USA 33 AIRFOIL (usa33-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 33 AIRFOIL (usa33-il) Reynolds number: 500,000 Max Cl/Cd: 67.36 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa33-il-500000-n5.txt Download as CSV file: xf-usa33-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 33 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6499 0.02900 0.02440 -0.0948 0.8898 0.0353
-11.000 -0.6349 0.02642 0.02128 -0.0948 0.8529 0.0356
-10.750 -0.6209 0.02550 0.02017 -0.0928 0.8314 0.0358
-10.250 -0.5885 0.02425 0.01868 -0.0891 0.8036 0.0362
-10.000 -0.5712 0.02368 0.01801 -0.0873 0.7927 0.0364
-9.750 -0.5535 0.02305 0.01727 -0.0856 0.7822 0.0366
-9.500 -0.5350 0.02252 0.01663 -0.0839 0.7723 0.0368
-9.250 -0.5163 0.02189 0.01589 -0.0823 0.7621 0.0370
-9.000 -0.4968 0.02139 0.01526 -0.0807 0.7519 0.0374
-8.750 -0.4769 0.02082 0.01458 -0.0793 0.7408 0.0378
-8.500 -0.4572 0.02025 0.01386 -0.0777 0.7293 0.0382
-8.250 -0.4371 0.01961 0.01306 -0.0762 0.7168 0.0385
-8.000 -0.4165 0.01901 0.01229 -0.0747 0.7049 0.0390
-7.750 -0.3954 0.01845 0.01157 -0.0733 0.6920 0.0393
-7.500 -0.3733 0.01797 0.01092 -0.0721 0.6797 0.0396
-7.250 -0.3515 0.01747 0.01031 -0.0708 0.6673 0.0399
-7.000 -0.3286 0.01707 0.00985 -0.0697 0.6548 0.0402
-6.750 -0.3054 0.01675 0.00946 -0.0686 0.6436 0.0405
-6.500 -0.2818 0.01645 0.00909 -0.0675 0.6323 0.0408
-6.250 -0.2580 0.01614 0.00871 -0.0665 0.6225 0.0411
-6.000 -0.2339 0.01587 0.00836 -0.0656 0.6114 0.0416
-5.750 -0.2098 0.01562 0.00801 -0.0646 0.6014 0.0421
-5.500 -0.1853 0.01535 0.00765 -0.0637 0.5909 0.0426
-5.250 -0.1607 0.01511 0.00731 -0.0628 0.5822 0.0431
-5.000 -0.1355 0.01483 0.00695 -0.0620 0.5745 0.0436
-4.750 -0.1104 0.01460 0.00663 -0.0612 0.5674 0.0440
-4.500 -0.0855 0.01429 0.00627 -0.0604 0.5618 0.0444
-4.250 -0.0600 0.01400 0.00599 -0.0597 0.5560 0.0448
-4.000 -0.0348 0.01379 0.00575 -0.0589 0.5492 0.0453
-3.750 -0.0099 0.01361 0.00553 -0.0581 0.5428 0.0458
-3.500 0.0159 0.01341 0.00531 -0.0574 0.5378 0.0463
-3.250 0.0418 0.01324 0.00512 -0.0567 0.5328 0.0471
-3.000 0.0675 0.01307 0.00493 -0.0560 0.5285 0.0478
-2.750 0.0931 0.01294 0.00475 -0.0553 0.5244 0.0484
-2.500 0.1184 0.01281 0.00458 -0.0545 0.5203 0.0488
-2.250 0.1437 0.01255 0.00436 -0.0538 0.5168 0.0495
-2.000 0.1692 0.01238 0.00421 -0.0530 0.5126 0.0501
-1.500 0.2196 0.01213 0.00395 -0.0514 0.5037 0.0516
-1.250 0.2445 0.01205 0.00384 -0.0506 0.4996 0.0525
-1.000 0.2702 0.01195 0.00375 -0.0499 0.4962 0.0535
-0.750 0.2955 0.01181 0.00364 -0.0491 0.4922 0.0544
-0.500 0.3203 0.01170 0.00355 -0.0482 0.4878 0.0555
-0.250 0.3450 0.01162 0.00347 -0.0473 0.4831 0.0566
0.000 0.3692 0.01159 0.00341 -0.0464 0.4777 0.0577
0.250 0.3945 0.01151 0.00335 -0.0456 0.4709 0.0590
0.500 0.4183 0.01145 0.00328 -0.0445 0.4628 0.0608
0.750 0.4420 0.01140 0.00323 -0.0434 0.4546 0.0633
1.000 0.4658 0.01135 0.00319 -0.0424 0.4452 0.0670
1.500 0.5102 0.01123 0.00320 -0.0398 0.4232 0.1141
1.750 0.5327 0.01130 0.00325 -0.0385 0.4063 0.1270
2.250 0.5740 0.01165 0.00341 -0.0354 0.3631 0.1428
2.500 0.5953 0.01181 0.00352 -0.0339 0.3487 0.1487
