GOE 701 AIRFOIL (goe701-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 701 AIRFOIL (goe701-il) Reynolds number: 200,000 Max Cl/Cd: 73.75 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe701-il-200000-n5.txt Download as CSV file: xf-goe701-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5356 0.03557 0.03084 -0.1088 0.9475 0.0493
-9.750 -0.5246 0.03064 0.02515 -0.1114 0.9429 0.0510
-9.500 -0.5131 0.02898 0.02327 -0.1098 0.9337 0.0520
-9.250 -0.4835 0.02820 0.02247 -0.1109 0.9303 0.0531
-9.000 -0.4532 0.02715 0.02131 -0.1123 0.9276 0.0542
-8.750 -0.4370 0.02611 0.02009 -0.1108 0.9189 0.0553
-8.500 -0.4111 0.02482 0.01856 -0.1113 0.9143 0.0567
-8.250 -0.3822 0.02344 0.01686 -0.1122 0.9111 0.0583
-8.000 -0.3653 0.02244 0.01558 -0.1105 0.9021 0.0593
-7.750 -0.3371 0.02138 0.01439 -0.1110 0.8977 0.0605
-7.500 -0.3102 0.02068 0.01362 -0.1111 0.8924 0.0616
-7.250 -0.2852 0.02016 0.01304 -0.1106 0.8855 0.0630
-7.000 -0.2545 0.01953 0.01229 -0.1113 0.8812 0.0647
-6.750 -0.2290 0.01892 0.01153 -0.1109 0.8746 0.0664
-6.500 -0.2018 0.01825 0.01068 -0.1108 0.8685 0.0680
-6.250 -0.1702 0.01757 0.00988 -0.1116 0.8642 0.0696
-6.000 -0.1463 0.01720 0.00949 -0.1108 0.8564 0.0712
-5.750 -0.1165 0.01683 0.00906 -0.1111 0.8507 0.0734
-5.500 -0.0879 0.01646 0.00859 -0.1112 0.8448 0.0761
-5.250 -0.0616 0.01607 0.00807 -0.1107 0.8378 0.0786
-5.000 -0.0312 0.01569 0.00766 -0.1112 0.8325 0.0811
-4.750 -0.0060 0.01547 0.00742 -0.1105 0.8252 0.0839
-4.500 0.0224 0.01521 0.00706 -0.1105 0.8189 0.0878
-4.250 0.0507 0.01493 0.00671 -0.1105 0.8131 0.0918
-4.000 0.0761 0.01476 0.00654 -0.1099 0.8057 0.0958
-3.750 0.1054 0.01455 0.00622 -0.1100 0.8001 0.1009
-3.500 0.1307 0.01434 0.00597 -0.1093 0.7931 0.1053
-3.250 0.1574 0.01418 0.00581 -0.1090 0.7864 0.1103
-3.000 0.1860 0.01405 0.00558 -0.1090 0.7808 0.1159
-2.750 0.2103 0.01389 0.00541 -0.1081 0.7733 0.1205
-2.500 0.2379 0.01374 0.00524 -0.1079 0.7672 0.1254
-2.250 0.2638 0.01364 0.00511 -0.1074 0.7606 0.1306
-2.000 0.2897 0.01353 0.00496 -0.1069 0.7536 0.1353
-1.750 0.3176 0.01340 0.00483 -0.1067 0.7480 0.1406
-1.500 0.3416 0.01334 0.00477 -0.1058 0.7402 0.1462
-1.250 0.3684 0.01325 0.00467 -0.1055 0.7338 0.1526
-1.000 0.3940 0.01320 0.00463 -0.1049 0.7269 0.1601
-0.750 0.4194 0.01313 0.00455 -0.1043 0.7197 0.1664
-0.500 0.4461 0.01304 0.00447 -0.1039 0.7134 0.1730
-0.250 0.4701 0.01300 0.00443 -0.1029 0.7047 0.1810
0.000 0.4960 0.01291 0.00435 -0.1024 0.6964 0.1906
0.250 0.5196 0.01285 0.00431 -0.1013 0.6857 0.2009
0.500 0.5437 0.01280 0.00425 -0.1004 0.6751 0.2129
0.750 0.5679 0.01273 0.00418 -0.0995 0.6637 0.2266
1.000 0.5906 0.01267 0.00415 -0.0983 0.6511 0.2429
1.250 0.6133 0.01261 0.00415 -0.0971 0.6393 0.2648
1.500 0.6366 0.01253 0.00417 -0.0961 0.6297 0.3031
1.750 0.6580 0.01235 0.00423 -0.0948 0.6199 0.3828
2.250 0.7997 0.01148 0.00466 -0.1128 0.5930 1.0000
2.500 0.8201 0.01162 0.00471 -0.1112 0.5817 1.0000
2.750 0.8403 0.01176 0.00479 -0.1095 0.5701 1.0000
