GOE 459 AIRFOIL (goe459-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 459 AIRFOIL (goe459-il) Reynolds number: 200,000 Max Cl/Cd: 45.28 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe459-il-200000-n5.txt Download as CSV file: xf-goe459-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 459 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
------ -------- --------- --------- -------- -------- --------
-17.750 -0.8164 0.14236 0.13825 -0.0055 1.0000 0.0188
-17.500 -0.8710 0.12573 0.12144 -0.0139 1.0000 0.0185
-17.250 -0.9056 0.11438 0.10993 -0.0197 1.0000 0.0181
-17.000 -0.9362 0.10433 0.09974 -0.0250 1.0000 0.0179
-16.750 -0.9643 0.09505 0.09030 -0.0299 1.0000 0.0179
-16.500 -0.9881 0.08693 0.08201 -0.0342 1.0000 0.0177
-16.250 -1.0081 0.07969 0.07461 -0.0380 1.0000 0.0176
-16.000 -1.0271 0.07293 0.06768 -0.0416 1.0000 0.0180
-15.750 -1.0423 0.06715 0.06175 -0.0444 1.0000 0.0179
-15.500 -1.0549 0.06203 0.05646 -0.0467 1.0000 0.0183
-15.250 -1.0667 0.05730 0.05156 -0.0486 1.0000 0.0188
-15.000 -1.0759 0.05316 0.04726 -0.0500 1.0000 0.0191
-14.750 -1.0831 0.04950 0.04344 -0.0508 1.0000 0.0194
-14.500 -1.0902 0.04607 0.03992 -0.0514 1.0000 0.0202
-14.250 -1.0940 0.04323 0.03697 -0.0515 1.0000 0.0208
-14.000 -1.0961 0.04071 0.03436 -0.0511 1.0000 0.0218
-13.750 -1.0960 0.03855 0.03209 -0.0504 1.0000 0.0227
-13.500 -1.0950 0.03659 0.03001 -0.0493 1.0000 0.0239
-13.250 -1.0911 0.03502 0.02841 -0.0482 1.0000 0.0257
-13.000 -1.0861 0.03361 0.02691 -0.0468 1.0000 0.0276
-12.750 -1.0793 0.03241 0.02561 -0.0452 1.0000 0.0303
-12.500 -1.0701 0.03151 0.02464 -0.0437 1.0000 0.0332
-12.250 -1.0605 0.03058 0.02354 -0.0420 1.0000 0.0363
-12.000 -1.0524 0.02978 0.02269 -0.0400 1.0000 0.0383
-11.750 -1.0423 0.02912 0.02192 -0.0381 1.0000 0.0410
-11.500 -1.0312 0.02849 0.02110 -0.0360 1.0000 0.0434
-11.250 -1.0237 0.02767 0.02022 -0.0334 1.0000 0.0452
-11.000 -1.0159 0.02705 0.01955 -0.0307 1.0000 0.0471
-10.750 -1.0071 0.02649 0.01892 -0.0280 1.0000 0.0490
-10.500 -0.9979 0.02595 0.01827 -0.0251 1.0000 0.0509
-10.250 -0.9880 0.02549 0.01769 -0.0222 1.0000 0.0528
-10.000 -0.9766 0.02507 0.01712 -0.0195 1.0000 0.0541
-9.750 -0.9670 0.02412 0.01619 -0.0168 1.0000 0.0562
-9.500 -0.9557 0.02347 0.01552 -0.0142 1.0000 0.0582
-9.250 -0.9429 0.02294 0.01494 -0.0118 1.0000 0.0605
-9.000 -0.9290 0.02245 0.01437 -0.0095 1.0000 0.0629
-8.750 -0.9144 0.02199 0.01382 -0.0073 1.0000 0.0649
-8.500 -0.8992 0.02156 0.01328 -0.0051 1.0000 0.0663
-8.250 -0.8874 0.02080 0.01252 -0.0024 1.0000 0.0677
-8.000 -0.8752 0.02016 0.01187 0.0003 1.0000 0.0689
