GOE 622 AIRFOIL (goe622-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 622 AIRFOIL (goe622-il) Reynolds number: 50,000 Max Cl/Cd: 38.23 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe622-il-50000-n5.txt Download as CSV file: xf-goe622-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 622 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4890 0.09974 0.09287 -0.0197 1.0000 0.0452
-8.500 -0.4857 0.09578 0.08896 -0.0207 1.0000 0.0446
-8.250 -0.4847 0.09173 0.08498 -0.0225 1.0000 0.0442
-8.000 -0.4849 0.08753 0.08086 -0.0250 1.0000 0.0440
-7.750 -0.4832 0.08286 0.07624 -0.0285 1.0000 0.0439
-7.500 -0.4804 0.07792 0.07134 -0.0322 1.0000 0.0439
-7.250 -0.4768 0.07277 0.06618 -0.0358 1.0000 0.0440
-7.000 -0.4723 0.06749 0.06084 -0.0390 1.0000 0.0441
-6.750 -0.4669 0.06215 0.05536 -0.0417 1.0000 0.0444
-6.500 -0.4597 0.05695 0.04995 -0.0436 1.0000 0.0447
-6.250 -0.4505 0.05192 0.04461 -0.0448 1.0000 0.0449
-6.000 -0.4391 0.04704 0.03933 -0.0455 1.0000 0.0452
-5.750 -0.4249 0.04233 0.03407 -0.0457 1.0000 0.0458
-5.500 -0.4092 0.03932 0.03089 -0.0454 1.0000 0.0481
-5.250 -0.3911 0.03720 0.02855 -0.0448 1.0000 0.0527
-5.000 -0.3706 0.03373 0.02442 -0.0443 1.0000 0.0567
-4.750 -0.3483 0.03050 0.02056 -0.0436 1.0000 0.0602
-4.500 -0.3272 0.02920 0.01907 -0.0429 1.0000 0.0692
-4.250 -0.3042 0.02732 0.01686 -0.0421 1.0000 0.0773
-4.000 -0.2814 0.02609 0.01538 -0.0413 1.0000 0.0908
-3.750 -0.2576 0.02468 0.01372 -0.0404 1.0000 0.1037
-3.500 -0.2333 0.02343 0.01227 -0.0396 1.0000 0.1175
-3.250 -0.2099 0.02262 0.01134 -0.0390 1.0000 0.1394
-3.000 -0.1856 0.02173 0.01033 -0.0383 1.0000 0.1591
-2.750 -0.1616 0.02105 0.00961 -0.0378 1.0000 0.1864
-2.500 -0.1377 0.02040 0.00902 -0.0375 1.0000 0.2176
-2.250 -0.1136 0.01975 0.00849 -0.0372 1.0000 0.2597
-2.000 -0.0894 0.01895 0.00807 -0.0370 1.0000 0.3325
-1.750 -0.0685 0.01763 0.00784 -0.0358 1.0000 0.5470
-1.500 -0.0432 0.01664 0.00768 -0.0338 1.0000 1.0000
-1.250 -0.0216 0.01682 0.00748 -0.0332 1.0000 1.0000
-1.000 -0.0001 0.01704 0.00740 -0.0327 1.0000 1.0000
-0.750 0.0385 0.01731 0.00736 -0.0355 0.9913 1.0000
-0.500 0.0803 0.01758 0.00735 -0.0389 0.9802 1.0000
-0.250 0.1212 0.01783 0.00738 -0.0420 0.9686 1.0000
0.000 0.1613 0.01806 0.00743 -0.0449 0.9565 1.0000
0.250 0.2006 0.01827 0.00752 -0.0476 0.9441 1.0000
0.500 0.2404 0.01848 0.00763 -0.0503 0.9318 1.0000
0.750 0.2807 0.01866 0.00774 -0.0530 0.9198 1.0000
1.000 0.3205 0.01882 0.00786 -0.0555 0.9077 1.0000
