GOE 450 AIRFOIL (goe450-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 450 AIRFOIL (goe450-il) Reynolds number: 100,000 Max Cl/Cd: 64.36 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe450-il-100000-n5.txt Download as CSV file: xf-goe450-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 450 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3202 0.10578 0.10100 -0.0328 1.0000 0.0486
-8.250 -0.3274 0.10422 0.09950 -0.0310 1.0000 0.0500
-8.000 -0.3373 0.10285 0.09822 -0.0290 1.0000 0.0512
-7.750 -0.3303 0.10007 0.09545 -0.0363 0.9923 0.0537
-7.500 -0.3087 0.09572 0.09109 -0.0511 0.9818 0.0545
-7.250 -0.2938 0.09048 0.08586 -0.0527 0.9778 0.0552
-7.000 -0.2771 0.08671 0.08207 -0.0507 0.9756 0.0570
-6.750 -0.2597 0.08349 0.07884 -0.0531 0.9696 0.0606
-6.500 -0.2182 0.07865 0.07378 -0.0759 0.9576 0.0665
-6.250 -0.2065 0.07377 0.06896 -0.0744 0.9536 0.0676
-6.000 -0.1861 0.07020 0.06538 -0.0750 0.9503 0.0694
-5.750 -0.1662 0.06695 0.06209 -0.0775 0.9433 0.0717
-5.500 -0.1120 0.06156 0.05621 -0.0958 0.9357 0.0804
-5.000 -0.0566 0.04861 0.04280 -0.1035 0.9238 0.0544
-4.750 -0.0281 0.04533 0.03948 -0.1060 0.9202 0.0527
-4.500 0.0026 0.04136 0.03517 -0.1095 0.9135 0.0531
-4.250 0.0342 0.03785 0.03134 -0.1124 0.9077 0.0525
-4.000 0.0705 0.03438 0.02750 -0.1157 0.9042 0.0512
-3.750 0.0986 0.03165 0.02438 -0.1168 0.8967 0.0505
-3.500 0.1325 0.02916 0.02143 -0.1187 0.8917 0.0507
-3.250 0.1694 0.02708 0.01887 -0.1207 0.8883 0.0524
-3.000 0.1954 0.02560 0.01705 -0.1206 0.8797 0.0524
-2.750 0.2298 0.02403 0.01513 -0.1218 0.8751 0.0524
-2.500 0.2588 0.02287 0.01368 -0.1220 0.8680 0.0526
-2.250 0.2902 0.02179 0.01237 -0.1224 0.8618 0.0530
-2.000 0.3217 0.02087 0.01125 -0.1229 0.8560 0.0536
-1.500 0.3811 0.01941 0.00969 -0.1234 0.8421 0.0580
-1.250 0.4081 0.01888 0.00913 -0.1230 0.8331 0.0595
-1.000 0.4377 0.01832 0.00852 -0.1231 0.8258 0.0610
-0.750 0.4659 0.01787 0.00803 -0.1229 0.8171 0.0630
-0.500 0.4941 0.01752 0.00761 -0.1227 0.8083 0.0655
-0.250 0.5239 0.01712 0.00717 -0.1228 0.8004 0.0696
0.000 0.5506 0.01690 0.00693 -0.1224 0.7903 0.0778
0.500 0.6077 0.01540 0.00663 -0.1228 0.7725 0.4917
1.000 0.6638 0.01433 0.00627 -0.1217 0.7543 1.0000
1.250 0.6902 0.01445 0.00626 -0.1212 0.7435 1.0000
1.500 0.7182 0.01451 0.00620 -0.1210 0.7341 1.0000
1.750 0.7461 0.01459 0.00617 -0.1208 0.7244 1.0000
2.000 0.7725 0.01474 0.00625 -0.1205 0.7139 1.0000
2.250 0.8002 0.01485 0.00627 -0.1203 0.7044 1.0000
2.500 0.8273 0.01499 0.00635 -0.1200 0.6942 1.0000
2.750 0.8534 0.01517 0.00650 -0.1196 0.6836 1.0000
3.000 0.8806 0.01532 0.00660 -0.1193 0.6738 1.0000
3.250 0.9073 0.01550 0.00675 -0.1190 0.6635 1.0000
3.500 0.9330 0.01572 0.00698 -0.1185 0.6524 1.0000
3.750 0.9593 0.01593 0.00717 -0.1181 0.6419 1.0000
4.000 0.9859 0.01612 0.00733 -0.1177 0.6311 1.0000
4.250 1.0106 0.01637 0.00763 -0.1171 0.6184 1.0000