-7.750 -0.8624 0.01960 0.01129 0.0029 1.0000 0.0700
-7.500 -0.8490 0.01911 0.01074 0.0055 1.0000 0.0713
-7.250 -0.8353 0.01865 0.01025 0.0080 1.0000 0.0726
-7.000 -0.8214 0.01823 0.00978 0.0105 1.0000 0.0742
-6.750 -0.8071 0.01785 0.00935 0.0129 1.0000 0.0757
-6.500 -0.7925 0.01750 0.00895 0.0153 1.0000 0.0775
-6.250 -0.7659 0.01705 0.00847 0.0151 0.9976 0.0809
-6.000 -0.7336 0.01658 0.00802 0.0137 0.9936 0.0864
-5.750 -0.7023 0.01612 0.00758 0.0126 0.9889 0.0941
-5.500 -0.6679 0.01560 0.00718 0.0108 0.9843 0.1128
-5.250 -0.6365 0.01509 0.00677 0.0097 0.9774 0.1406
-5.000 -0.6018 0.01463 0.00641 0.0080 0.9722 0.1661
-4.750 -0.5738 0.01420 0.00607 0.0077 0.9647 0.1905
-4.500 -0.5409 0.01377 0.00577 0.0063 0.9603 0.2203
-4.250 -0.5152 0.01339 0.00551 0.0066 0.9521 0.2504
-4.000 -0.4830 0.01298 0.00522 0.0054 0.9473 0.2850
-3.750 -0.4578 0.01256 0.00496 0.0058 0.9390 0.3191
-3.500 -0.4270 0.01213 0.00470 0.0050 0.9335 0.3553
-3.250 -0.4002 0.01173 0.00449 0.0052 0.9257 0.3993
-3.000 -0.3698 0.01136 0.00433 0.0046 0.9192 0.4522
-2.750 -0.3382 0.01107 0.00418 0.0038 0.9128 0.4949
-2.500 -0.3082 0.01080 0.00404 0.0035 0.9046 0.5317
-2.250 -0.2754 0.01054 0.00392 0.0026 0.8977 0.5676
-2.000 -0.2458 0.01034 0.00384 0.0024 0.8885 0.6006
-1.750 -0.2138 0.01017 0.00375 0.0017 0.8799 0.6272
-1.500 -0.1809 0.01003 0.00366 0.0008 0.8704 0.6504
-1.250 -0.1509 0.00991 0.00360 0.0007 0.8581 0.6748
-1.000 -0.1200 0.00979 0.00354 0.0004 0.8445 0.6991
-0.750 -0.0896 0.00969 0.00348 0.0002 0.8284 0.7222
-0.500 -0.0598 0.00963 0.00345 0.0001 0.8120 0.7430
-0.250 -0.0297 0.00959 0.00341 0.0000 0.7943 0.7603
0.000 0.0000 0.00958 0.00339 0.0000 0.7765 0.7765
0.250 0.0297 0.00959 0.00341 0.0000 0.7603 0.7941
0.500 0.0598 0.00963 0.00345 -0.0001 0.7430 0.8120
0.750 0.0896 0.00969 0.00349 -0.0002 0.7223 0.8286
1.000 0.1200 0.00979 0.00354 -0.0004 0.6993 0.8443
1.250 0.1509 0.00991 0.00360 -0.0007 0.6750 0.8582
1.500 0.1810 0.01003 0.00367 -0.0009 0.6508 0.8704
1.750 0.2139 0.01017 0.00375 -0.0017 0.6274 0.8799
2.000 0.2457 0.01034 0.00383 -0.0023 0.5990 0.8886
2.500 0.3081 0.01080 0.00404 -0.0034 0.5309 0.9046
2.750 0.3382 0.01107 0.00418 -0.0038 0.4950 0.9128
3.000 0.3699 0.01136 0.00433 -0.0046 0.4532 0.9192
3.250 0.4003 0.01173 0.00449 -0.0052 0.3997 0.9257
3.500 0.4270 0.01213 0.00470 -0.0050 0.3553 0.9335
3.750 0.4578 0.01256 0.00496 -0.0058 0.3193 0.9390
4.250 0.5153 0.01338 0.00551 -0.0066 0.2513 0.9521
4.500 0.5411 0.01376 0.00577 -0.0063 0.2215 0.9603
4.750 0.5738 0.01419 0.00607 -0.0077 0.1907 0.9647
5.000 0.6019 0.01463 0.00640 -0.0080 0.1664 0.9722
5.250 0.6365 0.01509 0.00677 -0.0097 0.1403 0.9774
