GOE 377 AIRFOIL (goe377-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 377 AIRFOIL (goe377-il) Reynolds number: 200,000 Max Cl/Cd: 77.91 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe377-il-200000.txt Download as CSV file: xf-goe377-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 377 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3693 0.08807 0.08471 -0.0237 1.0000 0.0299
-7.250 -0.3755 0.08593 0.08265 -0.0228 1.0000 0.0307
-7.000 -0.3782 0.08352 0.08030 -0.0227 1.0000 0.0311
-6.750 -0.3808 0.08105 0.07787 -0.0229 1.0000 0.0322
-6.500 -0.3826 0.07868 0.07554 -0.0231 1.0000 0.0329
-6.250 -0.3821 0.07637 0.07322 -0.0242 1.0000 0.0339
-6.000 -0.3763 0.07416 0.07099 -0.0266 1.0000 0.0347
-5.750 -0.3635 0.07217 0.06888 -0.0298 1.0000 0.0353
-5.500 -0.3547 0.06943 0.06607 -0.0301 1.0000 0.0355
-5.250 -0.3545 0.06368 0.06031 -0.0302 1.0000 0.0361
-5.000 -0.3541 0.06021 0.05690 -0.0279 1.0000 0.0370
-4.750 -0.3487 0.05756 0.05426 -0.0264 1.0000 0.0380
-4.500 -0.3198 0.05387 0.05047 -0.0301 0.9967 0.0398
-4.250 -0.2827 0.04976 0.04620 -0.0353 0.9923 0.0430
-4.000 -0.2255 0.04706 0.04289 -0.0420 0.9868 0.0481
-3.750 -0.1989 0.04025 0.03600 -0.0458 0.9834 0.0500
-3.500 -0.1726 0.03770 0.03342 -0.0474 0.9776 0.0535
-3.250 -0.1313 0.03429 0.02947 -0.0507 0.9728 0.0637
-3.000 -0.0972 0.03159 0.02676 -0.0534 0.9696 0.0679
-2.750 -0.0660 0.02916 0.02387 -0.0542 0.9623 0.0784
-2.500 -0.0284 0.02715 0.02155 -0.0565 0.9582 0.0920
-2.250 0.0018 0.02519 0.01958 -0.0580 0.9526 0.1090
-2.000 0.0355 0.02379 0.01793 -0.0594 0.9467 0.1350
-1.750 0.0819 0.01863 0.01149 -0.0586 0.9446 0.0644
-1.500 0.1204 0.01714 0.00975 -0.0603 0.9405 0.0650
-1.250 0.1550 0.01626 0.00880 -0.0614 0.9336 0.0697
-1.000 0.2025 0.01516 0.00754 -0.0648 0.9300 0.0732
-0.750 0.2418 0.01432 0.00663 -0.0665 0.9214 0.0759
-0.500 0.2844 0.01320 0.00562 -0.0691 0.9157 0.0834
-0.250 0.3157 0.01268 0.00507 -0.0693 0.9056 0.0898
0.000 0.3488 0.01200 0.00447 -0.0699 0.8970 0.1026
0.250 0.3722 0.01039 0.00407 -0.0690 0.8871 0.4623
0.500 0.4753 0.00899 0.00364 -0.0847 0.8859 1.0000
0.750 0.5018 0.00892 0.00347 -0.0839 0.8713 1.0000
1.000 0.5266 0.00889 0.00335 -0.0828 0.8551 1.0000
1.250 0.5512 0.00886 0.00325 -0.0817 0.8378 1.0000
1.500 0.5762 0.00884 0.00316 -0.0807 0.8198 1.0000
1.750 0.6014 0.00884 0.00308 -0.0797 0.8008 1.0000
2.000 0.6254 0.00888 0.00305 -0.0786 0.7795 1.0000
2.250 0.6499 0.00895 0.00301 -0.0775 0.7574 1.0000
