GOE 384 AIRFOIL (goe384-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 384 AIRFOIL (goe384-il) Reynolds number: 200,000 Max Cl/Cd: 59.08 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe384-il-200000-n5.txt Download as CSV file: xf-goe384-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 384 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.0219 0.09234 0.08733 -0.0900 0.7018 0.0441
-10.000 -0.0217 0.08821 0.08318 -0.0923 0.6963 0.0440
-9.750 -0.0225 0.08394 0.07887 -0.0947 0.6912 0.0440
-9.500 -0.0251 0.07939 0.07428 -0.0975 0.6866 0.0440
-9.250 -0.0300 0.07441 0.06926 -0.1008 0.6826 0.0442
-9.000 -0.0410 0.06810 0.06295 -0.1058 0.6785 0.0447
-8.750 -0.1642 0.04124 0.03533 -0.1255 0.6783 0.0453
-8.500 -0.1885 0.03314 0.02623 -0.1247 0.6747 0.0464
-8.250 -0.1761 0.03079 0.02346 -0.1240 0.6704 0.0470
-7.750 -0.1317 0.02928 0.02174 -0.1234 0.6614 0.0480
-7.500 -0.1093 0.02845 0.02078 -0.1231 0.6569 0.0487
-7.250 -0.0875 0.02739 0.01950 -0.1227 0.6530 0.0495
-7.000 -0.0658 0.02615 0.01796 -0.1223 0.6495 0.0504
-6.750 -0.0434 0.02491 0.01638 -0.1219 0.6459 0.0512
-6.500 -0.0201 0.02379 0.01495 -0.1214 0.6418 0.0521
-6.250 0.0050 0.02310 0.01418 -0.1212 0.6376 0.0527
-6.000 0.0309 0.02263 0.01366 -0.1211 0.6337 0.0535
-5.750 0.0571 0.02222 0.01314 -0.1210 0.6303 0.0544
-5.500 0.0835 0.02176 0.01255 -0.1209 0.6275 0.0556
-5.250 0.1097 0.02121 0.01189 -0.1208 0.6243 0.0568
-5.000 0.1360 0.02067 0.01120 -0.1206 0.6209 0.0579
-4.750 0.1625 0.02019 0.01068 -0.1205 0.6176 0.0588
-4.500 0.1892 0.01984 0.01032 -0.1204 0.6144 0.0598
-4.250 0.2164 0.01956 0.00999 -0.1204 0.6116 0.0611
-4.000 0.2440 0.01931 0.00963 -0.1204 0.6088 0.0627
-3.750 0.2704 0.01899 0.00926 -0.1203 0.6055 0.0644
-3.500 0.2967 0.01867 0.00897 -0.1201 0.6017 0.0657
-3.250 0.3232 0.01843 0.00875 -0.1200 0.5980 0.0671
-3.000 0.3501 0.01822 0.00851 -0.1199 0.5945 0.0689
-2.750 0.3775 0.01804 0.00826 -0.1199 0.5914 0.0712
-2.500 0.4044 0.01787 0.00808 -0.1198 0.5882 0.0733
-2.250 0.4304 0.01771 0.00798 -0.1196 0.5841 0.0755
-2.000 0.4566 0.01755 0.00783 -0.1194 0.5798 0.0781
-1.750 0.4830 0.01740 0.00767 -0.1192 0.5756 0.0810
-1.500 0.5102 0.01730 0.00753 -0.1192 0.5718 0.0847
-1.250 0.5362 0.01721 0.00745 -0.1189 0.5674 0.0890
-1.000 0.5617 0.01708 0.00739 -0.1187 0.5625 0.0934
-0.750 0.5878 0.01698 0.00728 -0.1184 0.5578 0.0996
-0.500 0.6143 0.01687 0.00713 -0.1183 0.5535 0.1074
-0.250 0.6392 0.01676 0.00709 -0.1179 0.5478 0.1164
0.000 0.6642 0.01665 0.00703 -0.1176 0.5416 0.1282
0.250 0.6895 0.01650 0.00693 -0.1173 0.5363 0.1500
0.500 0.7128 0.01618 0.00700 -0.1169 0.5297 0.2500
0.750 0.7353 0.01580 0.00707 -0.1163 0.5231 0.3894
1.250 0.7712 0.01482 0.00742 -0.1123 0.5093 0.8001
1.500 0.8231 0.01485 0.00757 -0.1167 0.5003 0.9762
1.750 0.8599 0.01502 0.00764 -0.1189 0.4906 1.0000
2.000 0.8777 0.01518 0.00767 -0.1172 0.4828 1.0000
2.250 0.8958 0.01536 0.00776 -0.1156 0.4749 1.0000
2.500 0.9137 0.01558 0.00784 -0.1139 0.4681 1.0000
2.750 0.9322 0.01582 0.00800 -0.1125 0.4611 1.0000
3.000 0.9496 0.01609 0.00815 -0.1108 0.4547 1.0000
3.250 0.9671 0.01637 0.00834 -0.1092 0.4488 1.0000
