GOE 390 AIRFOIL (goe390-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 390 AIRFOIL (goe390-il) Reynolds number: 100,000 Max Cl/Cd: 40.35 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe390-il-100000-n5.txt Download as CSV file: xf-goe390-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 390 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
------ -------- --------- --------- -------- -------- --------
-10.500 0.0762 0.09884 0.09284 -0.1112 0.8304 0.0613
-10.250 0.0761 0.09495 0.08891 -0.1130 0.8237 0.0617
-10.000 0.0757 0.09091 0.08481 -0.1148 0.8180 0.0619
-9.750 0.0745 0.08702 0.08092 -0.1166 0.8102 0.0618
-9.500 0.0715 0.08271 0.07659 -0.1186 0.8035 0.0618
-9.250 0.0631 0.07738 0.07120 -0.1214 0.7982 0.0619
-9.000 -0.0907 0.04934 0.04275 -0.1435 0.7875 0.0616
-8.750 -0.1367 0.04188 0.03445 -0.1448 0.7797 0.0625
-8.500 -0.1158 0.04094 0.03347 -0.1447 0.7754 0.0634
-8.250 -0.1063 0.03990 0.03236 -0.1434 0.7675 0.0643
-8.000 -0.0961 0.03810 0.03030 -0.1426 0.7611 0.0656
-7.750 -0.0850 0.03566 0.02737 -0.1421 0.7561 0.0673
-7.500 -0.0719 0.03399 0.02536 -0.1410 0.7498 0.0686
-7.250 -0.0541 0.03319 0.02452 -0.1398 0.7421 0.0697
-7.000 -0.0320 0.03203 0.02316 -0.1393 0.7362 0.0713
-6.750 -0.0108 0.03072 0.02149 -0.1387 0.7308 0.0737
-6.500 0.0062 0.03004 0.02074 -0.1373 0.7231 0.0755
-6.250 0.0296 0.02933 0.01996 -0.1368 0.7175 0.0779
-6.000 0.0554 0.02828 0.01855 -0.1366 0.7132 0.0811
-5.750 0.0757 0.02782 0.01817 -0.1356 0.7070 0.0830
-5.500 0.0971 0.02728 0.01757 -0.1346 0.7008 0.0858
-5.250 0.1228 0.02661 0.01677 -0.1343 0.6958 0.0892
-5.000 0.1515 0.02606 0.01616 -0.1345 0.6919 0.0928
-4.750 0.1700 0.02577 0.01582 -0.1330 0.6850 0.0964
-4.500 0.1936 0.02551 0.01559 -0.1323 0.6792 0.1000
-4.250 0.2215 0.02506 0.01503 -0.1323 0.6745 0.1047
-4.000 0.2488 0.02480 0.01474 -0.1321 0.6698 0.1093
-3.750 0.2684 0.02469 0.01462 -0.1308 0.6628 0.1139
-3.500 0.2943 0.02449 0.01438 -0.1303 0.6573 0.1190
-3.250 0.3237 0.02416 0.01397 -0.1305 0.6529 0.1247
-3.000 0.3471 0.02404 0.01379 -0.1297 0.6472 0.1307
-2.750 0.3688 0.02393 0.01371 -0.1286 0.6405 0.1363
-2.500 0.3965 0.02366 0.01333 -0.1284 0.6351 0.1444
-2.250 0.4275 0.02330 0.01291 -0.1288 0.6308 0.1531
-2.000 0.4445 0.02332 0.01301 -0.1270 0.6233 0.1613
-1.750 0.4690 0.02316 0.01282 -0.1264 0.6173 0.1724
-1.500 0.4979 0.02290 0.01252 -0.1265 0.6125 0.1850
-1.250 0.5212 0.02282 0.01249 -0.1257 0.6065 0.1970
-1.000 0.5417 0.02284 0.01256 -0.1245 0.5993 0.2092
-0.750 0.5689 0.02270 0.01238 -0.1243 0.5936 0.2234
-0.500 0.5973 0.02256 0.01221 -0.1243 0.5885 0.2393
-0.250 0.6141 0.02273 0.01250 -0.1225 0.5809 0.2545
0.000 0.6391 0.02268 0.01248 -0.1220 0.5750 0.2766
0.250 0.6692 0.02249 0.01230 -0.1224 0.5703 0.3072
