GOE 373 AIRFOIL (goe373-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 373 AIRFOIL (goe373-il) Reynolds number: 200,000 Max Cl/Cd: 80.13 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe373-il-200000.txt Download as CSV file: xf-goe373-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 373 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2431 0.10419 0.10082 -0.0261 1.0000 0.0236
-9.250 -0.2450 0.10221 0.09887 -0.0274 1.0000 0.0236
-7.750 -0.2990 0.09497 0.09161 -0.0237 1.0000 0.0240
-7.500 -0.2946 0.09190 0.08858 -0.0226 1.0000 0.0243
-7.250 -0.2949 0.08963 0.08636 -0.0215 1.0000 0.0246
-7.000 -0.2947 0.08734 0.08413 -0.0208 1.0000 0.0250
-6.750 -0.2939 0.08511 0.08195 -0.0206 1.0000 0.0253
-6.500 -0.2941 0.08302 0.07992 -0.0203 1.0000 0.0259
-6.250 -0.2960 0.08112 0.07808 -0.0197 1.0000 0.0264
-6.000 -0.3009 0.07954 0.07656 -0.0186 1.0000 0.0269
-5.750 -0.2935 0.07715 0.07420 -0.0208 0.9983 0.0276
-5.500 -0.2205 0.07207 0.06889 -0.0435 0.9900 0.0289
-5.250 -0.1957 0.06659 0.06342 -0.0470 0.9851 0.0293
-5.000 -0.1720 0.06255 0.05938 -0.0493 0.9797 0.0300
-4.750 -0.1372 0.05865 0.05542 -0.0551 0.9732 0.0313
-4.500 -0.0928 0.05461 0.05127 -0.0632 0.9678 0.0336
-4.250 -0.0255 0.05061 0.04684 -0.0761 0.9598 0.0356
-4.000 0.0007 0.04603 0.04235 -0.0790 0.9560 0.0366
-3.750 0.0333 0.04296 0.03922 -0.0824 0.9470 0.0382
-3.500 0.0808 0.03962 0.03569 -0.0886 0.9417 0.0414
-3.250 0.1237 0.03625 0.03205 -0.0931 0.9304 0.0452
-3.000 0.1556 0.03377 0.02951 -0.0955 0.9191 0.0477
-2.500 0.2285 0.02909 0.02435 -0.1002 0.8965 0.0567
-2.250 0.2570 0.02748 0.02262 -0.1010 0.8821 0.0616
-2.000 0.2883 0.02574 0.02057 -0.1017 0.8673 0.0687
-1.750 0.3145 0.02439 0.01910 -0.1017 0.8519 0.0749
-1.500 0.3417 0.02298 0.01746 -0.1018 0.8365 0.0843
-1.250 0.3682 0.02186 0.01612 -0.1016 0.8202 0.0968
-1.000 0.3938 0.02084 0.01490 -0.1012 0.8033 0.1109
-0.750 0.4184 0.01982 0.01376 -0.1008 0.7861 0.1276
-0.500 0.4428 0.01898 0.01279 -0.1004 0.7689 0.1563
-0.250 0.2464 0.03800 0.03440 -0.0437 0.7539 0.4523
0.750 0.5718 0.01485 0.00796 -0.0976 0.6860 0.2602
1.000 0.6103 0.01471 0.00696 -0.0955 0.6709 0.1045
1.250 0.6377 0.01409 0.00614 -0.0944 0.6553 0.0854
1.500 0.6643 0.01380 0.00569 -0.0935 0.6389 0.0762
1.750 0.6902 0.01340 0.00519 -0.0927 0.6222 0.0702
2.000 0.7162 0.01338 0.00505 -0.0919 0.6051 0.0665
2.250 0.7412 0.01307 0.00471 -0.0911 0.5881 0.0650
2.500 0.7662 0.01291 0.00451 -0.0903 0.5713 0.0639
2.750 0.7914 0.01286 0.00439 -0.0896 0.5556 0.0635
3.000 0.8169 0.01292 0.00435 -0.0890 0.5408 0.0639
3.250 0.8424 0.01303 0.00438 -0.0884 0.5263 0.0668
3.500 0.8678 0.01316 0.00445 -0.0878 0.5120 0.0746
3.750 0.8934 0.01330 0.00457 -0.0872 0.4982 0.0907
4.000 0.9244 0.01205 0.00482 -0.0881 0.4840 1.0000
4.250 0.9496 0.01230 0.00497 -0.0875 0.4709 1.0000
