GOE 509 AIRFOIL (goe509-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 509 AIRFOIL (goe509-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.22 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe509-il-1000000-n5.txt Download as CSV file: xf-goe509-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 509 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6799 0.02884 0.02598 -0.1128 0.9681 0.0067
-12.000 -0.6743 0.02447 0.02124 -0.1130 0.9642 0.0069
-11.750 -0.6620 0.02231 0.01886 -0.1119 0.9608 0.0071
-11.500 -0.6505 0.02093 0.01731 -0.1098 0.9568 0.0072
-11.250 -0.6334 0.01978 0.01601 -0.1085 0.9534 0.0073
-11.000 -0.6123 0.01878 0.01490 -0.1078 0.9502 0.0076
-10.750 -0.5942 0.01798 0.01398 -0.1062 0.9463 0.0078
-10.500 -0.5768 0.01721 0.01310 -0.1045 0.9416 0.0080
-10.250 -0.5557 0.01652 0.01230 -0.1034 0.9375 0.0082
-10.000 -0.5336 0.01587 0.01153 -0.1024 0.9335 0.0085
-9.750 -0.5152 0.01528 0.01085 -0.1006 0.9264 0.0087
-9.500 -0.4933 0.01473 0.01020 -0.0994 0.9178 0.0089
-9.250 -0.4723 0.01420 0.00956 -0.0980 0.9019 0.0091
-9.000 -0.4483 0.01353 0.00863 -0.0972 0.8536 0.0096
-8.750 -0.4283 0.01321 0.00808 -0.0955 0.8202 0.0099
-8.250 -0.3837 0.01255 0.00717 -0.0931 0.7934 0.0107
-8.000 -0.3607 0.01223 0.00674 -0.0921 0.7837 0.0112
-7.750 -0.3372 0.01194 0.00634 -0.0911 0.7736 0.0116
-7.500 -0.3136 0.01164 0.00594 -0.0902 0.7638 0.0121
-7.000 -0.2655 0.01109 0.00526 -0.0884 0.7450 0.0135
-6.750 -0.2411 0.01089 0.00497 -0.0876 0.7370 0.0145
-6.500 -0.2159 0.01065 0.00468 -0.0869 0.7297 0.0152
-6.250 -0.1912 0.01045 0.00445 -0.0861 0.7219 0.0166
-6.000 -0.1659 0.01028 0.00422 -0.0855 0.7135 0.0178
-5.750 -0.1413 0.01014 0.00400 -0.0847 0.7041 0.0188
-5.500 -0.1158 0.00997 0.00381 -0.0840 0.6954 0.0202
-5.250 -0.0907 0.00986 0.00365 -0.0833 0.6865 0.0215
-5.000 -0.0652 0.00975 0.00349 -0.0827 0.6771 0.0228
-4.750 -0.0403 0.00963 0.00331 -0.0819 0.6662 0.0239
-4.500 -0.0157 0.00953 0.00316 -0.0811 0.6546 0.0252
-4.250 0.0093 0.00946 0.00304 -0.0804 0.6419 0.0266
-4.000 0.0342 0.00940 0.00291 -0.0796 0.6279 0.0279
-3.750 0.0589 0.00935 0.00279 -0.0788 0.6129 0.0286
-3.500 0.0829 0.00926 0.00261 -0.0779 0.5961 0.0300
-3.250 0.1068 0.00922 0.00250 -0.0770 0.5764 0.0315
-3.000 0.1299 0.00924 0.00241 -0.0759 0.5470 0.0327
-2.750 0.1504 0.00942 0.00236 -0.0743 0.4940 0.0340
-2.500 0.1724 0.00954 0.00232 -0.0730 0.4592 0.0349
-2.250 0.1952 0.00961 0.00226 -0.0719 0.4364 0.0362
-2.000 0.2197 0.00957 0.00218 -0.0710 0.4273 0.0383
-1.750 0.2444 0.00954 0.00212 -0.0703 0.4203 0.0403
-1.500 0.2692 0.00952 0.00207 -0.0696 0.4143 0.0423
-1.250 0.2942 0.00950 0.00202 -0.0689 0.4084 0.0447
-1.000 0.3188 0.00946 0.00198 -0.0681 0.4035 0.0493
-0.750 0.3435 0.00945 0.00195 -0.0673 0.3992 0.0531
-0.500 0.3686 0.00941 0.00192 -0.0667 0.3961 0.0598
-0.250 0.3935 0.00938 0.00190 -0.0660 0.3925 0.0667
0.000 0.4177 0.00936 0.00190 -0.0651 0.3879 0.0787
0.250 0.4415 0.00934 0.00190 -0.0643 0.3841 0.0951
0.500 0.4646 0.00921 0.00189 -0.0632 0.3813 0.1373
0.750 0.4866 0.00904 0.00192 -0.0620 0.3780 0.2147
1.000 0.5107 0.00903 0.00196 -0.0612 0.3742 0.2417
1.250 0.5348 0.00905 0.00201 -0.0604 0.3705 0.2609
1.500 0.5588 0.00910 0.00206 -0.0595 0.3668 0.2749
1.750 0.5837 0.00911 0.00209 -0.0589 0.3638 0.2872
2.000 0.6080 0.00914 0.00214 -0.0581 0.3592 0.2989
2.250 0.6315 0.00920 0.00219 -0.0572 0.3526 0.3093
