GOE 396 AIRFOIL (goe396-il) Xfoil prediction polar at RE=200,000 Ncrit=0
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Airfoil: GOE 396 AIRFOIL (goe396-il) Reynolds number: 200,000 Max Cl/Cd: 92.37 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe396-il-200000.txt Download as CSV file: xf-goe396-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 396 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3212 0.12549 0.12188 -0.0296 1.0000 0.0153
-10.000 -0.3146 0.12162 0.11802 -0.0294 1.0000 0.0157
-9.750 -0.3092 0.11860 0.11502 -0.0296 1.0000 0.0161
-9.500 -0.3041 0.11586 0.11232 -0.0299 1.0000 0.0164
-9.250 -0.2993 0.11312 0.10960 -0.0301 1.0000 0.0169
-9.000 -0.2949 0.11052 0.10704 -0.0304 1.0000 0.0174
-8.750 -0.2909 0.10800 0.10456 -0.0305 1.0000 0.0178
-8.500 -0.2875 0.10554 0.10214 -0.0306 1.0000 0.0185
-8.250 -0.2848 0.10327 0.09991 -0.0304 1.0000 0.0188
-8.000 -0.2835 0.10108 0.09779 -0.0300 1.0000 0.0193
-7.750 -0.2842 0.09909 0.09585 -0.0292 1.0000 0.0198
-7.500 -0.2884 0.09748 0.09432 -0.0275 1.0000 0.0205
-7.250 -0.2994 0.09658 0.09352 -0.0243 1.0000 0.0208
-7.000 -0.3190 0.09663 0.09367 -0.0194 1.0000 0.0207
-6.750 -0.3357 0.09638 0.09349 -0.0155 0.9996 0.0209
-6.500 -0.3083 0.09204 0.08914 -0.0230 0.9943 0.0225
-6.250 -0.2689 0.08836 0.08541 -0.0353 0.9877 0.0243
-6.000 -0.2274 0.08497 0.08197 -0.0487 0.9803 0.0248
-5.750 -0.1926 0.08084 0.07779 -0.0573 0.9743 0.0249
-5.500 -0.1689 0.07455 0.07150 -0.0624 0.9700 0.0254
-5.250 -0.1544 0.06975 0.06670 -0.0620 0.9665 0.0266
-5.000 -0.1286 0.06598 0.06291 -0.0662 0.9602 0.0281
-4.750 -0.0900 0.06172 0.05859 -0.0739 0.9568 0.0302
-4.500 -0.0553 0.05796 0.05475 -0.0805 0.9496 0.0326
-4.250 0.0147 0.05407 0.05059 -0.0954 0.9454 0.0350
-4.000 0.0482 0.04821 0.04468 -0.1009 0.9430 0.0361
-3.750 0.0711 0.04510 0.04155 -0.1023 0.9364 0.0381
-3.500 0.1120 0.04161 0.03792 -0.1076 0.9322 0.0417
-3.250 0.1637 0.03702 0.03306 -0.1153 0.9292 0.0478
-3.000 0.1883 0.03494 0.03091 -0.1160 0.9214 0.0537
-2.750 0.2322 0.03108 0.02675 -0.1206 0.9171 0.0618
-2.500 0.2682 0.02841 0.02370 -0.1227 0.9103 0.0738
-2.250 0.3057 0.02050 0.01493 -0.1237 0.9047 0.0342
-2.000 0.3389 0.01734 0.01102 -0.1243 0.8999 0.0362
-1.750 0.3658 0.01582 0.00922 -0.1238 0.8916 0.0415
-1.500 0.3976 0.01440 0.00746 -0.1240 0.8863 0.0535
-1.250 0.4240 0.01372 0.00659 -0.1233 0.8775 0.0703
-1.000 0.4524 0.01323 0.00595 -0.1231 0.8702 0.0831
-0.750 0.4798 0.01263 0.00528 -0.1226 0.8622 0.0942
-0.500 0.5058 0.01223 0.00488 -0.1219 0.8532 0.1201
-0.250 0.5336 0.01194 0.00458 -0.1216 0.8452 0.1627
0.000 0.5590 0.01181 0.00444 -0.1208 0.8345 0.1917
0.250 0.5840 0.01167 0.00430 -0.1200 0.8230 0.2164
0.500 0.6093 0.01152 0.00419 -0.1192 0.8121 0.2474
0.750 0.6349 0.01131 0.00404 -0.1185 0.8020 0.2850
1.000 0.6590 0.01085 0.00393 -0.1177 0.7922 0.4065
1.250 0.7086 0.00981 0.00374 -0.1224 0.7825 1.0000
1.500 0.7344 0.00988 0.00371 -0.1218 0.7728 1.0000
1.750 0.7602 0.00994 0.00366 -0.1211 0.7624 1.0000
2.000 0.7849 0.01000 0.00367 -0.1203 0.7504 1.0000
2.250 0.8098 0.01008 0.00374 -0.1196 0.7390 1.0000
2.500 0.8351 0.01016 0.00379 -0.1189 0.7279 1.0000
2.750 0.8606 0.01023 0.00383 -0.1183 0.7170 1.0000
3.000 0.8859 0.01032 0.00390 -0.1176 0.7055 1.0000
3.250 0.9107 0.01041 0.00404 -0.1168 0.6922 1.0000
3.500 0.9354 0.01051 0.00417 -0.1161 0.6787 1.0000
3.750 0.9602 0.01064 0.00434 -0.1153 0.6653 1.0000
4.000 0.9840 0.01076 0.00445 -0.1143 0.6462 1.0000
4.250 1.0041 0.01087 0.00447 -0.1122 0.6061 1.0000
4.500 1.0225 0.01114 0.00457 -0.1100 0.5522 1.0000
4.750 1.0341 0.01190 0.00478 -0.1066 0.4446 1.0000
5.000 1.0289 0.01450 0.00582 -0.1013 0.1829 1.0000
5.250 1.0357 0.01654 0.00704 -0.0981 0.0425 1.0000
5.500 1.0515 0.01768 0.00817 -0.0958 0.0250 1.0000
5.750 1.0684 0.01869 0.00939 -0.0937 0.0216 1.0000
6.000 1.0833 0.01988 0.01079 -0.0912 0.0205 1.0000
6.250 1.0948 0.02131 0.01237 -0.0883 0.0202 1.0000
6.500 1.1051 0.02293 0.01405 -0.0853 0.0201 1.0000
6.750 1.1188 0.02454 0.01570 -0.0828 0.0192 1.0000
7.000 1.1377 0.02662 0.01780 -0.0811 0.0193 1.0000
7.250 1.1636 0.02812 0.01933 -0.0802 0.0209 1.0000
11.500 1.0488 0.09347 0.09042 -0.0380 0.0672 1.0000
11.750 1.0277 0.10000 0.09703 -0.0399 0.0681 1.0000
12.000 1.0087 0.10644 0.10352 -0.0420 0.0686 1.0000
12.250 0.9874 0.11248 0.10962 -0.0443 0.0689 1.0000
12.500 0.9678 0.11864 0.11583 -0.0472 0.0692 1.0000
12.750 0.9467 0.12519 0.12244 -0.0511 0.0693 1.0000
13.000 0.9260 0.13217 0.12945 -0.0558 0.0693 1.0000
13.250 0.9065 0.13959 0.13689 -0.0612 0.0693 1.0000
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Polar data table (+)
Polar graphs
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