USA 45 AIRFOIL (usa45-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 45 AIRFOIL (usa45-il) Reynolds number: 200,000 Max Cl/Cd: 62.04 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa45-il-200000-n5.txt Download as CSV file: xf-usa45-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3515 0.08968 0.08625 -0.0403 1.0000 0.0263
-10.250 -0.3625 0.08423 0.08086 -0.0425 1.0000 0.0264
-10.000 -0.3756 0.07871 0.07539 -0.0449 1.0000 0.0268
-9.750 -0.5113 0.05365 0.05024 -0.0588 1.0000 0.0260
-9.500 -0.5325 0.04808 0.04443 -0.0596 0.9882 0.0263
-9.250 -0.5238 0.04413 0.04020 -0.0619 0.9750 0.0271
-9.000 -0.5201 0.03894 0.03451 -0.0634 0.9613 0.0282
-8.750 -0.5139 0.03394 0.02880 -0.0636 0.9472 0.0295
-8.500 -0.4993 0.03059 0.02474 -0.0633 0.9333 0.0304
-8.250 -0.4733 0.02889 0.02297 -0.0642 0.9205 0.0313
-8.000 -0.4448 0.02775 0.02170 -0.0650 0.9061 0.0322
-7.750 -0.4176 0.02644 0.02019 -0.0654 0.8893 0.0332
-7.500 -0.3916 0.02501 0.01845 -0.0655 0.8708 0.0342
-7.250 -0.3657 0.02367 0.01678 -0.0653 0.8501 0.0353
-7.000 -0.3409 0.02264 0.01539 -0.0647 0.8278 0.0364
-6.750 -0.3167 0.02157 0.01404 -0.0640 0.8041 0.0372
-6.500 -0.2927 0.02057 0.01288 -0.0632 0.7799 0.0379
-6.250 -0.2691 0.01986 0.01201 -0.0623 0.7542 0.0387
-6.000 -0.2456 0.01929 0.01126 -0.0614 0.7278 0.0396
-5.750 -0.2224 0.01881 0.01059 -0.0603 0.7017 0.0409
-5.500 -0.1991 0.01829 0.00988 -0.0593 0.6762 0.0420
-5.250 -0.1760 0.01780 0.00919 -0.0582 0.6508 0.0429
-5.000 -0.1530 0.01736 0.00855 -0.0570 0.6247 0.0436
-4.750 -0.1301 0.01699 0.00799 -0.0559 0.6004 0.0444
-4.500 -0.1080 0.01653 0.00742 -0.0547 0.5775 0.0454
-4.250 -0.0856 0.01621 0.00699 -0.0537 0.5567 0.0469
-4.000 -0.0625 0.01597 0.00664 -0.0526 0.5377 0.0487
-3.750 -0.0393 0.01575 0.00629 -0.0516 0.5202 0.0505
-3.500 -0.0160 0.01554 0.00594 -0.0507 0.5046 0.0522
-3.000 0.0311 0.01513 0.00535 -0.0488 0.4786 0.0575
-2.750 0.0553 0.01498 0.00510 -0.0480 0.4686 0.0621
-2.500 0.0791 0.01480 0.00489 -0.0471 0.4595 0.0707
-2.250 0.1033 0.01461 0.00470 -0.0463 0.4509 0.0866
-2.000 0.1266 0.01440 0.00453 -0.0455 0.4431 0.1139
-1.750 0.1498 0.01413 0.00442 -0.0446 0.4359 0.1646
-1.500 0.1731 0.01392 0.00433 -0.0438 0.4291 0.2188
-1.250 0.1953 0.01366 0.00425 -0.0428 0.4236 0.2869
-1.000 0.2144 0.01313 0.00421 -0.0413 0.4181 0.4214
-0.750 0.2280 0.01243 0.00424 -0.0384 0.4133 0.6162
-0.500 0.2508 0.01210 0.00446 -0.0365 0.4086 0.7916
-0.250 0.2949 0.01222 0.00470 -0.0391 0.4022 0.8798
0.000 0.3384 0.01246 0.00484 -0.0418 0.3962 0.9139
0.250 0.3816 0.01272 0.00496 -0.0447 0.3912 0.9350
0.500 0.4243 0.01292 0.00508 -0.0475 0.3861 0.9501
0.750 0.4662 0.01315 0.00518 -0.0502 0.3813 0.9625
1.000 0.5091 0.01340 0.00527 -0.0533 0.3769 0.9738
1.250 0.5531 0.01355 0.00537 -0.0566 0.3720 0.9833
1.500 0.5953 0.01366 0.00539 -0.0597 0.3671 0.9892
