GOE 405 AIRFOIL (goe405-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 405 AIRFOIL (goe405-il) Reynolds number: 500,000 Max Cl/Cd: 115.44 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe405-il-500000.txt Download as CSV file: xf-goe405-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 405 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.0715 0.09122 0.08892 -0.0947 0.9709 0.0260
-9.250 -0.0624 0.08709 0.08479 -0.0992 0.9643 0.0262
-9.000 -0.0458 0.08246 0.08016 -0.1047 0.9608 0.0263
-8.750 -0.0307 0.07750 0.07520 -0.1084 0.9586 0.0270
-8.500 -0.0050 0.07473 0.07241 -0.1122 0.9564 0.0276
-8.250 0.0118 0.07204 0.06970 -0.1150 0.9483 0.0286
-8.000 0.0353 0.06812 0.06575 -0.1214 0.9429 0.0300
-7.750 0.0394 0.06278 0.06037 -0.1302 0.9255 0.0327
-7.500 0.0480 0.05827 0.05579 -0.1357 0.9118 0.0329
-7.000 -0.0234 0.02390 0.02011 -0.1504 0.8711 0.0258
-6.750 -0.0117 0.02052 0.01610 -0.1494 0.8617 0.0266
-6.500 0.0075 0.01858 0.01393 -0.1489 0.8541 0.0277
-6.250 0.0308 0.01811 0.01339 -0.1483 0.8455 0.0290
-6.000 0.0559 0.01742 0.01251 -0.1480 0.8382 0.0305
-5.750 0.0781 0.01652 0.01137 -0.1470 0.8285 0.0318
-5.500 0.1029 0.01597 0.01056 -0.1464 0.8194 0.0327
-5.250 0.1237 0.01411 0.00838 -0.1455 0.8101 0.0344
-5.000 0.1481 0.01361 0.00781 -0.1449 0.8011 0.0360
-4.750 0.1742 0.01314 0.00719 -0.1445 0.7940 0.0376
-4.500 0.1992 0.01264 0.00658 -0.1439 0.7864 0.0389
-4.250 0.2257 0.01228 0.00606 -0.1436 0.7798 0.0403
-4.000 0.2514 0.01197 0.00565 -0.1431 0.7728 0.0413
-3.750 0.2760 0.01113 0.00468 -0.1424 0.7662 0.0432
-3.500 0.3016 0.01078 0.00427 -0.1420 0.7598 0.0450
-3.250 0.3276 0.01054 0.00398 -0.1416 0.7532 0.0472
-3.000 0.3542 0.01034 0.00369 -0.1412 0.7475 0.0493
-2.750 0.3799 0.01015 0.00344 -0.1407 0.7408 0.0509
-2.500 0.4060 0.00985 0.00309 -0.1403 0.7350 0.0551
-2.250 0.4319 0.00968 0.00291 -0.1398 0.7288 0.0609
-2.000 0.4574 0.00943 0.00274 -0.1393 0.7227 0.0829
-1.750 0.4837 0.00933 0.00272 -0.1390 0.7169 0.1235
-1.500 0.5099 0.00932 0.00272 -0.1386 0.7105 0.1398
-1.250 0.5369 0.00935 0.00270 -0.1384 0.7048 0.1513
-1.000 0.5631 0.00937 0.00269 -0.1381 0.6985 0.1613
-0.750 0.5893 0.00937 0.00270 -0.1377 0.6920 0.1716
-0.500 0.6156 0.00939 0.00270 -0.1374 0.6859 0.1815
-0.250 0.6416 0.00942 0.00270 -0.1370 0.6790 0.1911
0.000 0.6677 0.00943 0.00270 -0.1366 0.6727 0.2014
0.250 0.6929 0.00940 0.00270 -0.1361 0.6652 0.2115
0.750 0.7437 0.00939 0.00269 -0.1350 0.6506 0.2307
1.000 0.7690 0.00942 0.00267 -0.1345 0.6432 0.2402
1.250 0.7936 0.00940 0.00269 -0.1339 0.6343 0.2510
1.500 0.8180 0.00940 0.00270 -0.1332 0.6259 0.2645
1.750 0.8420 0.00939 0.00272 -0.1324 0.6161 0.2801
2.000 0.8655 0.00936 0.00275 -0.1316 0.6056 0.3036
2.250 0.8825 0.00876 0.00286 -0.1297 0.5950 0.6167
