GOE 593 AIRFOIL (goe593-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 593 AIRFOIL (goe593-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.1 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe593-il-1000000-n5.txt Download as CSV file: xf-goe593-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 593 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
------ -------- --------- --------- -------- -------- --------
-15.250 -1.0205 0.03915 0.03640 -0.0955 1.0000 0.0078
-15.000 -1.0634 0.03488 0.03195 -0.0933 1.0000 0.0078
-14.750 -1.0636 0.03196 0.02884 -0.0939 0.9975 0.0079
-14.500 -1.0478 0.02961 0.02632 -0.0956 0.9951 0.0081
-14.250 -1.0320 0.02767 0.02422 -0.0962 0.9927 0.0081
-14.000 -1.0139 0.02608 0.02247 -0.0966 0.9899 0.0083
-13.750 -0.9917 0.02473 0.02099 -0.0973 0.9878 0.0084
-13.500 -0.9686 0.02321 0.01933 -0.0983 0.9860 0.0087
-13.250 -0.9484 0.02204 0.01805 -0.0982 0.9827 0.0089
-13.000 -0.9261 0.02098 0.01690 -0.0982 0.9792 0.0092
-12.750 -0.9001 0.02004 0.01587 -0.0988 0.9769 0.0096
-12.500 -0.8722 0.01916 0.01489 -0.0997 0.9753 0.0099
-12.250 -0.8536 0.01845 0.01410 -0.0984 0.9691 0.0102
-12.000 -0.8274 0.01775 0.01331 -0.0986 0.9659 0.0106
-11.750 -0.7994 0.01706 0.01253 -0.0992 0.9638 0.0109
-11.500 -0.7795 0.01639 0.01179 -0.0980 0.9567 0.0114
-11.250 -0.7510 0.01575 0.01109 -0.0986 0.9534 0.0119
-11.000 -0.7195 0.01517 0.01045 -0.0997 0.9510 0.0125
-10.750 -0.6918 0.01467 0.00988 -0.1000 0.9455 0.0130
-10.500 -0.6586 0.01416 0.00929 -0.1014 0.9418 0.0136
-10.250 -0.6232 0.01363 0.00871 -0.1033 0.9386 0.0143
-10.000 -0.5892 0.01323 0.00827 -0.1049 0.9341 0.0152
-9.750 -0.5560 0.01284 0.00782 -0.1062 0.9282 0.0160
-9.500 -0.5216 0.01249 0.00740 -0.1078 0.9226 0.0169
-9.250 -0.4919 0.01215 0.00701 -0.1083 0.9155 0.0177
-9.000 -0.4614 0.01190 0.00673 -0.1089 0.9085 0.0186
-8.750 -0.4335 0.01167 0.00644 -0.1090 0.9013 0.0194
-8.500 -0.4063 0.01144 0.00614 -0.1089 0.8938 0.0201
-8.250 -0.3794 0.01123 0.00586 -0.1087 0.8873 0.0207
-8.000 -0.3543 0.01096 0.00555 -0.1082 0.8798 0.0216
-7.750 -0.3280 0.01076 0.00530 -0.1078 0.8727 0.0223
-7.500 -0.3026 0.01058 0.00510 -0.1073 0.8653 0.0231
-7.250 -0.2767 0.01041 0.00486 -0.1068 0.8581 0.0238
-7.000 -0.2512 0.01024 0.00464 -0.1063 0.8507 0.0246
-6.750 -0.2256 0.01009 0.00443 -0.1057 0.8426 0.0251
-6.500 -0.2006 0.00988 0.00416 -0.1051 0.8345 0.0256
-6.250 -0.1761 0.00964 0.00387 -0.1043 0.8260 0.0267
-6.000 -0.1509 0.00946 0.00367 -0.1037 0.8171 0.0275
-5.750 -0.1258 0.00931 0.00346 -0.1030 0.8075 0.0282
