USA 33 AIRFOIL (usa33-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 33 AIRFOIL (usa33-il) Reynolds number: 50,000 Max Cl/Cd: 27.08 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa33-il-50000-n5.txt Download as CSV file: xf-usa33-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2236 0.11232 0.10543 -0.0326 1.0000 0.1433
-8.750 -0.2409 0.11155 0.10484 -0.0312 1.0000 0.1442
-8.500 -0.2449 0.10931 0.10269 -0.0338 0.9911 0.1447
-8.250 -0.2348 0.10549 0.09888 -0.0401 0.9740 0.1451
-8.000 -0.2239 0.10149 0.09487 -0.0457 0.9571 0.1452
-7.750 -0.2105 0.09737 0.09074 -0.0504 0.9416 0.1451
-7.500 -0.1965 0.09333 0.08666 -0.0546 0.9273 0.1450
-7.000 -0.1810 0.07939 0.07239 -0.0655 0.8992 0.1012
-6.750 -0.1612 0.07597 0.06893 -0.0675 0.8868 0.1000
-6.500 -0.1433 0.07216 0.06501 -0.0705 0.8762 0.0983
-6.250 -0.1361 0.06888 0.06161 -0.0716 0.8618 0.0967
-6.000 -0.1280 0.06548 0.05803 -0.0727 0.8497 0.0955
-5.750 -0.1161 0.06256 0.05493 -0.0734 0.8384 0.0958
-5.500 -0.1078 0.06010 0.05230 -0.0728 0.8259 0.0961
-5.250 -0.0932 0.05745 0.04944 -0.0729 0.8164 0.0969
-5.000 -0.0865 0.05534 0.04715 -0.0712 0.8039 0.0971
-4.750 -0.0714 0.05274 0.04428 -0.0707 0.7954 0.0969
-4.500 -0.0646 0.05088 0.04224 -0.0684 0.7838 0.0968
-4.250 -0.0481 0.04865 0.03973 -0.0675 0.7759 0.0971
-4.000 -0.0376 0.04703 0.03789 -0.0654 0.7658 0.0982
-3.750 -0.0225 0.04504 0.03556 -0.0639 0.7573 0.1000
-3.500 -0.0067 0.04291 0.03302 -0.0622 0.7498 0.1012
-3.250 0.0076 0.04191 0.03192 -0.0602 0.7401 0.1021
-3.000 0.0315 0.04056 0.03037 -0.0595 0.7338 0.1032
-2.750 0.0463 0.03975 0.02941 -0.0575 0.7246 0.1047
-2.500 0.0667 0.03867 0.02811 -0.0561 0.7166 0.1073
-2.250 0.0956 0.03687 0.02584 -0.0557 0.7109 0.1109
-2.000 0.1081 0.03663 0.02561 -0.0533 0.6994 0.1126
-1.750 0.1380 0.03557 0.02438 -0.0530 0.6920 0.1153
-1.500 0.1580 0.03487 0.02349 -0.0514 0.6822 0.1188
-1.250 0.1846 0.03414 0.02261 -0.0508 0.6737 0.1234
-1.000 0.2155 0.03344 0.02176 -0.0507 0.6670 0.1291
-0.750 0.2369 0.03305 0.02126 -0.0495 0.6571 0.1341
-0.500 0.2727 0.03246 0.02056 -0.0502 0.6503 0.1428
-0.250 0.3002 0.03227 0.02035 -0.0500 0.6419 0.1520
0.000 0.3337 0.03193 0.01993 -0.0506 0.6334 0.1655
0.250 0.3758 0.03131 0.01913 -0.0523 0.6274 0.1867
0.500 0.3955 0.03144 0.01930 -0.0511 0.6174 0.2015
0.750 0.4252 0.03112 0.01896 -0.0510 0.6099 0.2221
1.000 0.4520 0.03081 0.01871 -0.0506 0.6028 0.2477
