GOE 420 AIRFOIL (goe420-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 420 AIRFOIL (goe420-il) Reynolds number: 200,000 Max Cl/Cd: 66.67 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe420-il-200000.txt Download as CSV file: xf-goe420-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 420 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4876 0.07781 0.07368 -0.0927 0.9865 0.0617
-12.500 -0.5177 0.06702 0.06270 -0.1031 0.9820 0.0608
-12.250 -0.5557 0.05685 0.05219 -0.1144 0.9741 0.0599
-12.000 -0.5773 0.04948 0.04443 -0.1238 0.9669 0.0594
-11.750 -0.5913 0.04540 0.04003 -0.1269 0.9568 0.0591
-11.500 -0.5881 0.04190 0.03619 -0.1297 0.9512 0.0591
-11.250 -0.5875 0.03964 0.03368 -0.1289 0.9419 0.0592
-11.000 -0.5710 0.03721 0.03096 -0.1304 0.9369 0.0595
-10.750 -0.5475 0.03493 0.02840 -0.1323 0.9337 0.0599
-10.500 -0.5409 0.03372 0.02699 -0.1302 0.9245 0.0603
-10.250 -0.5192 0.03212 0.02515 -0.1307 0.9194 0.0609
-10.000 -0.4930 0.03068 0.02342 -0.1317 0.9157 0.0617
-9.750 -0.4809 0.02965 0.02228 -0.1296 0.9071 0.0624
-9.500 -0.4532 0.02835 0.02102 -0.1302 0.9021 0.0635
-9.250 -0.4239 0.02725 0.01989 -0.1310 0.8983 0.0647
-9.000 -0.4017 0.02641 0.01897 -0.1304 0.8928 0.0657
-8.750 -0.3854 0.02575 0.01823 -0.1287 0.8848 0.0667
-8.500 -0.3591 0.02488 0.01725 -0.1286 0.8801 0.0681
-8.250 -0.3301 0.02388 0.01618 -0.1291 0.8765 0.0696
-8.000 -0.3192 0.02335 0.01574 -0.1264 0.8669 0.0709
-7.750 -0.2959 0.02266 0.01505 -0.1258 0.8616 0.0732
-7.500 -0.2694 0.02200 0.01429 -0.1256 0.8577 0.0761
-7.250 -0.2578 0.02148 0.01384 -0.1231 0.8494 0.0783
-7.000 -0.2372 0.02085 0.01323 -0.1220 0.8431 0.0819
-6.750 -0.2124 0.02005 0.01240 -0.1215 0.8386 0.0865
-6.500 -0.1974 0.01961 0.01198 -0.1194 0.8304 0.0920
-6.250 -0.1772 0.01893 0.01135 -0.1181 0.8236 0.1012
-6.000 -0.1515 0.01812 0.01064 -0.1178 0.8188 0.1210
-5.750 -0.1350 0.01762 0.01025 -0.1159 0.8106 0.1523
-5.500 -0.1134 0.01702 0.00977 -0.1149 0.8041 0.1848
-5.250 -0.0861 0.01656 0.00940 -0.1149 0.7999 0.2146
-5.000 -0.0626 0.01643 0.00933 -0.1141 0.7943 0.2390
-4.750 -0.0403 0.01637 0.00930 -0.1130 0.7875 0.2605
-4.500 -0.0123 0.01622 0.00912 -0.1129 0.7828 0.2816
-4.250 0.0189 0.01608 0.00891 -0.1132 0.7790 0.3016
-4.000 0.0390 0.01614 0.00901 -0.1118 0.7716 0.3171
-3.750 0.0649 0.01609 0.00894 -0.1112 0.7660 0.3340
-3.500 0.0946 0.01601 0.00882 -0.1113 0.7618 0.3518
-3.250 0.1215 0.01605 0.00880 -0.1110 0.7569 0.3683
-3.000 0.1437 0.01609 0.00889 -0.1098 0.7498 0.3818
-2.750 0.1724 0.01594 0.00872 -0.1097 0.7446 0.3942
-2.500 0.2047 0.01581 0.00845 -0.1102 0.7405 0.4063
-2.250 0.2253 0.01578 0.00851 -0.1088 0.7329 0.4147
-2.000 0.2530 0.01568 0.00835 -0.1086 0.7271 0.4249
-1.750 0.2846 0.01546 0.00808 -0.1090 0.7227 0.4340
-1.500 0.3079 0.01546 0.00809 -0.1080 0.7158 0.4430
-1.250 0.3345 0.01533 0.00794 -0.1076 0.7093 0.4521
-1.000 0.3659 0.01514 0.00771 -0.1080 0.7041 0.4625
-0.750 0.3892 0.01511 0.00768 -0.1071 0.6967 0.4729
-0.500 0.4161 0.01499 0.00757 -0.1067 0.6896 0.4847
-0.250 0.4481 0.01481 0.00733 -0.1072 0.6842 0.4970
0.000 0.4691 0.01482 0.00739 -0.1058 0.6757 0.5100
0.250 0.4972 0.01466 0.00727 -0.1057 0.6689 0.5247
0.500 0.5241 0.01459 0.00722 -0.1053 0.6620 0.5405
0.750 0.5478 0.01453 0.00722 -0.1044 0.6534 0.5579
1.000 0.5785 0.01442 0.00708 -0.1046 0.6468 0.5781
1.250 0.5984 0.01442 0.00720 -0.1030 0.6372 0.5986
1.500 0.6262 0.01434 0.00715 -0.1028 0.6297 0.6237
1.750 0.6483 0.01436 0.00727 -0.1015 0.6210 0.6516
