GOE 101 AIRFOIL (goe101-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: GOE 101 AIRFOIL (goe101-il) Reynolds number: 500,000 Max Cl/Cd: 100.46 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe101-il-500000-n5.txt Download as CSV file: xf-goe101-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 101 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3636 0.08245 0.08036 -0.0206 1.0000 0.0062
-7.250 -0.3633 0.07950 0.07745 -0.0215 1.0000 0.0062
-7.000 -0.3599 0.07607 0.07405 -0.0236 1.0000 0.0062
-6.750 -0.3426 0.07125 0.06923 -0.0298 0.9909 0.0062
-6.500 -0.3156 0.06525 0.06319 -0.0389 0.9806 0.0062
-6.250 -0.2833 0.05820 0.05607 -0.0495 0.9690 0.0064
-6.000 -0.2505 0.05295 0.05073 -0.0576 0.9557 0.0066
-5.750 -0.2174 0.04964 0.04732 -0.0633 0.9408 0.0073
-5.500 -0.1856 0.04469 0.04219 -0.0691 0.9206 0.0081
-5.250 -0.1577 0.03865 0.03588 -0.0737 0.8973 0.0083
-5.000 -0.1321 0.03089 0.02766 -0.0768 0.8737 0.0090
-4.750 -0.1083 0.02400 0.02014 -0.0778 0.8507 0.0098
-4.500 -0.0838 0.02279 0.01869 -0.0775 0.8242 0.0106
-4.250 -0.0611 0.01490 0.00969 -0.0768 0.8033 0.0143
-4.000 -0.0353 0.01518 0.00985 -0.0764 0.7781 0.0149
-3.750 -0.0095 0.01540 0.00994 -0.0760 0.7546 0.0158
-3.500 0.0166 0.01509 0.00942 -0.0756 0.7333 0.0179
-3.250 0.0428 0.01407 0.00802 -0.0751 0.7134 0.0206
-3.000 0.0696 0.01410 0.00783 -0.0746 0.6941 0.0217
-2.750 0.0950 0.01290 0.00642 -0.0744 0.6761 0.0236
-2.500 0.1214 0.01252 0.00588 -0.0741 0.6585 0.0248
-2.250 0.1480 0.01220 0.00542 -0.0739 0.6412 0.0264
-2.000 0.1746 0.01187 0.00495 -0.0735 0.6241 0.0280
-1.750 0.2012 0.01148 0.00440 -0.0732 0.6073 0.0289
-1.500 0.2278 0.01114 0.00392 -0.0729 0.5906 0.0294
-1.250 0.2544 0.01083 0.00349 -0.0726 0.5744 0.0297
-1.000 0.2811 0.01065 0.00320 -0.0723 0.5594 0.0303
-0.750 0.3078 0.01042 0.00288 -0.0720 0.5465 0.0306
-0.500 0.3344 0.01015 0.00253 -0.0717 0.5347 0.0304
-0.250 0.3612 0.00993 0.00224 -0.0715 0.5242 0.0303
0.000 0.3880 0.00975 0.00201 -0.0713 0.5145 0.0303
0.500 0.4418 0.00953 0.00167 -0.0708 0.4942 0.0304
0.750 0.4687 0.00949 0.00156 -0.0706 0.4824 0.0305
1.000 0.4956 0.00947 0.00147 -0.0704 0.4707 0.0309
1.250 0.5225 0.00948 0.00142 -0.0702 0.4606 0.0314
1.500 0.5497 0.00946 0.00137 -0.0700 0.4523 0.0331
2.000 0.6040 0.00949 0.00138 -0.0697 0.4390 0.0422
2.250 0.6338 0.00752 0.00160 -0.0708 0.4318 1.0000
2.500 0.6607 0.00762 0.00167 -0.0706 0.4251 1.0000
2.750 0.6874 0.00776 0.00175 -0.0704 0.4163 1.0000
3.000 0.7141 0.00788 0.00183 -0.0701 0.4054 1.0000
3.250 0.7407 0.00801 0.00193 -0.0699 0.3950 1.0000