2.500 0.9422 0.00826 0.00305 -0.1368 0.5810 1.0000
2.750 0.9636 0.00841 0.00312 -0.1355 0.5688 1.0000
3.000 0.9852 0.00856 0.00320 -0.1342 0.5560 1.0000
3.250 1.0066 0.00872 0.00330 -0.1330 0.5432 1.0000
3.500 1.0277 0.00891 0.00341 -0.1316 0.5304 1.0000
3.750 1.0485 0.00910 0.00355 -0.1303 0.5179 1.0000
4.000 1.0688 0.00932 0.00370 -0.1288 0.5054 1.0000
4.250 1.0888 0.00956 0.00386 -0.1274 0.4936 1.0000
4.500 1.1097 0.00977 0.00403 -0.1261 0.4826 1.0000
4.750 1.1304 0.00999 0.00422 -0.1248 0.4729 1.0000
5.000 1.1500 0.01025 0.00442 -0.1232 0.4636 1.0000
5.250 1.1706 0.01046 0.00462 -0.1219 0.4541 1.0000
5.500 1.1899 0.01071 0.00484 -0.1204 0.4461 1.0000
5.750 1.2088 0.01094 0.00506 -0.1187 0.4379 1.0000
6.000 1.2268 0.01120 0.00530 -0.1169 0.4289 1.0000
6.500 1.2611 0.01174 0.00580 -0.1131 0.4088 1.0000
6.750 1.2785 0.01203 0.00608 -0.1113 0.3995 1.0000
7.250 1.3124 0.01265 0.00667 -0.1076 0.3783 1.0000
7.500 1.3294 0.01297 0.00699 -0.1058 0.3680 1.0000
7.750 1.3449 0.01335 0.00736 -0.1038 0.3556 1.0000
8.000 1.3597 0.01377 0.00775 -0.1018 0.3416 1.0000
8.250 1.3735 0.01425 0.00819 -0.0996 0.3239 1.0000
8.500 1.3854 0.01483 0.00870 -0.0972 0.3043 1.0000
8.750 1.3944 0.01558 0.00934 -0.0944 0.2804 1.0000
9.000 1.3952 0.01679 0.01031 -0.0906 0.2426 1.0000
9.250 1.3932 0.01825 0.01151 -0.0866 0.2008 1.0000
9.500 1.3801 0.02048 0.01332 -0.0815 0.1365 1.0000
9.750 1.3535 0.02377 0.01613 -0.0753 0.0556 1.0000
10.000 1.3490 0.02584 0.01808 -0.0720 0.0287 1.0000
10.250 1.3550 0.02726 0.01953 -0.0699 0.0234 1.0000
10.500 1.3609 0.02874 0.02105 -0.0680 0.0212 1.0000
10.750 1.3659 0.03033 0.02274 -0.0661 0.0200 1.0000
11.000 1.3730 0.03182 0.02432 -0.0645 0.0190 1.0000
11.250 1.3779 0.03352 0.02612 -0.0629 0.0181 1.0000
11.500 1.3814 0.03541 0.02809 -0.0614 0.0173 1.0000
11.750 1.3819 0.03765 0.03041 -0.0598 0.0165 1.0000
12.000 1.3784 0.04035 0.03322 -0.0582 0.0160 1.0000
12.250 1.3691 0.04376 0.03676 -0.0565 0.0155 1.0000
12.500 1.3701 0.04625 0.03935 -0.0555 0.0153 1.0000
12.750 1.3709 0.04882 0.04201 -0.0546 0.0149 1.0000
13.000 1.3689 0.05178 0.04509 -0.0538 0.0146 1.0000
13.250 1.3650 0.05505 0.04846 -0.0531 0.0145 1.0000
13.500 1.3625 0.05823 0.05174 -0.0526 0.0142 1.0000
13.750 1.3583 0.06171 0.05532 -0.0522 0.0139 1.0000
14.000 1.3555 0.06509 0.05879 -0.0520 0.0136 1.0000
14.250 1.3512 0.06874 0.06253 -0.0519 0.0134 1.0000
14.500 1.3486 0.07223 0.06609 -0.0519 0.0129 1.0000
14.750 1.3440 0.07599 0.06992 -0.0520 0.0126 1.0000
15.000 1.3376 0.07998 0.07396 -0.0520 0.0122 1.0000
15.250 1.3335 0.08354 0.07758 -0.0519 0.0120 1.0000
15.500 1.3327 0.08626 0.08033 -0.0510 0.0117 1.0000
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Polar data table (+)
Polar graphs
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