-5.500 -0.1007 0.00918 0.00328 -0.1024 0.7971 0.0291
-5.250 -0.0756 0.00904 0.00309 -0.1017 0.7870 0.0297
-5.000 -0.0507 0.00893 0.00291 -0.1009 0.7761 0.0302
-4.750 -0.0258 0.00883 0.00274 -0.1002 0.7645 0.0308
-4.500 -0.0014 0.00867 0.00252 -0.0994 0.7520 0.0321
-4.250 0.0228 0.00858 0.00237 -0.0985 0.7373 0.0331
-4.000 0.0465 0.00852 0.00223 -0.0975 0.7194 0.0341
-3.750 0.0706 0.00847 0.00210 -0.0966 0.7031 0.0352
-3.500 0.0954 0.00842 0.00199 -0.0958 0.6897 0.0364
-3.250 0.1205 0.00835 0.00188 -0.0951 0.6792 0.0382
-3.000 0.1456 0.00827 0.00178 -0.0945 0.6690 0.0413
-2.750 0.1712 0.00821 0.00169 -0.0939 0.6595 0.0446
-2.500 0.1960 0.00814 0.00160 -0.0932 0.6491 0.0521
-2.000 0.2456 0.00796 0.00148 -0.0918 0.6269 0.0855
-1.750 0.2706 0.00793 0.00144 -0.0911 0.6164 0.0986
-1.500 0.2959 0.00791 0.00141 -0.0905 0.6050 0.1084
-1.250 0.3216 0.00789 0.00139 -0.0899 0.5955 0.1180
-1.000 0.3467 0.00788 0.00136 -0.0893 0.5854 0.1282
-0.750 0.3721 0.00787 0.00135 -0.0887 0.5740 0.1387
-0.500 0.3973 0.00784 0.00133 -0.0881 0.5636 0.1563
-0.250 0.4213 0.00776 0.00134 -0.0873 0.5516 0.1953
0.000 0.4442 0.00766 0.00136 -0.0863 0.5360 0.2617
0.250 0.4675 0.00759 0.00138 -0.0853 0.5205 0.3125
0.500 0.4896 0.00749 0.00141 -0.0842 0.5030 0.3831
0.750 0.5105 0.00734 0.00146 -0.0828 0.4856 0.4868
1.000 0.5319 0.00729 0.00152 -0.0815 0.4670 0.5564
1.250 0.5521 0.00721 0.00160 -0.0799 0.4491 0.6367
1.500 0.5711 0.00714 0.00169 -0.0780 0.4315 0.7186
1.750 0.5869 0.00700 0.00180 -0.0753 0.4148 0.8246
2.000 0.6249 0.00702 0.00202 -0.0775 0.3947 0.9357
2.250 0.6857 0.00731 0.00221 -0.0850 0.3736 0.9640
2.500 0.7255 0.00753 0.00235 -0.0877 0.3588 0.9755
2.750 0.7631 0.00775 0.00250 -0.0900 0.3460 0.9875
3.250 0.8330 0.00813 0.00275 -0.0933 0.3240 0.9975
3.500 0.8686 0.00832 0.00288 -0.0952 0.3143 0.9998
3.750 0.8904 0.00848 0.00299 -0.0940 0.3046 1.0000
4.000 0.9106 0.00862 0.00311 -0.0924 0.2963 1.0000
4.250 0.9302 0.00880 0.00323 -0.0907 0.2876 1.0000
4.500 0.9504 0.00895 0.00335 -0.0892 0.2786 1.0000
4.750 0.9699 0.00914 0.00350 -0.0875 0.2693 1.0000
5.000 0.9902 0.00930 0.00363 -0.0859 0.2614 1.0000
5.250 1.0100 0.00949 0.00378 -0.0843 0.2543 1.0000
5.500 1.0308 0.00963 0.00392 -0.0829 0.2489 1.0000
5.750 1.0507 0.00982 0.00409 -0.0814 0.2422 1.0000
6.000 1.0710 0.01000 0.00425 -0.0799 0.2357 1.0000
6.250 1.0907 0.01021 0.00443 -0.0783 0.2283 1.0000
6.500 1.1104 0.01041 0.00462 -0.0767 0.2220 1.0000
6.750 1.1294 0.01059 0.00480 -0.0750 0.2164 1.0000
7.000 1.1460 0.01084 0.00500 -0.0728 0.2081 1.0000
