GOE 795 smoothed (goe795sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 795 smoothed (goe795sm-il) Reynolds number: 200,000 Max Cl/Cd: 76.51 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe795sm-il-200000.txt Download as CSV file: xf-goe795sm-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 795 smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4547 0.09390 0.09038 -0.0330 1.0000 0.0475
-8.500 -0.4626 0.09053 0.08707 -0.0353 1.0000 0.0477
-8.250 -0.4704 0.08723 0.08382 -0.0368 1.0000 0.0478
-8.000 -0.4745 0.08295 0.07955 -0.0398 1.0000 0.0479
-7.750 -0.4773 0.07886 0.07543 -0.0414 1.0000 0.0479
-7.500 -0.4836 0.07319 0.06987 -0.0387 1.0000 0.0491
-7.250 -0.4809 0.07061 0.06732 -0.0366 1.0000 0.0499
-7.000 -0.4790 0.06792 0.06464 -0.0354 1.0000 0.0508
-6.750 -0.4780 0.06490 0.06161 -0.0349 1.0000 0.0518
-6.500 -0.4767 0.06181 0.05850 -0.0343 1.0000 0.0533
-6.250 -0.4753 0.05837 0.05499 -0.0340 1.0000 0.0550
-6.000 -0.4729 0.05412 0.05022 -0.0357 1.0000 0.0605
-5.750 -0.4690 0.05159 0.04738 -0.0338 1.0000 0.0609
-5.500 -0.4696 0.04503 0.04090 -0.0327 1.0000 0.0626
-5.250 -0.4610 0.04256 0.03843 -0.0309 1.0000 0.0638
-5.000 -0.4512 0.04028 0.03607 -0.0292 1.0000 0.0655
-4.750 -0.4428 0.02700 0.02098 -0.0254 1.0000 0.0373
-4.500 -0.4173 0.02522 0.01909 -0.0260 0.9979 0.0399
-4.250 -0.3839 0.02232 0.01560 -0.0270 0.9946 0.0403
-4.000 -0.3501 0.02053 0.01341 -0.0280 0.9905 0.0434
-3.750 -0.3126 0.01983 0.01232 -0.0297 0.9858 0.0479
-3.500 -0.2772 0.01800 0.01039 -0.0315 0.9830 0.0549
-3.250 -0.2443 0.01717 0.00936 -0.0324 0.9772 0.0622
-3.000 -0.2080 0.01626 0.00843 -0.0342 0.9728 0.0711
-2.750 -0.1720 0.01548 0.00766 -0.0360 0.9686 0.0817
-2.500 -0.1399 0.01478 0.00697 -0.0369 0.9620 0.0930
-2.250 -0.1015 0.01421 0.00645 -0.0392 0.9580 0.1122
-2.000 -0.0711 0.01361 0.00601 -0.0398 0.9509 0.1449
-1.750 -0.0374 0.01269 0.00579 -0.0414 0.9458 0.2967
-1.500 -0.0102 0.01176 0.00567 -0.0416 0.9393 0.4953
-1.250 0.1134 0.01067 0.00581 -0.0613 0.9568 1.0000
-1.000 0.1481 0.01058 0.00558 -0.0627 0.9478 1.0000
-0.750 0.1953 0.01042 0.00529 -0.0667 0.9440 1.0000
-0.500 0.2328 0.01027 0.00505 -0.0686 0.9355 1.0000
-0.250 0.2809 0.01004 0.00474 -0.0726 0.9311 1.0000
0.000 0.3184 0.00987 0.00451 -0.0744 0.9223 1.0000
0.250 0.3625 0.00962 0.00422 -0.0776 0.9162 1.0000
0.500 0.3959 0.00948 0.00404 -0.0785 0.9053 1.0000
0.750 0.4300 0.00935 0.00389 -0.0796 0.8943 1.0000
1.000 0.4631 0.00924 0.00375 -0.0804 0.8828 1.0000