2.000 0.6731 0.01430 0.00727 -0.1007 0.6129 0.6831
2.250 0.6971 0.01427 0.00732 -0.0997 0.6051 0.7197
2.500 0.7168 0.01416 0.00742 -0.0978 0.5962 0.7642
2.750 0.7435 0.01411 0.00750 -0.0968 0.5895 0.8344
3.000 0.7707 0.01421 0.00776 -0.0963 0.5803 0.9166
3.250 0.8266 0.01433 0.00777 -0.1017 0.5726 0.9647
3.500 0.8823 0.01454 0.00798 -0.1076 0.5630 0.9948
3.750 0.9079 0.01466 0.00798 -0.1074 0.5557 1.0000
4.000 0.9246 0.01484 0.00809 -0.1054 0.5482 1.0000
4.250 0.9413 0.01499 0.00819 -0.1034 0.5405 1.0000
4.500 0.9673 0.01516 0.00820 -0.1030 0.5343 1.0000
4.750 0.9814 0.01539 0.00847 -0.1006 0.5270 1.0000
5.000 1.0029 0.01558 0.00860 -0.0994 0.5209 1.0000
5.250 1.0296 0.01582 0.00873 -0.0993 0.5154 1.0000
5.500 1.0460 0.01608 0.00904 -0.0973 0.5092 1.0000
5.750 1.0681 0.01632 0.00924 -0.0963 0.5036 1.0000
6.250 1.1126 0.01688 0.00975 -0.0944 0.4925 1.0000
6.500 1.1333 0.01714 0.00999 -0.0932 0.4866 1.0000
6.750 1.1614 0.01742 0.01017 -0.0934 0.4815 1.0000
7.000 1.1799 0.01777 0.01057 -0.0918 0.4762 1.0000
7.250 1.1984 0.01810 0.01092 -0.0903 0.4707 1.0000
7.500 1.2231 0.01839 0.01118 -0.0899 0.4655 1.0000
7.750 1.2488 0.01878 0.01152 -0.0897 0.4603 1.0000
8.000 1.2617 0.01914 0.01197 -0.0872 0.4545 1.0000
8.250 1.2825 0.01942 0.01221 -0.0861 0.4481 1.0000
8.500 1.3021 0.01977 0.01252 -0.0847 0.4410 1.0000
8.750 1.3079 0.02006 0.01286 -0.0810 0.4337 1.0000
9.000 1.3361 0.02035 0.01299 -0.0811 0.4256 1.0000
9.250 1.3325 0.02075 0.01354 -0.0759 0.4190 1.0000
9.500 1.3450 0.02109 0.01386 -0.0735 0.4119 1.0000
9.750 1.3635 0.02150 0.01423 -0.0722 0.4053 1.0000
10.000 1.3653 0.02200 0.01483 -0.0683 0.3982 1.0000
10.250 1.3819 0.02237 0.01514 -0.0667 0.3914 1.0000
10.500 1.3883 0.02296 0.01581 -0.0638 0.3848 1.0000
10.750 1.3946 0.02356 0.01647 -0.0610 0.3780 1.0000
11.000 1.4152 0.02393 0.01675 -0.0602 0.3717 1.0000
11.250 1.4125 0.02482 0.01781 -0.0564 0.3648 1.0000
11.500 1.4198 0.02551 0.01852 -0.0540 0.3579 1.0000
11.750 1.4299 0.02620 0.01922 -0.0521 0.3512 1.0000
12.000 1.4311 0.02722 0.02034 -0.0493 0.3437 1.0000
12.250 1.4435 0.02787 0.02092 -0.0478 0.3369 1.0000
12.500 1.4422 0.02916 0.02238 -0.0451 0.3292 1.0000
12.750 1.4487 0.03015 0.02335 -0.0432 0.3218 1.0000
13.000 1.4509 0.03146 0.02475 -0.0411 0.3139 1.0000
13.250 1.4545 0.03273 0.02602 -0.0392 0.3059 1.0000
13.500 1.4565 0.03422 0.02758 -0.0374 0.2976 1.0000
13.750 1.4586 0.03574 0.02909 -0.0357 0.2890 1.0000
14.000 1.4588 0.03754 0.03095 -0.0340 0.2799 1.0000
14.500 1.4570 0.04156 0.03500 -0.0311 0.2607 1.0000
14.750 1.4550 0.04380 0.03724 -0.0298 0.2508 1.0000
15.000 1.4507 0.04634 0.03974 -0.0286 0.2401 1.0000
15.250 1.4446 0.04923 0.04269 -0.0276 0.2285 1.0000
15.500 1.4368 0.05236 0.04582 -0.0268 0.2164 1.0000
15.750 1.4274 0.05578 0.04922 -0.0260 0.2041 1.0000
16.000 1.4160 0.05955 0.05295 -0.0255 0.1913 1.0000
16.250 1.4040 0.06352 0.05687 -0.0252 0.1792 1.0000
16.500 1.3940 0.06745 0.06080 -0.0251 0.1676 1.0000
16.750 1.3867 0.07116 0.06450 -0.0251 0.1584 1.0000
17.000 1.3797 0.07480 0.06805 -0.0252 0.1513 1.0000
17.250 1.3770 0.07810 0.07141 -0.0254 0.1446 1.0000
17.500 1.3754 0.08111 0.07429 -0.0254 0.1392 1.0000
17.750 1.3766 0.08401 0.07729 -0.0257 0.1347 1.0000
18.000 1.3773 0.08691 0.08019 -0.0260 0.1304 1.0000
18.250 1.3840 0.08883 0.08200 -0.0259 0.1265 1.0000
18.500 1.3856 0.09175 0.08503 -0.0264 0.1232 1.0000
18.750 1.3892 0.09434 0.08767 -0.0268 0.1201 1.0000
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