5.500 0.6680 0.01559 0.00718 -0.0108 0.1135 0.9843
5.750 0.7024 0.01612 0.00758 -0.0127 0.0943 0.9889
6.000 0.7337 0.01658 0.00802 -0.0138 0.0866 0.9936
6.250 0.7662 0.01704 0.00847 -0.0152 0.0812 0.9976
6.500 0.7924 0.01750 0.00894 -0.0153 0.0778 1.0000
6.750 0.8070 0.01785 0.00935 -0.0129 0.0758 1.0000
7.000 0.8213 0.01823 0.00978 -0.0105 0.0742 1.0000
7.250 0.8353 0.01865 0.01024 -0.0080 0.0728 1.0000
7.500 0.8491 0.01909 0.01073 -0.0055 0.0714 1.0000
7.750 0.8624 0.01960 0.01128 -0.0029 0.0701 1.0000
8.000 0.8753 0.02015 0.01186 -0.0003 0.0690 1.0000
8.250 0.8876 0.02078 0.01251 0.0024 0.0677 1.0000
8.500 0.8991 0.02156 0.01328 0.0051 0.0664 1.0000
8.750 0.9144 0.02199 0.01382 0.0073 0.0650 1.0000
9.000 0.9292 0.02243 0.01435 0.0095 0.0628 1.0000
9.250 0.9430 0.02291 0.01492 0.0118 0.0604 1.0000
9.500 0.9559 0.02346 0.01550 0.0142 0.0582 1.0000
9.750 0.9668 0.02412 0.01617 0.0168 0.0559 1.0000
10.000 0.9768 0.02503 0.01708 0.0195 0.0540 1.0000
10.250 0.9883 0.02545 0.01765 0.0222 0.0526 1.0000
10.500 0.9982 0.02596 0.01828 0.0251 0.0510 1.0000
10.750 1.0075 0.02649 0.01892 0.0279 0.0491 1.0000
11.000 1.0163 0.02704 0.01954 0.0307 0.0471 1.0000
11.250 1.0243 0.02769 0.02024 0.0334 0.0454 1.0000
11.500 1.0314 0.02851 0.02112 0.0359 0.0435 1.0000
11.750 1.0427 0.02913 0.02193 0.0380 0.0411 1.0000
12.000 1.0527 0.02981 0.02272 0.0400 0.0384 1.0000
12.250 1.0613 0.03055 0.02351 0.0419 0.0363 1.0000
12.500 1.0708 0.03150 0.02463 0.0436 0.0331 1.0000
12.750 1.0803 0.03237 0.02557 0.0451 0.0302 1.0000
13.000 1.0866 0.03362 0.02692 0.0467 0.0277 1.0000
13.250 1.0927 0.03494 0.02831 0.0480 0.0255 1.0000
13.500 1.0958 0.03659 0.03000 0.0492 0.0237 1.0000
13.750 1.0969 0.03854 0.03208 0.0502 0.0227 1.0000
14.000 1.0967 0.04073 0.03438 0.0510 0.0215 1.0000
14.250 1.0951 0.04320 0.03695 0.0513 0.0207 1.0000
14.500 1.0911 0.04608 0.03992 0.0513 0.0202 1.0000
14.750 1.0840 0.04952 0.04347 0.0507 0.0194 1.0000
15.000 1.0763 0.05326 0.04737 0.0498 0.0189 1.0000
15.250 1.0678 0.05732 0.05158 0.0484 0.0188 1.0000
15.500 1.0573 0.06187 0.05630 0.0466 0.0184 1.0000
15.750 1.0435 0.06717 0.06176 0.0442 0.0180 1.0000
16.000 1.0289 0.07288 0.06763 0.0414 0.0181 1.0000
16.250 1.0102 0.07959 0.07451 0.0379 0.0178 1.0000
16.500 0.9880 0.08725 0.08233 0.0338 0.0177 1.0000
16.750 0.9659 0.09511 0.09035 0.0296 0.0178 1.0000
17.000 0.9380 0.10437 0.09978 0.0247 0.0178 1.0000
17.250 0.9052 0.11494 0.11050 0.0191 0.0179 1.0000
17.500 0.8721 0.12597 0.12168 0.0135 0.0185 1.0000
17.750 0.8218 0.14159 0.13747 0.0056 0.0189 1.0000
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