2.500 0.6551 0.00923 0.00224 -0.0563 0.3463 0.3262
3.000 0.7020 0.00934 0.00236 -0.0545 0.3353 0.3472
3.250 0.7254 0.00938 0.00242 -0.0536 0.3285 0.3618
3.500 0.7475 0.00944 0.00249 -0.0524 0.3208 0.3843
3.750 0.7664 0.00946 0.00259 -0.0507 0.3048 0.4479
4.250 0.9090 0.00935 0.00350 -0.0713 0.2526 0.9761
4.500 0.9325 0.00986 0.00382 -0.0707 0.2206 0.9820
4.750 0.9569 0.01032 0.00413 -0.0704 0.1957 0.9862
5.000 0.9887 0.01071 0.00442 -0.0716 0.1793 0.9889
5.250 1.0193 0.01098 0.00464 -0.0725 0.1726 0.9913
5.500 1.0491 0.01122 0.00487 -0.0732 0.1678 0.9937
5.750 1.0830 0.01150 0.00510 -0.0749 0.1621 0.9955
6.000 1.1167 0.01173 0.00531 -0.0766 0.1572 0.9972
6.250 1.1491 0.01194 0.00552 -0.0780 0.1529 0.9985
6.500 1.1809 0.01219 0.00574 -0.0792 0.1484 0.9997
6.750 1.2034 0.01245 0.00597 -0.0784 0.1435 1.0000
7.000 1.2217 0.01263 0.00618 -0.0766 0.1404 1.0000
7.250 1.2372 0.01293 0.00643 -0.0743 0.1320 1.0000
7.500 1.2477 0.01329 0.00672 -0.0711 0.1178 1.0000
7.750 1.2493 0.01393 0.00719 -0.0661 0.0892 1.0000
8.000 1.2582 0.01435 0.00758 -0.0626 0.0792 1.0000
8.250 1.2692 0.01475 0.00796 -0.0596 0.0727 1.0000
8.500 1.2828 0.01506 0.00829 -0.0571 0.0680 1.0000
8.750 1.2822 0.01603 0.00910 -0.0523 0.0377 1.0000
9.000 1.2938 0.01652 0.00958 -0.0496 0.0339 1.0000
9.250 1.3067 0.01695 0.01004 -0.0472 0.0313 1.0000
9.500 1.3203 0.01739 0.01051 -0.0450 0.0300 1.0000
9.750 1.3335 0.01785 0.01101 -0.0428 0.0291 1.0000
10.000 1.3458 0.01838 0.01157 -0.0405 0.0279 1.0000
10.250 1.3578 0.01894 0.01217 -0.0383 0.0269 1.0000
10.500 1.3694 0.01956 0.01282 -0.0361 0.0258 1.0000
10.750 1.3821 0.02013 0.01343 -0.0341 0.0248 1.0000
11.000 1.3950 0.02071 0.01406 -0.0322 0.0242 1.0000
11.250 1.4074 0.02135 0.01474 -0.0304 0.0237 1.0000
11.500 1.4189 0.02206 0.01550 -0.0285 0.0229 1.0000
11.750 1.4296 0.02285 0.01633 -0.0266 0.0219 1.0000
12.000 1.4389 0.02377 0.01729 -0.0247 0.0208 1.0000
12.250 1.4483 0.02472 0.01829 -0.0230 0.0198 1.0000
12.500 1.4589 0.02564 0.01926 -0.0214 0.0190 1.0000
12.750 1.4685 0.02666 0.02033 -0.0199 0.0179 1.0000
13.000 1.4766 0.02784 0.02152 -0.0185 0.0163 1.0000
13.250 1.4842 0.02910 0.02282 -0.0170 0.0149 1.0000
13.500 1.4913 0.03046 0.02422 -0.0157 0.0139 1.0000
13.750 1.4970 0.03198 0.02578 -0.0144 0.0129 1.0000
14.000 1.5020 0.03359 0.02744 -0.0132 0.0120 1.0000
14.250 1.5062 0.03534 0.02925 -0.0121 0.0108 1.0000
14.500 1.5095 0.03725 0.03122 -0.0111 0.0102 1.0000
14.750 1.5111 0.03938 0.03341 -0.0101 0.0095 1.0000
15.000 1.5128 0.04157 0.03567 -0.0094 0.0092 1.0000
15.250 1.5136 0.04392 0.03810 -0.0087 0.0086 1.0000
15.500 1.5131 0.04651 0.04076 -0.0082 0.0082 1.0000
15.750 1.5109 0.04936 0.04370 -0.0078 0.0079 1.0000
16.000 1.5077 0.05241 0.04682 -0.0077 0.0075 1.0000
16.250 1.5021 0.05588 0.05038 -0.0077 0.0071 1.0000
16.500 1.4981 0.05928 0.05388 -0.0079 0.0069 1.0000
16.750 1.4926 0.06296 0.05765 -0.0083 0.0067 1.0000
17.000 1.4854 0.06696 0.06175 -0.0088 0.0065 1.0000
17.250 1.4777 0.07114 0.06603 -0.0096 0.0063 1.0000
17.500 1.4686 0.07561 0.07060 -0.0105 0.0062 1.0000
17.750 1.4586 0.08020 0.07528 -0.0115 0.0060 1.0000
18.000 1.4478 0.08494 0.08012 -0.0126 0.0059 1.0000
18.250 1.4374 0.08967 0.08494 -0.0138 0.0059 1.0000
18.500 1.4243 0.09484 0.09021 -0.0152 0.0056 1.0000
18.750 1.4106 0.10014 0.09560 -0.0167 0.0054 1.0000
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