7.250 1.1635 0.01106 0.00521 -0.0708 0.1996 1.0000
7.500 1.1810 0.01130 0.00543 -0.0689 0.1924 1.0000
7.750 1.1984 0.01157 0.00567 -0.0669 0.1832 1.0000
8.000 1.2155 0.01187 0.00594 -0.0650 0.1722 1.0000
8.250 1.2314 0.01224 0.00625 -0.0629 0.1585 1.0000
8.500 1.2443 0.01277 0.00667 -0.0604 0.1382 1.0000
9.000 1.2604 0.01439 0.00795 -0.0540 0.0817 1.0000
9.250 1.2737 0.01498 0.00848 -0.0517 0.0702 1.0000
9.500 1.2884 0.01551 0.00899 -0.0497 0.0626 1.0000
9.750 1.3029 0.01607 0.00952 -0.0478 0.0568 1.0000
10.000 1.3197 0.01651 0.00998 -0.0463 0.0539 1.0000
10.250 1.3358 0.01700 0.01048 -0.0447 0.0510 1.0000
10.500 1.3505 0.01757 0.01106 -0.0430 0.0479 1.0000
10.750 1.3661 0.01811 0.01163 -0.0414 0.0454 1.0000
11.000 1.3824 0.01863 0.01218 -0.0400 0.0439 1.0000
11.250 1.3972 0.01923 0.01280 -0.0385 0.0416 1.0000
11.500 1.4105 0.01995 0.01352 -0.0369 0.0389 1.0000
11.750 1.4251 0.02060 0.01421 -0.0355 0.0373 1.0000
12.000 1.4393 0.02129 0.01494 -0.0341 0.0353 1.0000
12.250 1.4516 0.02212 0.01578 -0.0325 0.0326 1.0000
12.500 1.4634 0.02301 0.01668 -0.0310 0.0296 1.0000
12.750 1.4740 0.02400 0.01768 -0.0295 0.0265 1.0000
13.000 1.4841 0.02504 0.01875 -0.0280 0.0234 1.0000
13.250 1.4905 0.02639 0.02010 -0.0263 0.0189 1.0000
13.500 1.4967 0.02780 0.02152 -0.0247 0.0161 1.0000
13.750 1.5030 0.02926 0.02302 -0.0233 0.0143 1.0000
14.000 1.5100 0.03071 0.02452 -0.0220 0.0132 1.0000
14.250 1.5154 0.03233 0.02619 -0.0208 0.0121 1.0000
14.500 1.5199 0.03410 0.02802 -0.0196 0.0112 1.0000
14.750 1.5252 0.03585 0.02984 -0.0187 0.0106 1.0000
15.000 1.5299 0.03772 0.03179 -0.0178 0.0102 1.0000
15.250 1.5330 0.03980 0.03393 -0.0171 0.0096 1.0000
15.500 1.5351 0.04205 0.03625 -0.0164 0.0092 1.0000
15.750 1.5359 0.04451 0.03878 -0.0159 0.0088 1.0000
16.000 1.5358 0.04714 0.04149 -0.0155 0.0085 1.0000
16.250 1.5364 0.04975 0.04418 -0.0153 0.0081 1.0000
16.500 1.5354 0.05264 0.04715 -0.0151 0.0078 1.0000
16.750 1.5338 0.05565 0.05026 -0.0152 0.0076 1.0000
17.000 1.5305 0.05895 0.05364 -0.0154 0.0074 1.0000
17.250 1.5259 0.06248 0.05726 -0.0157 0.0073 1.0000
17.500 1.5193 0.06637 0.06125 -0.0162 0.0071 1.0000
17.750 1.5115 0.07052 0.06549 -0.0169 0.0069 1.0000
18.000 1.5008 0.07512 0.07019 -0.0179 0.0066 1.0000
18.250 1.4903 0.07982 0.07500 -0.0190 0.0065 1.0000
18.500 1.4813 0.08438 0.07966 -0.0201 0.0065 1.0000
18.750 1.4715 0.08913 0.08452 -0.0215 0.0064 1.0000
19.000 1.4603 0.09410 0.08960 -0.0229 0.0063 1.0000
19.250 1.4487 0.09921 0.09480 -0.0245 0.0062 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 593 AIRFOIL (goe593-il)