2.750 0.6173 0.01195 0.00363 -0.0327 0.3378 0.1543
3.000 0.6385 0.01213 0.00374 -0.0312 0.3279 0.1583
3.250 0.6608 0.01223 0.00384 -0.0300 0.3200 0.1623
3.500 0.6817 0.01239 0.00398 -0.0286 0.3116 0.1672
3.750 0.7037 0.01252 0.00409 -0.0273 0.3046 0.1720
4.000 0.7253 0.01263 0.00420 -0.0259 0.2980 0.1758
4.250 0.7448 0.01281 0.00435 -0.0243 0.2901 0.1800
4.500 0.7663 0.01292 0.00447 -0.0229 0.2827 0.1851
4.750 0.7855 0.01311 0.00462 -0.0212 0.2740 0.1898
5.000 0.8054 0.01322 0.00475 -0.0196 0.2674 0.1963
5.250 0.8241 0.01337 0.00489 -0.0178 0.2598 0.2012
5.500 0.8404 0.01353 0.00503 -0.0155 0.2521 0.2059
5.750 0.8560 0.01369 0.00518 -0.0131 0.2424 0.2115
6.000 0.8712 0.01390 0.00536 -0.0107 0.2326 0.2176
6.250 0.8848 0.01417 0.00560 -0.0080 0.2203 0.2258
6.500 0.8960 0.01455 0.00591 -0.0050 0.2030 0.2365
6.750 0.9062 0.01489 0.00626 -0.0019 0.1892 0.2697
7.000 0.8877 0.01391 0.00655 0.0071 0.1839 0.8127
7.500 1.0629 0.01578 0.00850 -0.0200 0.1410 0.9834
7.750 1.0879 0.01635 0.00902 -0.0202 0.1307 0.9911
8.000 1.1079 0.01745 0.00990 -0.0202 0.0986 0.9981
8.250 1.1102 0.01887 0.01112 -0.0174 0.0656 1.0000
8.500 1.1137 0.01957 0.01181 -0.0138 0.0620 1.0000
8.750 1.1204 0.02023 0.01248 -0.0109 0.0604 1.0000
9.000 1.1276 0.02096 0.01322 -0.0083 0.0590 1.0000
9.250 1.1353 0.02175 0.01403 -0.0059 0.0579 1.0000
9.500 1.1432 0.02262 0.01493 -0.0037 0.0570 1.0000
9.750 1.1513 0.02357 0.01589 -0.0018 0.0563 1.0000
10.000 1.1602 0.02453 0.01689 0.0000 0.0557 1.0000
10.250 1.1695 0.02554 0.01793 0.0015 0.0553 1.0000
10.500 1.1785 0.02663 0.01905 0.0029 0.0549 1.0000
10.750 1.1871 0.02780 0.02027 0.0043 0.0545 1.0000
11.000 1.1954 0.02905 0.02156 0.0055 0.0541 1.0000
11.250 1.2030 0.03041 0.02296 0.0066 0.0537 1.0000
11.500 1.2101 0.03187 0.02446 0.0077 0.0534 1.0000
11.750 1.2158 0.03349 0.02613 0.0086 0.0530 1.0000
12.000 1.2214 0.03518 0.02787 0.0095 0.0527 1.0000
12.250 1.2262 0.03701 0.02975 0.0102 0.0524 1.0000
12.500 1.2299 0.03898 0.03177 0.0109 0.0521 1.0000
12.750 1.2335 0.04101 0.03385 0.0115 0.0519 1.0000
13.000 1.2350 0.04333 0.03622 0.0119 0.0515 1.0000
13.250 1.2363 0.04573 0.03868 0.0123 0.0512 1.0000
13.500 1.2370 0.04824 0.04126 0.0125 0.0511 1.0000
13.750 1.2370 0.05089 0.04396 0.0127 0.0508 1.0000
14.000 1.2348 0.05384 0.04697 0.0127 0.0505 1.0000
14.250 1.2341 0.05667 0.04987 0.0127 0.0503 1.0000
14.500 1.2349 0.05938 0.05264 0.0126 0.0502 1.0000
14.750 1.2364 0.06205 0.05537 0.0125 0.0501 1.0000
15.000 1.2356 0.06503 0.05843 0.0122 0.0499 1.0000
15.250 1.2357 0.06793 0.06140 0.0119 0.0498 1.0000
15.500 1.2338 0.07114 0.06467 0.0115 0.0497 1.0000
15.750 1.2335 0.07420 0.06780 0.0111 0.0496 1.0000
16.000 1.2321 0.07744 0.07111 0.0105 0.0495 1.0000
16.250 1.2305 0.08073 0.07447 0.0099 0.0493 1.0000
16.500 1.2296 0.08395 0.07775 0.0093 0.0492 1.0000
16.750 1.2279 0.08736 0.08123 0.0086 0.0491 1.0000
17.000 1.2269 0.09066 0.08459 0.0079 0.0490 1.0000
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Polar data table (+)
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