GOE 401 AIRFOIL (goe401-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 401 AIRFOIL (goe401-il) Reynolds number: 200,000 Max Cl/Cd: 75.4 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe401-il-200000-n5.txt Download as CSV file: xf-goe401-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 401 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3067 0.09295 0.08952 -0.0231 1.0000 0.0262
-7.500 -0.3141 0.09122 0.08787 -0.0234 1.0000 0.0264
-7.250 -0.3161 0.08882 0.08554 -0.0249 1.0000 0.0265
-7.000 -0.3144 0.08613 0.08290 -0.0270 1.0000 0.0266
-6.750 -0.3090 0.08304 0.07984 -0.0288 0.9995 0.0267
-6.500 -0.2801 0.07786 0.07462 -0.0363 0.9915 0.0267
-6.250 -0.2531 0.07294 0.06963 -0.0427 0.9805 0.0267
-6.000 -0.2281 0.06822 0.06486 -0.0480 0.9656 0.0267
-5.750 -0.2016 0.06351 0.06007 -0.0530 0.9509 0.0267
-5.500 -0.1843 0.06125 0.05786 -0.0523 0.9384 0.0285
-5.250 -0.1270 0.05634 0.05265 -0.0659 0.9245 0.0340
-5.000 -0.1012 0.05165 0.04794 -0.0696 0.9128 0.0352
-4.750 -0.0685 0.04875 0.04495 -0.0733 0.9009 0.0369
-4.500 -0.0307 0.04527 0.04127 -0.0786 0.8866 0.0404
-4.250 0.0053 0.04134 0.03709 -0.0835 0.8706 0.0452
-4.000 0.0428 0.03869 0.03403 -0.0871 0.8546 0.0536
-3.750 0.0639 0.03632 0.03163 -0.0875 0.8390 0.0548
-3.500 0.0873 0.03481 0.03002 -0.0877 0.8233 0.0578
-3.250 0.1202 0.02835 0.02276 -0.0887 0.8102 0.0436
-3.000 0.1437 0.02603 0.02015 -0.0884 0.7954 0.0439
-2.750 0.1693 0.02434 0.01815 -0.0879 0.7810 0.0432
-2.500 0.1927 0.02253 0.01614 -0.0874 0.7666 0.0424
-2.250 0.2170 0.02078 0.01408 -0.0867 0.7520 0.0418
-2.000 0.2417 0.01918 0.01213 -0.0859 0.7370 0.0413
-1.750 0.2667 0.01780 0.01041 -0.0851 0.7217 0.0411
-1.500 0.2920 0.01673 0.00902 -0.0843 0.7057 0.0410
-1.250 0.3173 0.01590 0.00791 -0.0835 0.6885 0.0411
-1.000 0.3427 0.01533 0.00710 -0.0828 0.6702 0.0419
-0.750 0.3680 0.01483 0.00637 -0.0820 0.6507 0.0423
-0.500 0.3931 0.01434 0.00570 -0.0812 0.6298 0.0421
-0.250 0.4180 0.01395 0.00515 -0.0803 0.6072 0.0419
0.000 0.4426 0.01364 0.00468 -0.0794 0.5837 0.0418
0.250 0.4669 0.01341 0.00430 -0.0785 0.5604 0.0418
0.500 0.4912 0.01323 0.00401 -0.0776 0.5377 0.0417
0.750 0.5153 0.01312 0.00377 -0.0767 0.5177 0.0418
1.000 0.5395 0.01305 0.00359 -0.0758 0.5002 0.0419
1.250 0.5639 0.01302 0.00346 -0.0750 0.4852 0.0421
1.500 0.5886 0.01302 0.00338 -0.0743 0.4722 0.0424
1.750 0.6135 0.01304 0.00333 -0.0736 0.4609 0.0428
2.000 0.6384 0.01309 0.00331 -0.0729 0.4511 0.0434
2.250 0.6633 0.01314 0.00331 -0.0722 0.4419 0.0449
2.500 0.6885 0.01320 0.00335 -0.0715 0.4336 0.0474
2.750 0.7134 0.01329 0.00343 -0.0709 0.4259 0.0520
3.000 0.7385 0.01332 0.00358 -0.0703 0.4186 0.0949
3.250 0.7634 0.01340 0.00376 -0.0697 0.4114 0.1566
3.500 0.8228 0.01210 0.00406 -0.0770 0.4019 1.0000