2.500 0.6739 0.00905 0.00303 -0.0763 0.7333 1.0000
2.750 0.6973 0.00919 0.00307 -0.0751 0.7077 1.0000
3.000 0.7205 0.00936 0.00315 -0.0739 0.6816 1.0000
3.250 0.7431 0.00957 0.00324 -0.0725 0.6531 1.0000
3.500 0.7651 0.00982 0.00339 -0.0711 0.6225 1.0000
3.750 0.7866 0.01010 0.00354 -0.0696 0.5903 1.0000
4.000 0.8077 0.01041 0.00372 -0.0681 0.5568 1.0000
4.250 0.8286 0.01077 0.00394 -0.0666 0.5236 1.0000
4.500 0.8492 0.01114 0.00419 -0.0651 0.4895 1.0000
4.750 0.8698 0.01152 0.00450 -0.0636 0.4556 1.0000
5.000 0.8904 0.01193 0.00479 -0.0622 0.4250 1.0000
5.250 0.9111 0.01235 0.00512 -0.0608 0.3967 1.0000
5.500 0.9314 0.01279 0.00546 -0.0594 0.3683 1.0000
5.750 0.9516 0.01324 0.00582 -0.0580 0.3406 1.0000
6.000 0.9718 0.01369 0.00623 -0.0567 0.3127 1.0000
6.250 0.9923 0.01412 0.00663 -0.0554 0.2860 1.0000
6.500 1.0124 0.01457 0.00704 -0.0541 0.2558 1.0000
6.750 1.0302 0.01523 0.00750 -0.0525 0.1972 1.0000
7.000 1.0314 0.01786 0.00904 -0.0486 0.0497 1.0000
7.250 1.0465 0.01910 0.01037 -0.0462 0.0380 1.0000
7.500 1.0599 0.02036 0.01176 -0.0438 0.0327 1.0000
7.750 1.0758 0.02133 0.01284 -0.0418 0.0296 1.0000
8.000 1.0890 0.02255 0.01414 -0.0394 0.0274 1.0000
8.250 1.1001 0.02404 0.01569 -0.0368 0.0262 1.0000
8.500 1.1110 0.02605 0.01774 -0.0342 0.0252 1.0000
8.750 1.1284 0.02893 0.02069 -0.0327 0.0246 1.0000
9.000 1.1481 0.03065 0.02257 -0.0314 0.0241 1.0000
9.250 1.1646 0.03184 0.02402 -0.0296 0.0224 1.0000
9.500 1.1834 0.03441 0.02684 -0.0283 0.0224 1.0000
9.750 1.1989 0.03738 0.03013 -0.0266 0.0224 1.0000
10.000 1.2099 0.04071 0.03381 -0.0244 0.0228 1.0000
10.250 1.2160 0.04453 0.03797 -0.0220 0.0234 1.0000
10.500 1.2259 0.05031 0.04400 -0.0207 0.0248 1.0000
10.750 1.2140 0.05204 0.04650 -0.0145 0.0285 1.0000
11.000 1.1967 0.05675 0.05157 -0.0103 0.0312 1.0000
11.250 1.1066 0.04975 0.04495 -0.0013 0.0291 1.0000
11.500 1.0823 0.05437 0.04983 0.0009 0.0300 1.0000
11.750 1.0581 0.05923 0.05489 0.0019 0.0305 1.0000
12.000 1.0336 0.06449 0.06035 0.0018 0.0308 1.0000
12.250 1.0086 0.07018 0.06621 0.0006 0.0308 1.0000
12.500 0.9824 0.07650 0.07269 -0.0016 0.0306 1.0000
12.750 0.9567 0.08324 0.07959 -0.0048 0.0303 1.0000
13.000 0.9306 0.09050 0.08699 -0.0090 0.0299 1.0000
13.250 0.9038 0.09841 0.09503 -0.0140 0.0294 1.0000
13.500 0.8762 0.10697 0.10369 -0.0197 0.0290 1.0000
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Polar data table (+)
Polar graphs
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