1.250 0.3585 0.01896 0.00800 -0.0575 0.8948 1.0000
1.500 0.3938 0.01910 0.00815 -0.0589 0.8806 1.0000
1.750 0.4268 0.01924 0.00831 -0.0597 0.8650 1.0000
2.000 0.4586 0.01936 0.00848 -0.0602 0.8480 1.0000
2.250 0.4902 0.01941 0.00858 -0.0604 0.8302 1.0000
2.500 0.5212 0.01941 0.00863 -0.0603 0.8118 1.0000
2.750 0.5477 0.01950 0.00881 -0.0595 0.7903 1.0000
3.000 0.5762 0.01952 0.00890 -0.0589 0.7708 1.0000
3.250 0.6022 0.01963 0.00909 -0.0580 0.7499 1.0000
3.500 0.6289 0.01973 0.00931 -0.0571 0.7295 1.0000
3.750 0.6553 0.01984 0.00951 -0.0561 0.7081 1.0000
4.000 0.6815 0.01991 0.00966 -0.0550 0.6842 1.0000
4.250 0.7064 0.01998 0.00982 -0.0535 0.6554 1.0000
4.500 0.7300 0.02012 0.00997 -0.0518 0.6213 1.0000
4.750 0.7533 0.02034 0.01020 -0.0501 0.5859 1.0000
5.000 0.7768 0.02067 0.01057 -0.0487 0.5532 1.0000
5.250 0.7996 0.02109 0.01114 -0.0474 0.5194 1.0000
5.500 0.8221 0.02154 0.01170 -0.0460 0.4836 1.0000
5.750 0.8433 0.02206 0.01230 -0.0445 0.4418 1.0000
6.000 0.8637 0.02268 0.01292 -0.0429 0.3966 1.0000
6.250 0.8835 0.02348 0.01365 -0.0414 0.3534 1.0000
6.500 0.9012 0.02450 0.01451 -0.0397 0.3058 1.0000
6.750 0.9157 0.02571 0.01551 -0.0380 0.2507 1.0000
7.000 0.9323 0.02690 0.01665 -0.0367 0.2066 1.0000
7.250 0.9467 0.02829 0.01781 -0.0354 0.1475 1.0000
7.500 0.9594 0.03025 0.01951 -0.0339 0.0952 1.0000
7.750 0.9719 0.03243 0.02149 -0.0321 0.0629 1.0000
8.000 0.9839 0.03458 0.02362 -0.0303 0.0505 1.0000
8.250 0.9956 0.03679 0.02595 -0.0284 0.0449 1.0000
8.500 1.0095 0.03889 0.02829 -0.0265 0.0410 1.0000
8.750 1.0216 0.04108 0.03057 -0.0249 0.0378 1.0000
9.000 1.0368 0.04338 0.03318 -0.0233 0.0348 1.0000
9.250 1.0506 0.04579 0.03600 -0.0218 0.0323 1.0000
9.500 1.0629 0.04846 0.03892 -0.0203 0.0310 1.0000
9.750 1.0729 0.05138 0.04208 -0.0188 0.0301 1.0000
10.000 1.0803 0.05466 0.04558 -0.0173 0.0294 1.0000
10.250 1.0817 0.05820 0.04949 -0.0155 0.0291 1.0000
10.500 1.0765 0.06182 0.05350 -0.0135 0.0288 1.0000
10.750 1.0670 0.06569 0.05771 -0.0121 0.0287 1.0000
11.000 1.0543 0.06992 0.06224 -0.0115 0.0286 1.0000
11.250 1.0392 0.07463 0.06722 -0.0121 0.0285 1.0000
11.500 1.0228 0.07992 0.07274 -0.0137 0.0286 1.0000
11.750 1.0058 0.08584 0.07885 -0.0165 0.0288 1.0000
12.000 0.9886 0.09244 0.08560 -0.0202 0.0290 1.0000
12.250 0.9721 0.09957 0.09285 -0.0245 0.0292 1.0000
12.500 0.9414 0.11172 0.10524 -0.0332 0.0304 1.0000
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Polar data table (+)
Polar graphs
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