3.500 0.7674 0.00815 0.00204 -0.0697 0.3875 1.0000
3.750 0.7943 0.00826 0.00216 -0.0695 0.3808 1.0000
4.000 0.8209 0.00840 0.00230 -0.0693 0.3727 1.0000
4.250 0.8476 0.00853 0.00245 -0.0691 0.3638 1.0000
4.500 0.8740 0.00870 0.00260 -0.0688 0.3503 1.0000
4.750 0.8993 0.00899 0.00278 -0.0685 0.3172 1.0000
5.250 0.9429 0.01055 0.00365 -0.0670 0.1793 1.0000
5.500 0.9663 0.01111 0.00406 -0.0665 0.1454 1.0000
5.750 0.9877 0.01196 0.00459 -0.0657 0.0880 1.0000
6.000 1.0116 0.01245 0.00503 -0.0652 0.0699 1.0000
6.250 1.0312 0.01352 0.00583 -0.0642 0.0183 1.0000
6.500 1.0548 0.01404 0.00641 -0.0635 0.0127 1.0000
6.750 1.0787 0.01447 0.00691 -0.0629 0.0108 1.0000
7.000 1.1020 0.01497 0.00750 -0.0623 0.0095 1.0000
7.250 1.1241 0.01561 0.00822 -0.0615 0.0083 1.0000
7.500 1.1443 0.01650 0.00926 -0.0604 0.0074 1.0000
7.750 1.1662 0.01711 0.00995 -0.0596 0.0069 1.0000
8.000 1.1878 0.01770 0.01060 -0.0588 0.0060 1.0000
8.250 1.2079 0.01844 0.01141 -0.0578 0.0056 1.0000
8.500 1.2264 0.01933 0.01238 -0.0566 0.0052 1.0000
8.750 1.2396 0.02073 0.01389 -0.0547 0.0049 1.0000
9.000 1.2558 0.02174 0.01502 -0.0532 0.0047 1.0000
9.250 1.2702 0.02287 0.01631 -0.0515 0.0045 1.0000
9.500 1.2827 0.02413 0.01769 -0.0495 0.0043 1.0000
9.750 1.2931 0.02550 0.01919 -0.0473 0.0041 1.0000
10.000 1.3026 0.02679 0.02060 -0.0450 0.0039 1.0000
10.250 1.3097 0.02802 0.02194 -0.0424 0.0038 1.0000
10.500 1.3173 0.02913 0.02315 -0.0402 0.0036 1.0000
10.750 1.3243 0.03034 0.02444 -0.0381 0.0034 1.0000
11.000 1.3284 0.03187 0.02607 -0.0360 0.0033 1.0000
11.250 1.3307 0.03369 0.02799 -0.0342 0.0032 1.0000
11.500 1.3292 0.03610 0.03054 -0.0324 0.0031 1.0000
11.750 1.3270 0.03884 0.03345 -0.0310 0.0030 1.0000
12.000 1.3272 0.04142 0.03622 -0.0301 0.0029 1.0000
12.250 1.3254 0.04440 0.03940 -0.0295 0.0029 1.0000
12.500 1.3219 0.04775 0.04294 -0.0292 0.0028 1.0000
12.750 1.3158 0.05161 0.04702 -0.0294 0.0028 1.0000
13.000 1.3076 0.05595 0.05158 -0.0300 0.0028 1.0000
13.250 1.2995 0.06042 0.05627 -0.0310 0.0028 1.0000
13.500 1.2878 0.06570 0.06178 -0.0326 0.0027 1.0000
13.750 1.2750 0.07135 0.06763 -0.0348 0.0027 1.0000
14.000 1.2625 0.07717 0.07363 -0.0373 0.0027 1.0000
14.250 1.2476 0.08374 0.08038 -0.0404 0.0027 1.0000
14.500 1.2309 0.09101 0.08785 -0.0440 0.0026 1.0000
14.750 1.2151 0.09849 0.09549 -0.0480 0.0026 1.0000
15.000 1.1985 0.10659 0.10375 -0.0526 0.0026 1.0000
15.250 1.1828 0.11486 0.11217 -0.0573 0.0027 1.0000
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Polar data table (+)
Polar graphs
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