3.750 0.8473 0.01233 0.00420 -0.0763 0.3952 1.0000
4.000 0.8722 0.01252 0.00437 -0.0757 0.3883 1.0000
4.250 0.8968 0.01274 0.00456 -0.0750 0.3817 1.0000
4.500 0.9215 0.01296 0.00476 -0.0743 0.3754 1.0000
4.750 0.9460 0.01317 0.00495 -0.0736 0.3680 1.0000
5.000 0.9701 0.01339 0.00515 -0.0728 0.3596 1.0000
5.250 0.9940 0.01361 0.00537 -0.0721 0.3502 1.0000
5.500 1.0183 0.01382 0.00560 -0.0713 0.3416 1.0000
5.750 1.0418 0.01408 0.00583 -0.0705 0.3338 1.0000
6.000 1.0659 0.01429 0.00609 -0.0698 0.3241 1.0000
6.250 1.0892 0.01453 0.00636 -0.0690 0.3138 1.0000
6.500 1.1121 0.01480 0.00662 -0.0681 0.3027 1.0000
6.750 1.1351 0.01508 0.00692 -0.0672 0.2922 1.0000
7.000 1.1582 0.01536 0.00725 -0.0664 0.2829 1.0000
7.250 1.1804 0.01568 0.00760 -0.0654 0.2719 1.0000
7.500 1.2021 0.01604 0.00795 -0.0644 0.2596 1.0000
8.000 1.2443 0.01683 0.00876 -0.0622 0.2327 1.0000
8.250 1.2649 0.01727 0.00922 -0.0611 0.2190 1.0000
8.500 1.2845 0.01777 0.00975 -0.0598 0.2029 1.0000
8.750 1.3018 0.01844 0.01034 -0.0583 0.1762 1.0000
9.000 1.3160 0.01936 0.01108 -0.0564 0.1376 1.0000
9.250 1.3226 0.02089 0.01226 -0.0536 0.0862 1.0000
9.500 1.3335 0.02203 0.01332 -0.0513 0.0726 1.0000
9.750 1.3463 0.02294 0.01431 -0.0492 0.0668 1.0000
10.000 1.3571 0.02391 0.01535 -0.0468 0.0626 1.0000
10.250 1.3633 0.02498 0.01648 -0.0438 0.0592 1.0000
10.500 1.3726 0.02583 0.01748 -0.0412 0.0571 1.0000
10.750 1.3803 0.02680 0.01857 -0.0387 0.0545 1.0000
11.000 1.3853 0.02797 0.01984 -0.0360 0.0519 1.0000
11.250 1.3858 0.02950 0.02143 -0.0333 0.0491 1.0000
11.500 1.3905 0.03085 0.02291 -0.0312 0.0459 1.0000
11.750 1.3987 0.03204 0.02424 -0.0297 0.0429 1.0000
12.000 1.4043 0.03351 0.02581 -0.0283 0.0399 1.0000
12.250 1.4050 0.03548 0.02785 -0.0269 0.0372 1.0000
12.500 1.4032 0.03785 0.03032 -0.0258 0.0357 1.0000
12.750 1.4084 0.03969 0.03233 -0.0250 0.0341 1.0000
13.000 1.4119 0.04180 0.03459 -0.0245 0.0318 1.0000
13.250 1.4133 0.04425 0.03715 -0.0242 0.0295 1.0000
13.500 1.4111 0.04724 0.04024 -0.0242 0.0276 1.0000
13.750 1.4097 0.05027 0.04340 -0.0244 0.0251 1.0000
14.000 1.4074 0.05353 0.04679 -0.0248 0.0226 1.0000
14.250 1.4019 0.05736 0.05068 -0.0257 0.0204 1.0000
14.500 1.3959 0.06136 0.05481 -0.0266 0.0184 1.0000
14.750 1.3885 0.06569 0.05924 -0.0277 0.0167 1.0000
15.000 1.3783 0.07056 0.06419 -0.0292 0.0155 1.0000
15.250 1.3691 0.07538 0.06913 -0.0307 0.0146 1.0000
15.500 1.3599 0.08030 0.07417 -0.0323 0.0133 1.0000
15.750 1.3508 0.08526 0.07925 -0.0340 0.0130 1.0000
16.000 1.3412 0.09041 0.08451 -0.0359 0.0125 1.0000
16.250 1.3307 0.09583 0.09002 -0.0379 0.0120 1.0000
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Polar data table (+)
Polar graphs
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