4.500 1.0355 0.01663 0.00791 -0.1165 0.6057 1.0000
4.750 1.0603 0.01688 0.00818 -0.1159 0.5926 1.0000
5.000 1.0849 0.01714 0.00849 -0.1152 0.5794 1.0000
5.250 1.1090 0.01741 0.00879 -0.1144 0.5652 1.0000
5.500 1.1323 0.01769 0.00911 -0.1135 0.5495 1.0000
5.750 1.1544 0.01797 0.00944 -0.1123 0.5303 1.0000
6.000 1.1753 0.01826 0.00967 -0.1109 0.5077 1.0000
6.250 1.1946 0.01861 0.01000 -0.1093 0.4809 1.0000
6.500 1.2137 0.01903 0.01037 -0.1077 0.4550 1.0000
6.750 1.2337 0.01948 0.01084 -0.1063 0.4346 1.0000
7.000 1.2533 0.01997 0.01136 -0.1049 0.4147 1.0000
7.250 1.2711 0.02053 0.01192 -0.1032 0.3906 1.0000
7.500 1.2862 0.02120 0.01253 -0.1011 0.3600 1.0000
7.750 1.2989 0.02201 0.01323 -0.0988 0.3245 1.0000
8.000 1.3087 0.02298 0.01407 -0.0960 0.2785 1.0000
8.250 1.3147 0.02422 0.01505 -0.0929 0.2213 1.0000
8.500 1.3133 0.02588 0.01633 -0.0888 0.1714 1.0000
8.750 1.3150 0.02757 0.01781 -0.0854 0.1287 1.0000
9.000 1.3137 0.02954 0.01948 -0.0819 0.0901 1.0000
9.250 1.3146 0.03139 0.02123 -0.0788 0.0749 1.0000
9.500 1.3186 0.03305 0.02297 -0.0761 0.0656 1.0000
9.750 1.3213 0.03484 0.02483 -0.0735 0.0591 1.0000
10.000 1.3260 0.03653 0.02664 -0.0713 0.0539 1.0000
10.250 1.3273 0.03854 0.02870 -0.0690 0.0505 1.0000
10.500 1.3298 0.04053 0.03082 -0.0670 0.0477 1.0000
10.750 1.3320 0.04261 0.03303 -0.0651 0.0449 1.0000
11.000 1.3323 0.04493 0.03543 -0.0634 0.0425 1.0000
11.250 1.3293 0.04764 0.03820 -0.0615 0.0408 1.0000
11.500 1.3313 0.04998 0.04068 -0.0599 0.0393 1.0000
11.750 1.3341 0.05230 0.04319 -0.0585 0.0374 1.0000
12.000 1.3365 0.05471 0.04571 -0.0572 0.0355 1.0000
12.250 1.3386 0.05719 0.04826 -0.0560 0.0338 1.0000
12.500 1.3417 0.05967 0.05076 -0.0545 0.0325 1.0000
12.750 1.3491 0.06190 0.05306 -0.0529 0.0312 1.0000
13.000 1.3551 0.06424 0.05564 -0.0518 0.0299 1.0000
13.250 1.3594 0.06681 0.05842 -0.0508 0.0284 1.0000
13.500 1.3628 0.06951 0.06133 -0.0499 0.0272 1.0000
13.750 1.3661 0.07230 0.06428 -0.0491 0.0262 1.0000
14.000 1.3688 0.07522 0.06734 -0.0483 0.0255 1.0000
14.250 1.3712 0.07827 0.07051 -0.0476 0.0247 1.0000
14.500 1.3747 0.08166 0.07397 -0.0467 0.0239 1.0000
14.750 1.3659 0.08588 0.07851 -0.0470 0.0235 1.0000
15.000 1.3555 0.09052 0.08347 -0.0476 0.0231 1.0000
15.250 1.3440 0.09556 0.08881 -0.0487 0.0227 1.0000
15.500 1.3313 0.10099 0.09453 -0.0504 0.0223 1.0000
15.750 1.3175 0.10685 0.10066 -0.0525 0.0220 1.0000
16.000 1.3025 0.11321 0.10727 -0.0553 0.0218 1.0000
16.250 1.2864 0.12014 0.11446 -0.0587 0.0217 1.0000
16.500 1.2690 0.12778 0.12233 -0.0630 0.0216 1.0000
16.750 1.2502 0.13627 0.13105 -0.0682 0.0217 1.0000
17.000 1.2298 0.14580 0.14079 -0.0744 0.0219 1.0000
17.250 1.2076 0.15667 0.15184 -0.0818 0.0222 1.0000
17.500 1.1840 0.16918 0.16449 -0.0903 0.0226 1.0000
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Polar data table (+)
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