GOE 414 AIRFOIL (goe414-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 414 AIRFOIL (goe414-il) Reynolds number: 200,000 Max Cl/Cd: 72.95 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe414-il-200000-n5.txt Download as CSV file: xf-goe414-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 414 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3950 0.04398 0.04027 -0.1178 0.9488 0.0190
-9.750 -0.4080 0.03676 0.03245 -0.1226 0.9364 0.0193
-9.500 -0.4043 0.03283 0.02797 -0.1233 0.9280 0.0199
-9.250 -0.3909 0.03006 0.02483 -0.1236 0.9218 0.0206
-9.000 -0.3714 0.02850 0.02312 -0.1237 0.9168 0.0214
-8.750 -0.3531 0.02729 0.02175 -0.1231 0.9101 0.0224
-8.500 -0.3300 0.02597 0.02019 -0.1233 0.9056 0.0239
-8.250 -0.3099 0.02468 0.01858 -0.1227 0.8989 0.0255
-8.000 -0.2866 0.02352 0.01709 -0.1224 0.8927 0.0267
-7.750 -0.2655 0.02188 0.01530 -0.1219 0.8867 0.0283
-7.500 -0.2425 0.02104 0.01435 -0.1215 0.8792 0.0302
-7.250 -0.2166 0.02016 0.01328 -0.1214 0.8737 0.0324
-7.000 -0.1932 0.01938 0.01229 -0.1207 0.8660 0.0342
-6.750 -0.1672 0.01841 0.01114 -0.1206 0.8608 0.0363
-6.500 -0.1439 0.01774 0.01041 -0.1200 0.8527 0.0387
-6.250 -0.1167 0.01710 0.00963 -0.1200 0.8465 0.0411
-6.000 -0.0919 0.01660 0.00899 -0.1194 0.8382 0.0436
-5.750 -0.0648 0.01601 0.00831 -0.1194 0.8319 0.0466
-5.500 -0.0396 0.01559 0.00783 -0.1189 0.8234 0.0496
-5.250 -0.0118 0.01518 0.00729 -0.1189 0.8163 0.0542
-5.000 0.0140 0.01486 0.00698 -0.1185 0.8066 0.0611
-4.750 0.0410 0.01455 0.00661 -0.1183 0.7979 0.0702
-4.500 0.0682 0.01430 0.00625 -0.1181 0.7885 0.0807
-4.250 0.0948 0.01412 0.00598 -0.1178 0.7787 0.0899
-4.000 0.1222 0.01391 0.00570 -0.1177 0.7703 0.0979
-3.750 0.1490 0.01378 0.00547 -0.1175 0.7608 0.1060
-3.500 0.1757 0.01360 0.00525 -0.1174 0.7515 0.1140
-3.250 0.2030 0.01346 0.00499 -0.1172 0.7420 0.1204
-3.000 0.2294 0.01329 0.00479 -0.1169 0.7313 0.1265
-2.750 0.2562 0.01316 0.00459 -0.1167 0.7211 0.1346
-2.500 0.2829 0.01301 0.00439 -0.1165 0.7111 0.1432
-2.250 0.3094 0.01288 0.00422 -0.1163 0.7008 0.1555
-2.000 0.3358 0.01273 0.00408 -0.1161 0.6910 0.1736
-1.750 0.3623 0.01259 0.00396 -0.1159 0.6816 0.1998
-1.500 0.3883 0.01246 0.00390 -0.1157 0.6718 0.2367
-1.250 0.4146 0.01238 0.00386 -0.1154 0.6625 0.2760
-1.000 0.4408 0.01233 0.00382 -0.1152 0.6534 0.3100
-0.750 0.4669 0.01229 0.00380 -0.1149 0.6439 0.3403
-0.500 0.4929 0.01227 0.00377 -0.1146 0.6347 0.3700
-0.250 0.5185 0.01222 0.00377 -0.1143 0.6251 0.4029
0.250 0.5675 0.01194 0.00381 -0.1132 0.6069 0.5321
0.500 0.6076 0.01116 0.00403 -0.1151 0.5972 0.9258
0.750 0.6540 0.01129 0.00405 -0.1193 0.5871 1.0000
1.000 0.6778 0.01143 0.00409 -0.1185 0.5775 1.0000
1.250 0.7017 0.01157 0.00414 -0.1178 0.5677 1.0000
1.500 0.7255 0.01173 0.00420 -0.1171 0.5582 1.0000
1.750 0.7492 0.01189 0.00428 -0.1164 0.5480 1.0000