1.250 0.4675 0.03090 0.01891 -0.0486 0.5931 0.2647
1.500 0.4959 0.03047 0.01844 -0.0481 0.5866 0.2793
1.750 0.5092 0.03072 0.01872 -0.0456 0.5774 0.2893
2.000 0.5272 0.03069 0.01873 -0.0437 0.5692 0.3004
2.250 0.5559 0.03026 0.01827 -0.0431 0.5634 0.3159
2.500 0.5592 0.03086 0.01904 -0.0394 0.5526 0.3291
2.750 0.5794 0.03046 0.01888 -0.0377 0.5455 0.3716
3.250 0.7987 0.03001 0.01949 -0.0661 0.5221 1.0000
3.500 0.8060 0.03078 0.02025 -0.0629 0.5126 1.0000
3.750 0.8213 0.03119 0.02056 -0.0606 0.5043 1.0000
4.000 0.8460 0.03124 0.02044 -0.0595 0.4981 1.0000
4.250 0.8433 0.03237 0.02165 -0.0550 0.4875 1.0000
4.500 0.8666 0.03235 0.02147 -0.0536 0.4800 1.0000
4.750 0.8669 0.03327 0.02241 -0.0495 0.4700 1.0000
5.000 0.8840 0.03343 0.02247 -0.0473 0.4616 1.0000
5.250 0.8903 0.03405 0.02306 -0.0439 0.4527 1.0000
5.500 0.8989 0.03456 0.02354 -0.0408 0.4438 1.0000
5.750 0.9164 0.03473 0.02360 -0.0387 0.4366 1.0000
6.000 0.9102 0.03592 0.02485 -0.0341 0.4275 1.0000
6.250 0.9355 0.03579 0.02459 -0.0329 0.4213 1.0000
6.500 0.9225 0.03737 0.02624 -0.0277 0.4127 1.0000
6.750 0.9348 0.03782 0.02664 -0.0252 0.4059 1.0000
7.000 0.9499 0.03817 0.02691 -0.0230 0.3998 1.0000
7.250 0.9270 0.04011 0.02892 -0.0169 0.3918 1.0000
7.500 0.9523 0.04002 0.02874 -0.0159 0.3861 1.0000
7.750 0.9415 0.04176 0.03051 -0.0117 0.3790 1.0000
8.000 0.9361 0.04344 0.03221 -0.0084 0.3716 1.0000
8.250 0.9727 0.04267 0.03133 -0.0081 0.3668 1.0000
8.500 0.9330 0.04689 0.03568 -0.0035 0.3577 1.0000
8.750 0.9487 0.04741 0.03616 -0.0020 0.3515 1.0000
9.000 1.0002 0.04530 0.03387 -0.0020 0.3468 1.0000
9.250 0.9276 0.05311 0.04193 0.0019 0.3355 1.0000
9.500 0.9687 0.05124 0.03996 0.0030 0.3308 1.0000
9.750 0.9062 0.05994 0.04884 0.0041 0.3196 1.0000
10.000 0.9237 0.06030 0.04917 0.0054 0.3139 1.0000
10.250 0.9813 0.05621 0.04492 0.0071 0.3106 1.0000
10.500 0.8712 0.07233 0.06133 0.0051 0.2959 1.0000
10.750 0.9166 0.06871 0.05764 0.0074 0.2930 1.0000
11.000 0.9773 0.06358 0.05237 0.0098 0.2907 1.0000
11.250 0.8605 0.08242 0.07148 0.0055 0.2752 1.0000
11.500 0.9032 0.07883 0.06784 0.0080 0.2731 1.0000
12.000 0.8417 0.09483 0.08399 0.0042 0.2567 1.0000
12.500 0.8089 0.10672 0.09596 0.0013 0.2429 1.0000
12.750 0.8345 0.10565 0.09490 0.0028 0.2397 1.0000
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Polar data table (+)
Polar graphs
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