1.250 0.4941 0.00917 0.00365 -0.0807 0.8704 1.0000
1.500 0.5225 0.00915 0.00360 -0.0805 0.8565 1.0000
1.750 0.5491 0.00916 0.00360 -0.0799 0.8416 1.0000
2.000 0.5747 0.00920 0.00361 -0.0791 0.8261 1.0000
2.250 0.5995 0.00924 0.00363 -0.0781 0.8095 1.0000
2.500 0.6242 0.00930 0.00365 -0.0771 0.7919 1.0000
2.750 0.6474 0.00936 0.00369 -0.0757 0.7710 1.0000
3.000 0.6704 0.00943 0.00370 -0.0742 0.7479 1.0000
3.250 0.6922 0.00953 0.00378 -0.0725 0.7239 1.0000
3.500 0.7144 0.00965 0.00386 -0.0710 0.6996 1.0000
3.750 0.7362 0.00980 0.00398 -0.0694 0.6735 1.0000
4.000 0.7575 0.00997 0.00410 -0.0677 0.6452 1.0000
4.250 0.7781 0.01017 0.00425 -0.0659 0.6134 1.0000
4.500 0.7980 0.01043 0.00441 -0.0641 0.5783 1.0000
4.750 0.8170 0.01074 0.00461 -0.0620 0.5374 1.0000
5.000 0.8347 0.01113 0.00488 -0.0598 0.4906 1.0000
5.250 0.8510 0.01163 0.00517 -0.0573 0.4380 1.0000
5.500 0.8661 0.01223 0.00552 -0.0548 0.3802 1.0000
5.750 0.8804 0.01293 0.00595 -0.0523 0.3162 1.0000
6.000 0.8937 0.01378 0.00645 -0.0497 0.2443 1.0000
6.250 0.9067 0.01477 0.00706 -0.0472 0.1764 1.0000
6.500 0.9203 0.01579 0.00782 -0.0448 0.1265 1.0000
6.750 0.9332 0.01694 0.00872 -0.0423 0.0845 1.0000
7.000 0.9451 0.01824 0.00986 -0.0395 0.0579 1.0000
7.250 0.9589 0.01934 0.01094 -0.0370 0.0459 1.0000
7.500 0.9707 0.02073 0.01236 -0.0341 0.0402 1.0000
7.750 0.9862 0.02188 0.01359 -0.0319 0.0363 1.0000
8.000 1.0011 0.02332 0.01504 -0.0297 0.0336 1.0000
8.250 1.0183 0.02562 0.01744 -0.0281 0.0312 1.0000
8.500 1.0374 0.02668 0.01868 -0.0265 0.0289 1.0000
8.750 1.0574 0.02851 0.02069 -0.0252 0.0275 1.0000
9.000 1.0764 0.03060 0.02301 -0.0237 0.0264 1.0000
9.250 1.0935 0.03297 0.02564 -0.0221 0.0257 1.0000
9.500 1.1076 0.03569 0.02868 -0.0200 0.0254 1.0000
9.750 1.1183 0.03788 0.03103 -0.0180 0.0242 1.0000
10.000 1.1201 0.04247 0.03593 -0.0155 0.0230 1.0000
10.250 1.1198 0.04604 0.03986 -0.0123 0.0229 1.0000
10.500 1.1173 0.04915 0.04328 -0.0090 0.0229 1.0000
10.750 1.1127 0.05181 0.04625 -0.0054 0.0231 1.0000
11.000 1.1048 0.05382 0.04850 -0.0013 0.0234 1.0000
11.250 1.0914 0.05628 0.05125 0.0027 0.0239 1.0000
11.500 1.0466 0.06201 0.05752 0.0067 0.0255 1.0000
11.750 1.0120 0.06807 0.06390 0.0071 0.0266 1.0000
12.000 0.9847 0.07397 0.07000 0.0056 0.0271 1.0000
12.250 0.9593 0.08052 0.07671 0.0023 0.0274 1.0000
12.500 0.9333 0.08844 0.08477 -0.0029 0.0277 1.0000
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Polar data table (+)
Polar graphs
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