1.750 0.6303 0.01380 0.00544 -0.0614 0.3635 0.9940
2.000 0.6658 0.01394 0.00547 -0.0632 0.3602 0.9980
2.250 0.6949 0.01404 0.00555 -0.0637 0.3567 1.0000
2.500 0.7155 0.01416 0.00566 -0.0625 0.3534 1.0000
2.750 0.7359 0.01429 0.00575 -0.0612 0.3501 1.0000
3.000 0.7562 0.01446 0.00585 -0.0598 0.3471 1.0000
3.250 0.7766 0.01465 0.00597 -0.0586 0.3444 1.0000
3.500 0.7975 0.01480 0.00614 -0.0573 0.3416 1.0000
3.750 0.8184 0.01497 0.00632 -0.0561 0.3387 1.0000
4.000 0.8392 0.01515 0.00649 -0.0549 0.3356 1.0000
4.250 0.8600 0.01534 0.00665 -0.0536 0.3328 1.0000
4.500 0.8808 0.01556 0.00682 -0.0524 0.3302 1.0000
4.750 0.9020 0.01579 0.00703 -0.0512 0.3277 1.0000
5.000 0.9233 0.01599 0.00728 -0.0501 0.3250 1.0000
5.250 0.9445 0.01621 0.00752 -0.0489 0.3221 1.0000
5.500 0.9656 0.01642 0.00775 -0.0478 0.3192 1.0000
5.750 0.9867 0.01666 0.00797 -0.0466 0.3165 1.0000
6.000 1.0081 0.01693 0.00820 -0.0456 0.3142 1.0000
6.250 1.0293 0.01719 0.00851 -0.0445 0.3116 1.0000
6.500 1.0503 0.01743 0.00882 -0.0434 0.3087 1.0000
6.750 1.0711 0.01768 0.00911 -0.0422 0.3055 1.0000
7.000 1.0918 0.01793 0.00940 -0.0410 0.3027 1.0000
7.250 1.1126 0.01820 0.00966 -0.0399 0.3001 1.0000
7.500 1.1331 0.01850 0.00996 -0.0388 0.2971 1.0000
7.750 1.1525 0.01875 0.01032 -0.0374 0.2934 1.0000
8.000 1.1717 0.01900 0.01065 -0.0361 0.2894 1.0000
8.250 1.1908 0.01926 0.01092 -0.0347 0.2860 1.0000
8.500 1.2092 0.01954 0.01120 -0.0333 0.2821 1.0000
8.750 1.2269 0.01981 0.01160 -0.0317 0.2773 1.0000
9.000 1.2427 0.02003 0.01187 -0.0299 0.2715 1.0000
9.250 1.2580 0.02031 0.01217 -0.0280 0.2659 1.0000
9.500 1.2723 0.02059 0.01254 -0.0259 0.2589 1.0000
9.750 1.2832 0.02093 0.01286 -0.0233 0.2538 1.0000
10.000 1.2969 0.02129 0.01335 -0.0213 0.2477 1.0000
10.250 1.3068 0.02171 0.01379 -0.0187 0.2409 1.0000
10.500 1.3183 0.02218 0.01434 -0.0166 0.2327 1.0000
10.750 1.3265 0.02279 0.01495 -0.0141 0.2242 1.0000
11.000 1.3357 0.02347 0.01568 -0.0120 0.2141 1.0000
11.250 1.3432 0.02429 0.01654 -0.0099 0.2036 1.0000
11.500 1.3465 0.02540 0.01764 -0.0076 0.1904 1.0000
11.750 1.3437 0.02698 0.01916 -0.0052 0.1737 1.0000
12.000 1.3381 0.02896 0.02109 -0.0030 0.1586 1.0000
12.250 1.3291 0.03144 0.02354 -0.0012 0.1430 1.0000
12.500 1.3165 0.03454 0.02662 0.0002 0.1281 1.0000
12.750 1.3029 0.03806 0.03015 0.0008 0.1162 1.0000
13.000 1.2839 0.04251 0.03461 0.0009 0.1032 1.0000
13.250 1.2653 0.04728 0.03943 0.0004 0.0915 1.0000
13.500 1.2381 0.05335 0.04552 -0.0008 0.0731 1.0000
13.750 1.2179 0.05887 0.05111 -0.0020 0.0627 1.0000
14.000 1.1919 0.06528 0.05756 -0.0036 0.0506 1.0000
14.250 1.1656 0.07191 0.06424 -0.0054 0.0402 1.0000
14.500 1.1437 0.07809 0.07047 -0.0071 0.0332 1.0000
14.750 1.1248 0.08403 0.07648 -0.0088 0.0287 1.0000
15.000 1.1118 0.08923 0.08176 -0.0103 0.0264 1.0000
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