GOE 55 AIRFOIL (goe55-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 55 AIRFOIL (goe55-il) Reynolds number: 200,000 Max Cl/Cd: 54.51 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe55-il-200000.txt Download as CSV file: xf-goe55-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 55 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6304 0.10791 0.10431 0.0388 1.0000 0.0479
-8.250 -0.6256 0.10440 0.10083 0.0372 1.0000 0.0491
-8.000 -0.6219 0.10079 0.09724 0.0349 1.0000 0.0506
-7.750 -0.5348 0.08487 0.08156 0.0142 1.0000 0.0543
-7.500 -0.5166 0.08157 0.07825 0.0184 1.0000 0.0556
-7.250 -0.5109 0.07815 0.07486 0.0184 1.0000 0.0569
-7.000 -0.5076 0.07429 0.07100 0.0167 1.0000 0.0582
-6.750 -0.5022 0.06981 0.06653 0.0132 1.0000 0.0599
-6.500 -0.4935 0.06363 0.06028 0.0030 1.0000 0.0632
-6.250 -0.4809 0.05447 0.05087 -0.0092 1.0000 0.0649
-6.000 -0.4699 0.05089 0.04736 -0.0072 1.0000 0.0657
-5.750 -0.4560 0.04782 0.04433 -0.0064 1.0000 0.0670
-5.500 -0.4392 0.04452 0.04100 -0.0073 1.0000 0.0696
-5.000 -0.4160 0.04733 0.04288 -0.0177 1.0000 0.0778
-4.750 -0.3949 0.04474 0.04034 -0.0179 1.0000 0.0794
-4.500 -0.3700 0.04226 0.03780 -0.0188 1.0000 0.0825
-4.250 -0.3338 0.03828 0.03327 -0.0228 1.0000 0.0909
-4.000 -0.3106 0.03592 0.03102 -0.0230 1.0000 0.0932
-3.750 -0.2827 0.03397 0.02896 -0.0238 1.0000 0.0990
-3.500 -0.2511 0.03102 0.02569 -0.0255 1.0000 0.1061
-3.250 -0.2236 0.02907 0.02372 -0.0260 1.0000 0.1099
-3.000 -0.1798 0.02292 0.01636 -0.0276 1.0000 0.0781
-2.750 -0.1493 0.02087 0.01412 -0.0278 1.0000 0.0735
-2.500 -0.1185 0.01861 0.01157 -0.0280 1.0000 0.0700
-2.250 -0.0878 0.01682 0.00949 -0.0280 1.0000 0.0683
-2.000 -0.0583 0.01566 0.00820 -0.0279 1.0000 0.0686
-1.750 -0.0292 0.01481 0.00732 -0.0278 1.0000 0.0702
-1.500 -0.0002 0.01416 0.00667 -0.0277 1.0000 0.0731
-1.250 0.0290 0.01347 0.00599 -0.0275 1.0000 0.0751
-1.000 0.0536 0.01404 0.00542 -0.0252 0.5982 0.0772
-0.750 0.0805 0.01398 0.00494 -0.0248 0.5106 0.0812
-0.500 0.1089 0.01392 0.00468 -0.0247 0.4808 0.0876
-0.250 0.1374 0.01367 0.00438 -0.0247 0.4635 0.0972
0.000 0.1665 0.01334 0.00403 -0.0247 0.4503 0.1140
0.250 0.1959 0.01284 0.00375 -0.0250 0.4396 0.1686
0.500 0.2152 0.01040 0.00360 -0.0229 0.4319 1.0000
0.750 0.2440 0.01060 0.00360 -0.0227 0.4215 1.0000
1.000 0.2725 0.01083 0.00364 -0.0226 0.4098 1.0000
1.500 0.3296 0.01125 0.00382 -0.0224 0.3904 1.0000
1.750 0.3580 0.01154 0.00396 -0.0223 0.3834 1.0000
2.000 0.3867 0.01171 0.00412 -0.0222 0.3754 1.0000
2.250 0.4149 0.01200 0.00428 -0.0220 0.3671 1.0000
2.500 0.4434 0.01211 0.00440 -0.0219 0.3564 1.0000
2.750 0.4717 0.01228 0.00452 -0.0218 0.3449 1.0000
3.000 0.4998 0.01249 0.00465 -0.0216 0.3343 1.0000
3.250 0.5282 0.01260 0.00478 -0.0215 0.3235 1.0000
3.500 0.5564 0.01270 0.00488 -0.0214 0.3106 1.0000
3.750 0.5846 0.01274 0.00494 -0.0212 0.2957 1.0000
4.000 0.6129 0.01281 0.00503 -0.0211 0.2817 1.0000
4.250 0.6412 0.01285 0.00511 -0.0209 0.2656 1.0000
4.500 0.6695 0.01288 0.00516 -0.0208 0.2451 1.0000
4.750 0.6978 0.01297 0.00522 -0.0207 0.2158 1.0000
5.000 0.7255 0.01331 0.00538 -0.0207 0.1766 1.0000
5.250 0.7527 0.01406 0.00588 -0.0207 0.1314 1.0000
5.500 0.7798 0.01506 0.00663 -0.0208 0.0878 1.0000
5.750 0.8072 0.01583 0.00732 -0.0207 0.0743 1.0000
6.000 0.8346 0.01650 0.00802 -0.0205 0.0686 1.0000
6.250 0.8610 0.01746 0.00895 -0.0204 0.0646 1.0000
6.500 0.8878 0.01820 0.00977 -0.0201 0.0622 1.0000
6.750 0.9143 0.01900 0.01063 -0.0199 0.0597 1.0000
7.000 0.9402 0.01993 0.01160 -0.0196 0.0579 1.0000
7.250 0.9656 0.02104 0.01274 -0.0192 0.0564 1.0000
7.500 0.9902 0.02254 0.01425 -0.0188 0.0552 1.0000
7.750 1.0148 0.02420 0.01601 -0.0184 0.0542 1.0000
8.000 1.0400 0.02541 0.01742 -0.0180 0.0533 1.0000
8.250 1.0647 0.02681 0.01903 -0.0176 0.0522 1.0000
8.500 1.0885 0.02856 0.02101 -0.0171 0.0515 1.0000
8.750 1.1113 0.03056 0.02328 -0.0166 0.0509 1.0000
9.000 1.1330 0.03270 0.02572 -0.0162 0.0501 1.0000
9.250 1.1537 0.03481 0.02807 -0.0158 0.0490 1.0000
9.500 1.1730 0.03715 0.03065 -0.0153 0.0481 1.0000
9.750 1.1889 0.04028 0.03414 -0.0149 0.0478 1.0000
10.000 1.2007 0.04409 0.03837 -0.0144 0.0477 1.0000
10.250 1.2082 0.04822 0.04290 -0.0141 0.0474 1.0000
10.500 1.2106 0.05269 0.04776 -0.0140 0.0472 1.0000
10.750 1.1240 0.06939 0.06561 -0.0216 0.0510 1.0000
11.000 1.0613 0.08894 0.08532 -0.0413 0.0532 1.0000
11.250 1.0402 0.09913 0.09554 -0.0470 0.0554 1.0000
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Polar data table (+)
Polar graphs
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