3.000 0.8604 0.01192 0.00488 -0.1079 0.5584 1.0000
3.250 0.8800 0.01209 0.00498 -0.1061 0.5463 1.0000
3.500 0.8989 0.01228 0.00509 -0.1042 0.5331 1.0000
3.750 0.9173 0.01248 0.00522 -0.1022 0.5188 1.0000
4.000 0.9352 0.01270 0.00537 -0.1001 0.5037 1.0000
4.250 0.9528 0.01292 0.00553 -0.0980 0.4889 1.0000
4.500 0.9699 0.01316 0.00571 -0.0959 0.4740 1.0000
4.750 0.9861 0.01343 0.00590 -0.0935 0.4581 1.0000
5.000 1.0012 0.01372 0.00612 -0.0910 0.4407 1.0000
5.250 1.0151 0.01404 0.00635 -0.0882 0.4226 1.0000
5.500 1.0277 0.01440 0.00661 -0.0853 0.4036 1.0000
5.750 1.0392 0.01476 0.00688 -0.0821 0.3858 1.0000
6.000 1.0499 0.01513 0.00719 -0.0789 0.3685 1.0000
6.250 1.0602 0.01555 0.00752 -0.0756 0.3511 1.0000
6.500 1.0709 0.01600 0.00788 -0.0725 0.3346 1.0000
6.750 1.0822 0.01647 0.00829 -0.0696 0.3197 1.0000
7.250 1.1068 0.01747 0.00918 -0.0644 0.2941 1.0000
7.500 1.1196 0.01800 0.00967 -0.0620 0.2830 1.0000
7.750 1.1314 0.01859 0.01020 -0.0595 0.2728 1.0000
8.000 1.1451 0.01914 0.01073 -0.0574 0.2629 1.0000
8.250 1.1581 0.01974 0.01131 -0.0552 0.2553 1.0000
8.500 1.1726 0.02030 0.01187 -0.0533 0.2478 1.0000
9.000 1.2008 0.02150 0.01309 -0.0496 0.2357 1.0000
9.250 1.2137 0.02218 0.01378 -0.0477 0.2290 1.0000
9.500 1.2269 0.02287 0.01447 -0.0459 0.2231 1.0000
9.750 1.2416 0.02350 0.01516 -0.0443 0.2172 1.0000
10.000 1.2540 0.02427 0.01593 -0.0425 0.2120 1.0000
10.250 1.2674 0.02500 0.01671 -0.0409 0.2068 1.0000
10.500 1.2815 0.02571 0.01749 -0.0395 0.2012 1.0000
10.750 1.2923 0.02662 0.01839 -0.0377 0.1955 1.0000
11.000 1.3057 0.02740 0.01925 -0.0363 0.1902 1.0000
11.250 1.3176 0.02828 0.02018 -0.0348 0.1832 1.0000
11.500 1.3278 0.02930 0.02123 -0.0333 0.1773 1.0000
11.750 1.3406 0.03018 0.02220 -0.0320 0.1711 1.0000
12.000 1.3492 0.03136 0.02339 -0.0305 0.1647 1.0000
12.250 1.3613 0.03234 0.02446 -0.0293 0.1579 1.0000
12.500 1.3692 0.03362 0.02578 -0.0279 0.1511 1.0000
12.750 1.3792 0.03481 0.02703 -0.0267 0.1437 1.0000
13.000 1.3854 0.03631 0.02854 -0.0254 0.1357 1.0000
13.250 1.3918 0.03785 0.03011 -0.0242 0.1261 1.0000
13.500 1.3964 0.03958 0.03187 -0.0230 0.1163 1.0000
13.750 1.3996 0.04150 0.03379 -0.0218 0.1070 1.0000
14.000 1.3999 0.04375 0.03604 -0.0207 0.0957 1.0000
14.250 1.3993 0.04616 0.03844 -0.0197 0.0846 1.0000
14.500 1.3963 0.04890 0.04116 -0.0188 0.0705 1.0000
14.750 1.3815 0.05297 0.04508 -0.0180 0.0458 1.0000
15.000 1.3701 0.05689 0.04896 -0.0174 0.0391 1.0000
15.250 1.3633 0.06045 0.05259 -0.0172 0.0361 1.0000
15.500 1.3574 0.06404 0.05629 -0.0171 0.0341 1.0000
15.750 1.3504 0.06790 0.06026 -0.0173 0.0327 1.0000
16.250 1.3348 0.07622 0.06883 -0.0184 0.0306 1.0000
16.500 1.3270 0.08057 0.07334 -0.0192 0.0297 1.0000
16.750 1.3178 0.08525 0.07816 -0.0203 0.0289 1.0000
17.000 1.3067 0.09034 0.08341 -0.0216 0.0282 1.0000
17.250 1.2937 0.09584 0.08905 -0.0233 0.0276 1.0000
17.500 1.2795 0.10170 0.09504 -0.0253 0.0272 1.0000
17.750 1.2643 0.10786 0.10134 -0.0276 0.0268 1.0000
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