 0.1512 1.0000
9.500 1.2078 0.02068 0.01218 -0.0202 0.1207 1.0000
9.750 1.2009 0.02269 0.01378 -0.0159 0.0550 1.0000
10.000 1.1900 0.02455 0.01549 -0.0109 0.0305 1.0000
10.250 1.1930 0.02573 0.01673 -0.0079 0.0261 1.0000
10.500 1.1960 0.02700 0.01809 -0.0053 0.0239 1.0000
10.750 1.2006 0.02827 0.01948 -0.0032 0.0223 1.0000
11.000 1.2043 0.02969 0.02105 -0.0014 0.0214 1.0000
11.250 1.2063 0.03136 0.02286 0.0002 0.0206 1.0000
11.500 1.2058 0.03341 0.02505 0.0015 0.0199 1.0000
11.750 1.2025 0.03593 0.02771 0.0023 0.0193 1.0000
12.000 1.1943 0.03923 0.03117 0.0025 0.0186 1.0000
12.250 1.1886 0.04259 0.03468 0.0021 0.0182 1.0000
12.500 1.1814 0.04638 0.03863 0.0013 0.0180 1.0000
12.750 1.1745 0.05036 0.04276 0.0003 0.0177 1.0000
13.000 1.1668 0.05458 0.04712 -0.0010 0.0172 1.0000
13.250 1.1572 0.05914 0.05183 -0.0025 0.0169 1.0000
13.500 1.1457 0.06404 0.05687 -0.0041 0.0169 1.0000
13.750 1.1340 0.06900 0.06196 -0.0058 0.0165 1.0000
14.000 1.1227 0.07401 0.06709 -0.0075 0.0164 1.0000
14.250 1.1111 0.07916 0.07235 -0.0093 0.0163 1.0000
14.500 1.1003 0.08432 0.07763 -0.0112 0.0161 1.0000
14.750 1.0919 0.08919 0.08260 -0.0130 0.0160 1.0000
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Polar data table (+)
Polar graphs
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