GOE 701 AIRFOIL (goe701-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 701 AIRFOIL (goe701-il) Reynolds number: 500,000 Max Cl/Cd: 108.69 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe701-il-500000.txt Download as CSV file: xf-goe701-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 701 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.3322 0.14135 0.13887 -0.0388 1.0000 0.0340
-13.250 -0.9040 0.03967 0.03663 -0.0929 0.9964 0.0319
-13.000 -0.8938 0.03439 0.03090 -0.0990 0.9911 0.0326
-12.750 -0.8738 0.03223 0.02868 -0.1010 0.9869 0.0336
-12.500 -0.8419 0.03167 0.02814 -0.1029 0.9847 0.0345
-12.250 -0.8114 0.03051 0.02686 -0.1054 0.9828 0.0357
-12.000 -0.7910 0.02907 0.02520 -0.1060 0.9778 0.0369
-11.750 -0.7674 0.02739 0.02324 -0.1074 0.9739 0.0381
-11.500 -0.7380 0.02630 0.02215 -0.1090 0.9717 0.0392
-11.250 -0.7029 0.02597 0.02182 -0.1109 0.9703 0.0403
-11.000 -0.6773 0.02517 0.02091 -0.1113 0.9662 0.0415
-10.750 -0.6524 0.02419 0.01974 -0.1117 0.9616 0.0427
-10.500 -0.6229 0.02306 0.01837 -0.1130 0.9590 0.0439
-10.250 -0.5912 0.02197 0.01727 -0.1147 0.9573 0.0453
-10.000 -0.5554 0.02146 0.01675 -0.1167 0.9562 0.0466
-9.750 -0.5194 0.02081 0.01599 -0.1188 0.9552 0.0481
-9.500 -0.4992 0.02023 0.01527 -0.1175 0.9479 0.0493
-9.250 -0.4674 0.01973 0.01459 -0.1185 0.9447 0.0503
-9.000 -0.4383 0.01816 0.01295 -0.1197 0.9419 0.0521
-8.750 -0.4040 0.01762 0.01238 -0.1212 0.9398 0.0535
-8.500 -0.3836 0.01721 0.01189 -0.1197 0.9316 0.0547
-8.250 -0.3534 0.01661 0.01118 -0.1202 0.9272 0.0561
-8.000 -0.3211 0.01606 0.01049 -0.1212 0.9237 0.0573
-7.750 -0.3017 0.01527 0.00957 -0.1196 0.9147 0.0585
-7.500 -0.2733 0.01452 0.00878 -0.1198 0.9094 0.0601
-7.250 -0.2483 0.01412 0.00833 -0.1192 0.9018 0.0613
-7.000 -0.2210 0.01372 0.00787 -0.1189 0.8949 0.0628
-6.750 -0.1935 0.01338 0.00743 -0.1188 0.8881 0.0645
-6.500 -0.1675 0.01306 0.00700 -0.1182 0.8802 0.0658
-6.250 -0.1406 0.01246 0.00632 -0.1180 0.8735 0.0675
-6.000 -0.1160 0.01210 0.00595 -0.1172 0.8651 0.0694
-5.750 -0.0873 0.01188 0.00566 -0.1173 0.8586 0.0716
-5.500 -0.0624 0.01169 0.00542 -0.1165 0.8503 0.0737
-5.250 -0.0338 0.01151 0.00513 -0.1164 0.8436 0.0756
-5.000 -0.0100 0.01113 0.00477 -0.1155 0.8357 0.0787
-4.750 0.0174 0.01100 0.00459 -0.1152 0.8289 0.0816
-4.500 0.0439 0.01089 0.00443 -0.1148 0.8217 0.0849
-4.250 0.0696 0.01068 0.00419 -0.1142 0.8146 0.0889
-4.000 0.0972 0.01061 0.00410 -0.1139 0.8082 0.0934
-3.750 0.1231 0.01056 0.00401 -0.1133 0.8009 0.0978
-3.500 0.1497 0.01034 0.00378 -0.1130 0.7946 0.1037
-3.250 0.1758 0.01031 0.00373 -0.1124 0.7878 0.1091
-3.000 0.2019 0.01018 0.00356 -0.1119 0.7811 0.1144
-2.750 0.2288 0.01010 0.00346 -0.1116 0.7749 0.1197
-2.500 0.2544 0.01004 0.00339 -0.1109 0.7679 0.1241
-2.250 0.2812 0.00996 0.00325 -0.1106 0.7616 0.1281
-2.000 0.3066 0.00983 0.00315 -0.1099 0.7549 0.1331
-1.750 0.3327 0.00978 0.00309 -0.1094 0.7480 0.1377
-1.500 0.3593 0.00977 0.00301 -0.1089 0.7408 0.1412
-1.250 0.3836 0.00961 0.00288 -0.1080 0.7322 0.1462
-1.000 0.4096 0.00957 0.00282 -0.1075 0.7243 0.1514
-0.750 0.4346 0.00953 0.00277 -0.1067 0.7156 0.1564
-0.500 0.4599 0.00946 0.00270 -0.1060 0.7074 0.1637
-0.250 0.4845 0.00943 0.00267 -0.1051 0.6973 0.1719
0.000 0.5090 0.00936 0.00262 -0.1043 0.6879 0.1813
0.250 0.5339 0.00933 0.00258 -0.1035 0.6790 0.1932
0.500 0.5589 0.00928 0.00257 -0.1028 0.6711 0.2087
0.750 0.5834 0.00922 0.00255 -0.1020 0.6627 0.2262
1.000 0.6076 0.00915 0.00255 -0.1011 0.6539 0.2473