4.500 0.9749 0.01258 0.00517 -0.0869 0.4596 1.0000
4.750 1.0002 0.01282 0.00539 -0.0863 0.4480 1.0000
5.000 1.0254 0.01307 0.00563 -0.0858 0.4370 1.0000
5.250 1.0500 0.01330 0.00583 -0.0851 0.4242 1.0000
5.500 1.0736 0.01347 0.00598 -0.0843 0.4061 1.0000
5.750 1.0968 0.01370 0.00613 -0.0834 0.3878 1.0000
6.000 1.1203 0.01399 0.00638 -0.0827 0.3720 1.0000
6.250 1.1435 0.01427 0.00665 -0.0819 0.3539 1.0000
6.500 1.1657 0.01460 0.00694 -0.0809 0.3306 1.0000
6.750 1.1878 0.01497 0.00726 -0.0800 0.3075 1.0000
7.000 1.2098 0.01537 0.00760 -0.0791 0.2839 1.0000
7.250 1.2320 0.01577 0.00797 -0.0782 0.2567 1.0000
7.500 1.2522 0.01635 0.00841 -0.0771 0.2168 1.0000
7.750 1.2684 0.01736 0.00908 -0.0756 0.1728 1.0000
8.000 1.2873 0.01816 0.00978 -0.0744 0.1518 1.0000
8.250 1.3071 0.01885 0.01045 -0.0732 0.1330 1.0000
8.500 1.3249 0.01973 0.01120 -0.0719 0.1019 1.0000
8.750 1.3360 0.02121 0.01237 -0.0697 0.0570 1.0000
9.000 1.3461 0.02273 0.01370 -0.0674 0.0315 1.0000
9.250 1.3592 0.02390 0.01486 -0.0654 0.0266 1.0000
9.500 1.3731 0.02492 0.01604 -0.0634 0.0252 1.0000
9.750 1.3850 0.02602 0.01730 -0.0612 0.0243 1.0000
10.000 1.3935 0.02717 0.01860 -0.0586 0.0238 1.0000
10.250 1.3982 0.02847 0.02008 -0.0555 0.0233 1.0000
10.500 1.4005 0.02995 0.02171 -0.0525 0.0229 1.0000
10.750 1.4012 0.03160 0.02351 -0.0497 0.0226 1.0000
11.000 1.3996 0.03356 0.02560 -0.0471 0.0224 1.0000
11.250 1.3972 0.03577 0.02794 -0.0449 0.0222 1.0000
11.500 1.3950 0.03818 0.03047 -0.0432 0.0221 1.0000
11.750 1.3920 0.04087 0.03327 -0.0419 0.0218 1.0000
12.000 1.3891 0.04375 0.03624 -0.0408 0.0216 1.0000
12.250 1.3861 0.04684 0.03941 -0.0397 0.0211 1.0000
12.500 1.3861 0.04986 0.04253 -0.0385 0.0207 1.0000
12.750 1.3916 0.05242 0.04518 -0.0374 0.0206 1.0000
13.000 1.3992 0.05490 0.04777 -0.0363 0.0206 1.0000
13.250 1.4099 0.05743 0.05041 -0.0351 0.0206 1.0000
13.500 1.4173 0.06007 0.05323 -0.0344 0.0207 1.0000
13.750 1.4221 0.06282 0.05614 -0.0340 0.0209 1.0000
14.000 1.4244 0.06585 0.05937 -0.0337 0.0210 1.0000
14.250 1.4234 0.06919 0.06293 -0.0339 0.0213 1.0000
14.500 1.4188 0.07316 0.06717 -0.0345 0.0216 1.0000
14.750 1.4104 0.07784 0.07216 -0.0355 0.0221 1.0000
15.000 1.3993 0.08326 0.07790 -0.0370 0.0227 1.0000
15.250 1.3817 0.08978 0.08474 -0.0395 0.0232 1.0000
15.500 1.3641 0.09661 0.09185 -0.0426 0.0236 1.0000
15.750 1.3455 0.10393 0.09941 -0.0463 0.0240 1.0000
16.000 1.3262 0.11171 0.10742 -0.0506 0.0243 1.0000
16.250 1.3068 0.11993 0.11585 -0.0556 0.0246 1.0000
16.500 1.2869 0.12865 0.12476 -0.0612 0.0248 1.0000
16.750 1.2658 0.13819 0.13447 -0.0676 0.0250 1.0000
17.000 1.2443 0.14842 0.14486 -0.0746 0.0252 1.0000
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Polar data table (+)
Polar graphs
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