GOE 408 AIRFOIL (goe408-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 408 AIRFOIL (goe408-il) Reynolds number: 200,000 Max Cl/Cd: 78.35 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe408-il-200000.txt Download as CSV file: xf-goe408-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 408 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4066 0.10956 0.10606 -0.0243 1.0000 0.0351
-8.500 -0.4106 0.10703 0.10359 -0.0249 1.0000 0.0351
-8.250 -0.4179 0.10470 0.10130 -0.0252 1.0000 0.0352
-8.000 -0.4094 0.09835 0.09497 -0.0232 1.0000 0.0357
-7.750 -0.3988 0.09431 0.09093 -0.0212 1.0000 0.0362
-7.500 -0.4001 0.09163 0.08830 -0.0200 1.0000 0.0365
-7.250 -0.4011 0.08898 0.08568 -0.0186 1.0000 0.0372
-7.000 -0.4008 0.08622 0.08296 -0.0182 1.0000 0.0381
-6.750 -0.4000 0.08338 0.08015 -0.0184 1.0000 0.0385
-6.500 -0.3988 0.08043 0.07723 -0.0187 1.0000 0.0394
-6.250 -0.3966 0.07754 0.07437 -0.0193 1.0000 0.0412
-6.000 -0.3921 0.07470 0.07152 -0.0209 1.0000 0.0428
-5.750 -0.3795 0.07252 0.06916 -0.0260 1.0000 0.0442
-5.500 -0.3735 0.06977 0.06631 -0.0260 1.0000 0.0444
-5.250 -0.3684 0.06711 0.06356 -0.0249 1.0000 0.0445
-5.000 -0.3621 0.06063 0.05715 -0.0254 0.9979 0.0453
-4.750 -0.3361 0.05671 0.05323 -0.0280 0.9932 0.0466
-4.500 -0.3034 0.05312 0.04954 -0.0320 0.9871 0.0489
-4.250 -0.2477 0.05080 0.04656 -0.0386 0.9780 0.0558
-4.000 -0.2258 0.04417 0.03994 -0.0413 0.9724 0.0574
-3.750 -0.1972 0.04120 0.03696 -0.0433 0.9647 0.0602
-3.500 -0.1602 0.03848 0.03359 -0.0449 0.9547 0.0696
-3.250 -0.1332 0.03520 0.03047 -0.0469 0.9490 0.0734
-3.000 -0.1012 0.03294 0.02773 -0.0474 0.9393 0.0840
-2.750 -0.0758 0.03057 0.02542 -0.0480 0.9301 0.0887
-2.500 -0.0413 0.02837 0.02296 -0.0495 0.9248 0.1013
-2.250 -0.0134 0.02668 0.02099 -0.0493 0.9146 0.1135
-2.000 0.0199 0.02486 0.01900 -0.0505 0.9094 0.1281
-1.750 0.0486 0.02319 0.01723 -0.0507 0.9002 0.1434
-1.500 0.0839 0.02152 0.01543 -0.0522 0.8940 0.1606
-1.000 0.1726 0.01733 0.01005 -0.0546 0.8792 0.0934
-0.750 0.2171 0.01581 0.00830 -0.0576 0.8694 0.0887
-0.500 0.2657 0.01487 0.00720 -0.0617 0.8581 0.0900
-0.250 0.3192 0.01396 0.00615 -0.0669 0.8456 0.0899
0.000 0.3666 0.01330 0.00538 -0.0709 0.8306 0.0906
0.250 0.4077 0.01285 0.00485 -0.0736 0.8139 0.0924
0.500 0.4436 0.01255 0.00448 -0.0751 0.7969 0.0947
0.750 0.4754 0.01227 0.00418 -0.0758 0.7799 0.0993
1.000 0.5041 0.01211 0.00399 -0.0759 0.7635 0.1041
1.250 0.5311 0.01203 0.00384 -0.0755 0.7475 0.1094
1.500 0.5566 0.01195 0.00372 -0.0748 0.7319 0.1177
1.750 0.7445 0.01038 0.00396 -0.1116 0.7043 1.0000
2.000 0.7673 0.01058 0.00403 -0.1103 0.6853 1.0000
2.250 0.7875 0.01074 0.00410 -0.1084 0.6636 1.0000
2.500 0.8084 0.01092 0.00416 -0.1067 0.6427 1.0000
2.750 0.8289 0.01109 0.00424 -0.1049 0.6224 1.0000
3.000 0.8502 0.01127 0.00437 -0.1033 0.6041 1.0000