3.500 0.9837 0.01667 0.00857 -0.1075 0.4429 1.0000
3.750 1.0006 0.01702 0.00881 -0.1058 0.4378 1.0000
4.000 1.0193 0.01736 0.00909 -0.1046 0.4333 1.0000
4.250 1.0385 0.01771 0.00940 -0.1035 0.4289 1.0000
4.500 1.0579 0.01809 0.00972 -0.1024 0.4247 1.0000
4.750 1.0774 0.01849 0.01004 -0.1014 0.4210 1.0000
5.000 1.0977 0.01890 0.01037 -0.1006 0.4175 1.0000
5.250 1.1174 0.01931 0.01078 -0.0997 0.4137 1.0000
5.500 1.1368 0.01974 0.01120 -0.0988 0.4099 1.0000
5.750 1.1564 0.02019 0.01160 -0.0980 0.4064 1.0000
6.000 1.1767 0.02064 0.01199 -0.0973 0.4033 1.0000
6.250 1.1984 0.02108 0.01236 -0.0968 0.4006 1.0000
6.500 1.2174 0.02157 0.01289 -0.0960 0.3978 1.0000
6.750 1.2363 0.02207 0.01342 -0.0952 0.3949 1.0000
7.000 1.2549 0.02260 0.01396 -0.0944 0.3919 1.0000
7.250 1.2738 0.02313 0.01448 -0.0936 0.3890 1.0000
7.500 1.2935 0.02365 0.01497 -0.0930 0.3862 1.0000
7.750 1.3151 0.02413 0.01538 -0.0926 0.3835 1.0000
8.000 1.3324 0.02475 0.01604 -0.0917 0.3811 1.0000
8.250 1.3489 0.02541 0.01677 -0.0908 0.3785 1.0000
8.500 1.3654 0.02608 0.01750 -0.0900 0.3760 1.0000
8.750 1.3823 0.02676 0.01821 -0.0892 0.3734 1.0000
9.000 1.3995 0.02742 0.01889 -0.0884 0.3710 1.0000
9.250 1.4177 0.02805 0.01952 -0.0878 0.3686 1.0000
9.500 1.4381 0.02859 0.02002 -0.0874 0.3663 1.0000
9.750 1.4547 0.02933 0.02079 -0.0866 0.3639 1.0000
10.000 1.4663 0.03030 0.02187 -0.0855 0.3614 1.0000
10.250 1.4791 0.03125 0.02291 -0.0845 0.3590 1.0000
10.500 1.4924 0.03219 0.02392 -0.0835 0.3566 1.0000
10.750 1.5061 0.03312 0.02490 -0.0827 0.3543 1.0000
11.000 1.5212 0.03396 0.02577 -0.0820 0.3520 1.0000
11.250 1.5389 0.03464 0.02645 -0.0815 0.3498 1.0000
11.500 1.5592 0.03521 0.02699 -0.0812 0.3475 1.0000
11.750 1.5610 0.03690 0.02885 -0.0796 0.3447 1.0000
12.000 1.5640 0.03858 0.03066 -0.0781 0.3412 1.0000
12.250 1.5686 0.04018 0.03233 -0.0769 0.3373 1.0000
12.500 1.5791 0.04135 0.03350 -0.0761 0.3336 1.0000
12.750 1.5944 0.04218 0.03431 -0.0756 0.3304 1.0000
13.000 1.5908 0.04469 0.03699 -0.0742 0.3268 1.0000
13.250 1.5925 0.04682 0.03926 -0.0732 0.3234 1.0000
13.500 1.5975 0.04870 0.04121 -0.0725 0.3203 1.0000
13.750 1.6073 0.05013 0.04268 -0.0719 0.3176 1.0000
14.000 1.6230 0.05099 0.04353 -0.0716 0.3152 1.0000
14.250 1.6218 0.05359 0.04628 -0.0708 0.3121 1.0000
14.500 1.6152 0.05680 0.04966 -0.0700 0.3082 1.0000
14.750 1.6138 0.05951 0.05247 -0.0693 0.3045 1.0000
15.000 1.6218 0.06120 0.05418 -0.0690 0.3012 1.0000
15.250 1.6352 0.06229 0.05526 -0.0687 0.2982 1.0000
15.500 1.6143 0.06733 0.06054 -0.0679 0.2934 1.0000
15.750 1.6057 0.07103 0.06436 -0.0675 0.2888 1.0000
16.000 1.6143 0.07268 0.06602 -0.0673 0.2851 1.0000
16.250 1.6089 0.07607 0.06950 -0.0670 0.2808 1.0000
16.500 1.5837 0.08201 0.07563 -0.0666 0.2752 1.0000
16.750 1.5876 0.08434 0.07797 -0.0666 0.2705 1.0000
17.000 1.5764 0.08862 0.08235 -0.0665 0.2653 1.0000
17.250 1.5461 0.09556 0.08946 -0.0667 0.2588 1.0000
17.500 1.5630 0.09619 0.09004 -0.0668 0.2542 1.0000
17.750 1.5126 0.10617 0.10026 -0.0676 0.2465 1.0000
18.000 1.5194 0.10821 0.10230 -0.0679 0.2410 1.0000
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