0.500 0.6856 0.02264 0.01263 -0.1206 0.5628 0.3395
0.750 0.7076 0.02258 0.01276 -0.1197 0.5562 0.3955
1.000 0.7349 0.02227 0.01274 -0.1195 0.5512 0.5002
1.250 0.7518 0.02230 0.01307 -0.1176 0.5447 0.5984
1.500 0.7669 0.02215 0.01340 -0.1148 0.5384 0.7295
1.750 0.8149 0.02191 0.01334 -0.1180 0.5329 1.0000
2.000 0.8354 0.02220 0.01348 -0.1169 0.5272 1.0000
2.250 0.8502 0.02261 0.01382 -0.1149 0.5205 1.0000
2.500 0.8734 0.02282 0.01388 -0.1142 0.5152 1.0000
2.750 0.9010 0.02297 0.01383 -0.1142 0.5109 1.0000
3.000 0.9095 0.02355 0.01442 -0.1112 0.5044 1.0000
3.250 0.9280 0.02391 0.01467 -0.1099 0.4989 1.0000
3.500 0.9546 0.02407 0.01467 -0.1097 0.4945 1.0000
3.750 0.9711 0.02455 0.01509 -0.1081 0.4893 1.0000
4.000 0.9844 0.02515 0.01566 -0.1062 0.4837 1.0000
4.250 1.0057 0.02550 0.01592 -0.1053 0.4790 1.0000
4.500 1.0347 0.02564 0.01590 -0.1056 0.4751 1.0000
4.750 1.0456 0.02639 0.01665 -0.1034 0.4698 1.0000
5.000 1.0592 0.02708 0.01732 -0.1017 0.4645 1.0000
5.250 1.0807 0.02747 0.01763 -0.1010 0.4601 1.0000
5.500 1.1106 0.02759 0.01760 -0.1013 0.4564 1.0000
5.750 1.1187 0.02855 0.01859 -0.0991 0.4513 1.0000
6.000 1.1298 0.02941 0.01946 -0.0973 0.4462 1.0000
6.250 1.1498 0.02991 0.01990 -0.0965 0.4418 1.0000
6.500 1.1789 0.03004 0.01989 -0.0967 0.4381 1.0000
6.750 1.1879 0.03106 0.02095 -0.0948 0.4334 1.0000
7.000 1.1931 0.03230 0.02224 -0.0926 0.4282 1.0000
7.250 1.2101 0.03297 0.02288 -0.0916 0.4237 1.0000
7.500 1.2365 0.03319 0.02301 -0.0916 0.4201 1.0000
7.750 1.2539 0.03393 0.02371 -0.0907 0.4161 1.0000
8.000 1.2482 0.03588 0.02580 -0.0878 0.4107 1.0000
8.250 1.2587 0.03698 0.02692 -0.0864 0.4061 1.0000
8.500 1.2815 0.03737 0.02725 -0.0861 0.4024 1.0000
8.750 1.3150 0.03720 0.02695 -0.0867 0.3993 1.0000
9.000 1.2919 0.04043 0.03040 -0.0827 0.3933 1.0000
9.250 1.2919 0.04236 0.03241 -0.0809 0.3882 1.0000
9.500 1.3110 0.04297 0.03298 -0.0803 0.3844 1.0000
9.750 1.3410 0.04283 0.03275 -0.0805 0.3814 1.0000
10.000 1.3143 0.04687 0.03700 -0.0772 0.3752 1.0000
10.250 1.3019 0.05005 0.04030 -0.0752 0.3692 1.0000
10.500 1.3219 0.05055 0.04077 -0.0747 0.3656 1.0000
10.750 1.3537 0.05008 0.04021 -0.0749 0.3630 1.0000
11.000 1.2752 0.05977 0.05029 -0.0708 0.3525 1.0000
11.250 1.2893 0.06083 0.05134 -0.0703 0.3486 1.0000
11.500 1.3208 0.06010 0.05054 -0.0702 0.3462 1.0000
11.750 1.3584 0.05883 0.04918 -0.0703 0.3442 1.0000
12.000 1.2508 0.07319 0.06395 -0.0675 0.3300 1.0000
12.250 1.2840 0.07204 0.06275 -0.0673 0.3284 1.0000
12.500 1.3212 0.07046 0.06110 -0.0672 0.3271 1.0000
13.000 1.2418 0.08594 0.07688 -0.0661 0.3093 1.0000
13.500 1.1906 0.09918 0.09032 -0.0665 0.2931 1.0000
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Polar data table (+)
Polar graphs
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