1.250 0.6313 0.00909 0.00255 -0.1002 0.6448 0.2777
1.500 0.6538 0.00891 0.00261 -0.0990 0.6356 0.3522
1.750 0.6635 0.00806 0.00267 -0.0954 0.6274 0.6767
2.000 0.7861 0.00792 0.00312 -0.1154 0.6131 0.9911
2.250 0.8429 0.00804 0.00316 -0.1217 0.5998 1.0000
2.500 0.8634 0.00815 0.00321 -0.1201 0.5883 1.0000
2.750 0.8833 0.00828 0.00326 -0.1184 0.5769 1.0000
3.000 0.9035 0.00839 0.00333 -0.1167 0.5647 1.0000
3.250 0.9233 0.00852 0.00341 -0.1150 0.5526 1.0000
3.500 0.9423 0.00867 0.00350 -0.1131 0.5398 1.0000
3.750 0.9606 0.00885 0.00361 -0.1110 0.5259 1.0000
4.000 0.9782 0.00903 0.00373 -0.1089 0.5113 1.0000
4.250 0.9956 0.00923 0.00386 -0.1067 0.4960 1.0000
4.500 1.0128 0.00943 0.00400 -0.1045 0.4804 1.0000
4.750 1.0289 0.00966 0.00416 -0.1020 0.4637 1.0000
5.000 1.0440 0.00991 0.00433 -0.0994 0.4449 1.0000
5.250 1.0585 0.01018 0.00452 -0.0967 0.4244 1.0000
5.500 1.0714 0.01051 0.00474 -0.0937 0.4023 1.0000
5.750 1.0817 0.01088 0.00499 -0.0902 0.3784 1.0000
6.000 1.0894 0.01127 0.00526 -0.0862 0.3533 1.0000
6.250 1.0972 0.01169 0.00555 -0.0823 0.3304 1.0000
6.500 1.1074 0.01212 0.00587 -0.0789 0.3093 1.0000
6.750 1.1190 0.01255 0.00620 -0.0759 0.2926 1.0000
7.000 1.1321 0.01296 0.00655 -0.0732 0.2795 1.0000
7.250 1.1449 0.01342 0.00693 -0.0706 0.2675 1.0000
7.500 1.1606 0.01379 0.00728 -0.0685 0.2583 1.0000
7.750 1.1752 0.01422 0.00768 -0.0663 0.2507 1.0000
8.000 1.1913 0.01460 0.00806 -0.0643 0.2428 1.0000
8.250 1.2056 0.01508 0.00850 -0.0622 0.2358 1.0000
8.500 1.2230 0.01544 0.00888 -0.0605 0.2294 1.0000
8.750 1.2377 0.01594 0.00936 -0.0585 0.2238 1.0000
9.000 1.2540 0.01637 0.00981 -0.0568 0.2185 1.0000
9.250 1.2710 0.01679 0.01026 -0.0553 0.2132 1.0000
9.500 1.2847 0.01738 0.01082 -0.0533 0.2073 1.0000
9.750 1.3019 0.01781 0.01129 -0.0519 0.2021 1.0000
10.000 1.3180 0.01831 0.01182 -0.0504 0.1965 1.0000
10.250 1.3311 0.01898 0.01246 -0.0485 0.1898 1.0000
10.500 1.3488 0.01942 0.01296 -0.0473 0.1843 1.0000
10.750 1.3627 0.02009 0.01362 -0.0457 0.1778 1.0000
11.000 1.3782 0.02069 0.01425 -0.0443 0.1713 1.0000
11.250 1.3915 0.02143 0.01498 -0.0427 0.1630 1.0000
11.500 1.4056 0.02214 0.01571 -0.0413 0.1544 1.0000
11.750 1.4171 0.02305 0.01658 -0.0397 0.1446 1.0000
12.000 1.4264 0.02412 0.01760 -0.0380 0.1309 1.0000
12.250 1.4329 0.02542 0.01882 -0.0361 0.1149 1.0000
12.500 1.4343 0.02714 0.02042 -0.0338 0.0964 1.0000
12.750 1.4338 0.02905 0.02222 -0.0316 0.0773 1.0000
13.000 1.4210 0.03203 0.02495 -0.0288 0.0439 1.0000
13.250 1.4170 0.03444 0.02733 -0.0267 0.0361 1.0000
13.500 1.4193 0.03642 0.02936 -0.0253 0.0336 1.0000
13.750 1.4198 0.03863 0.03164 -0.0239 0.0317 1.0000
14.000 1.4223 0.04074 0.03384 -0.0228 0.0303 1.0000
14.250 1.4246 0.04291 0.03610 -0.0218 0.0292 1.0000
14.500 1.4244 0.04540 0.03868 -0.0209 0.0282 1.0000
14.750 1.4197 0.04845 0.04181 -0.0201 0.0272 1.0000
15.000 1.4108 0.05207 0.04553 -0.0194 0.0264 1.0000
15.250 1.4123 0.05465 0.04822 -0.0191 0.0258 1.0000
15.500 1.4107 0.05765 0.05132 -0.0188 0.0253 1.0000
15.750 1.4083 0.06083 0.05460 -0.0187 0.0247 1.0000
16.000 1.4027 0.06448 0.05836 -0.0188 0.0241 1.0000
16.250 1.3965 0.06829 0.06227 -0.0190 0.0237 1.0000
16.500 1.3885 0.07245 0.06652 -0.0195 0.0233 1.0000
16.750 1.3777 0.07705 0.07122 -0.0202 0.0229 1.0000
17.000 1.3639 0.08216 0.07642 -0.0211 0.0225 1.0000
17.250 1.3464 0.08789 0.08225 -0.0223 0.0221 1.0000
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Polar data table (+)
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