2.000 0.7730 0.01205 0.00437 -0.1157 0.5379 1.0000
2.250 0.7965 0.01223 0.00447 -0.1149 0.5282 1.0000
2.500 0.8199 0.01241 0.00458 -0.1142 0.5180 1.0000
2.750 0.8434 0.01261 0.00471 -0.1135 0.5081 1.0000
3.000 0.8666 0.01282 0.00484 -0.1127 0.4992 1.0000
3.250 0.8901 0.01303 0.00500 -0.1120 0.4906 1.0000
3.500 0.9135 0.01326 0.00516 -0.1113 0.4836 1.0000
3.750 0.9373 0.01348 0.00535 -0.1107 0.4769 1.0000
4.000 0.9608 0.01373 0.00555 -0.1100 0.4713 1.0000
4.250 0.9849 0.01396 0.00577 -0.1095 0.4656 1.0000
4.500 1.0087 0.01421 0.00600 -0.1089 0.4604 1.0000
4.750 1.0326 0.01448 0.00624 -0.1083 0.4561 1.0000
5.000 1.0570 0.01471 0.00651 -0.1079 0.4516 1.0000
5.250 1.0808 0.01498 0.00678 -0.1074 0.4469 1.0000
5.500 1.1044 0.01527 0.00706 -0.1068 0.4424 1.0000
5.750 1.1281 0.01554 0.00737 -0.1062 0.4377 1.0000
6.000 1.1517 0.01581 0.00769 -0.1057 0.4332 1.0000
6.250 1.1753 0.01611 0.00801 -0.1051 0.4293 1.0000
6.500 1.1977 0.01643 0.00835 -0.1044 0.4236 1.0000
6.750 1.2169 0.01673 0.00869 -0.1030 0.4140 1.0000
7.000 1.2344 0.01706 0.00904 -0.1014 0.4025 1.0000
7.250 1.2516 0.01742 0.00940 -0.0997 0.3923 1.0000
7.500 1.2673 0.01774 0.00979 -0.0977 0.3819 1.0000
7.750 1.2834 0.01808 0.01020 -0.0958 0.3717 1.0000
8.000 1.2962 0.01849 0.01065 -0.0935 0.3556 1.0000
8.250 1.3065 0.01903 0.01116 -0.0908 0.3316 1.0000
8.500 1.3131 0.01981 0.01183 -0.0877 0.2946 1.0000
8.750 1.3078 0.02133 0.01304 -0.0833 0.2477 1.0000
9.000 1.3014 0.02322 0.01466 -0.0792 0.2076 1.0000
9.250 1.2870 0.02581 0.01686 -0.0745 0.1349 1.0000
9.500 1.2705 0.02878 0.01950 -0.0702 0.0867 1.0000
9.750 1.2523 0.03213 0.02254 -0.0662 0.0309 1.0000
10.000 1.2536 0.03415 0.02460 -0.0642 0.0241 1.0000
10.250 1.2573 0.03605 0.02659 -0.0625 0.0216 1.0000
10.500 1.2607 0.03803 0.02868 -0.0610 0.0201 1.0000
10.750 1.2654 0.03997 0.03075 -0.0597 0.0190 1.0000
11.000 1.2684 0.04213 0.03305 -0.0585 0.0179 1.0000
11.250 1.2700 0.04450 0.03555 -0.0574 0.0170 1.0000
11.500 1.2696 0.04717 0.03835 -0.0563 0.0162 1.0000
11.750 1.2674 0.05016 0.04147 -0.0554 0.0156 1.0000
12.000 1.2630 0.05350 0.04498 -0.0547 0.0152 1.0000
12.250 1.2563 0.05722 0.04885 -0.0541 0.0148 1.0000
12.500 1.2520 0.06076 0.05251 -0.0537 0.0145 1.0000
12.750 1.2491 0.06420 0.05609 -0.0534 0.0143 1.0000
13.000 1.2458 0.06775 0.05976 -0.0532 0.0140 1.0000
13.250 1.2424 0.07136 0.06348 -0.0531 0.0137 1.0000
13.500 1.2393 0.07500 0.06723 -0.0531 0.0134 1.0000
13.750 1.2363 0.07864 0.07098 -0.0532 0.0130 1.0000
14.000 1.2339 0.08223 0.07466 -0.0533 0.0125 1.0000
14.250 1.2317 0.08579 0.07830 -0.0535 0.0121 1.0000
14.500 1.2301 0.08927 0.08186 -0.0536 0.0118 1.0000
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Polar data table (+)
Polar graphs
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