3.250 0.8719 0.01145 0.00449 -0.1019 0.5868 1.0000
3.500 0.8937 0.01165 0.00463 -0.1005 0.5704 1.0000
3.750 0.9155 0.01185 0.00479 -0.0990 0.5542 1.0000
4.000 0.9373 0.01207 0.00498 -0.0976 0.5384 1.0000
4.250 0.9589 0.01230 0.00517 -0.0962 0.5226 1.0000
4.500 0.9800 0.01253 0.00537 -0.0947 0.5061 1.0000
4.750 1.0005 0.01277 0.00560 -0.0931 0.4879 1.0000
5.000 1.0209 0.01303 0.00585 -0.0914 0.4700 1.0000
5.250 1.0408 0.01331 0.00610 -0.0897 0.4516 1.0000
5.500 1.0605 0.01362 0.00637 -0.0879 0.4333 1.0000
5.750 1.0794 0.01391 0.00667 -0.0860 0.4121 1.0000
6.000 1.0974 0.01424 0.00696 -0.0840 0.3899 1.0000
6.250 1.1159 0.01457 0.00733 -0.0820 0.3679 1.0000
6.500 1.1330 0.01496 0.00768 -0.0798 0.3437 1.0000
6.750 1.1488 0.01539 0.00805 -0.0774 0.3120 1.0000
7.000 1.1636 0.01591 0.00846 -0.0749 0.2774 1.0000
7.250 1.1770 0.01656 0.00897 -0.0722 0.2433 1.0000
7.500 1.1914 0.01721 0.00952 -0.0697 0.2154 1.0000
7.750 1.2059 0.01787 0.01011 -0.0673 0.1908 1.0000
8.000 1.2190 0.01862 0.01077 -0.0647 0.1638 1.0000
8.250 1.2294 0.01957 0.01156 -0.0617 0.1272 1.0000
8.500 1.2293 0.02130 0.01276 -0.0569 0.0662 1.0000
8.750 1.2261 0.02294 0.01434 -0.0513 0.0531 1.0000
9.000 1.2290 0.02412 0.01566 -0.0469 0.0465 1.0000
9.250 1.2245 0.02575 0.01732 -0.0414 0.0428 1.0000
9.500 1.2294 0.02696 0.01866 -0.0376 0.0396 1.0000
9.750 1.2357 0.02811 0.01989 -0.0343 0.0364 1.0000
10.000 1.2390 0.02955 0.02136 -0.0308 0.0342 1.0000
10.250 1.2401 0.03187 0.02368 -0.0273 0.0324 1.0000
10.500 1.2500 0.03316 0.02512 -0.0248 0.0309 1.0000
10.750 1.2608 0.03473 0.02681 -0.0226 0.0298 1.0000
11.000 1.2719 0.03645 0.02867 -0.0205 0.0284 1.0000
11.250 1.2815 0.03810 0.03044 -0.0184 0.0274 1.0000
11.500 1.2890 0.03982 0.03223 -0.0164 0.0260 1.0000
11.750 1.3018 0.04233 0.03480 -0.0151 0.0251 1.0000
12.000 1.3110 0.04593 0.03864 -0.0135 0.0242 1.0000
12.250 1.3116 0.04811 0.04108 -0.0110 0.0239 1.0000
12.500 1.3087 0.05076 0.04402 -0.0083 0.0236 1.0000
12.750 1.3045 0.05368 0.04719 -0.0061 0.0234 1.0000
13.000 1.2983 0.05697 0.05073 -0.0042 0.0235 1.0000
13.250 1.2887 0.06056 0.05457 -0.0027 0.0235 1.0000
13.500 1.2737 0.06453 0.05881 -0.0015 0.0234 1.0000
13.750 1.2604 0.06877 0.06329 -0.0010 0.0235 1.0000
14.000 1.2436 0.07348 0.06824 -0.0012 0.0236 1.0000
14.250 1.2254 0.07859 0.07357 -0.0021 0.0236 1.0000
14.500 1.2090 0.08423 0.07937 -0.0031 0.0240 1.0000
14.750 1.1872 0.09028 0.08563 -0.0054 0.0239 1.0000
15.000 1.1666 0.09686 0.09235 -0.0080 0.0241 1.0000
15.250 1.1468 0.10417 0.09982 -0.0105 0.0244 1.0000
15.500 1.1339 0.10961 0.10540 -0.0138 0.0246 1.0000
15.750 1.1151 0.11678 0.11274 -0.0183 0.0248 1.0000
16.000 1.0937 0.12535 0.12150 -0.0243 0.0251 1.0000
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Polar data table (+)
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