GOE 368 AIRFOIL (goe368-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 368 AIRFOIL (goe368-il) Reynolds number: 500,000 Max Cl/Cd: 83.91 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe368-il-500000.txt Download as CSV file: xf-goe368-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 368 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3392 0.09462 0.09257 -0.0070 1.0000 0.0158
-9.000 -0.4283 0.09955 0.09737 -0.0057 1.0000 0.0146
-8.750 -0.4239 0.09652 0.09435 -0.0059 1.0000 0.0151
-8.500 -0.4186 0.09361 0.09146 -0.0067 1.0000 0.0154
-8.250 -0.4131 0.09090 0.08877 -0.0073 1.0000 0.0158
-8.000 -0.4091 0.08795 0.08584 -0.0082 1.0000 0.0161
-7.750 -0.4067 0.08488 0.08280 -0.0093 1.0000 0.0163
-7.500 -0.4060 0.08196 0.07992 -0.0101 1.0000 0.0167
-7.250 -0.4065 0.07897 0.07697 -0.0111 1.0000 0.0171
-7.000 -0.4016 0.07539 0.07341 -0.0138 1.0000 0.0175
-6.750 -0.3950 0.07148 0.06952 -0.0170 1.0000 0.0180
-6.500 -0.3863 0.06724 0.06528 -0.0207 1.0000 0.0186
-6.250 -0.3747 0.06258 0.06061 -0.0248 1.0000 0.0195
-6.000 -0.3584 0.05748 0.05547 -0.0293 1.0000 0.0205
-5.750 -0.3366 0.05205 0.04997 -0.0339 1.0000 0.0213
-5.500 -0.3177 0.04349 0.04121 -0.0396 1.0000 0.0215
-5.250 -0.3106 0.02950 0.02652 -0.0460 1.0000 0.0229
-5.000 -0.2930 0.02683 0.02376 -0.0456 1.0000 0.0240
-4.750 -0.2648 0.02408 0.02079 -0.0472 0.9981 0.0256
-4.500 -0.2244 0.01732 0.01287 -0.0497 0.9929 0.0170
-4.250 -0.1859 0.01464 0.00965 -0.0514 0.9864 0.0158
-4.000 -0.1483 0.01349 0.00838 -0.0535 0.9780 0.0172
-3.750 -0.1097 0.01236 0.00710 -0.0555 0.9672 0.0181
-3.500 -0.0722 0.01115 0.00573 -0.0571 0.9486 0.0184
-3.250 -0.0310 0.01024 0.00467 -0.0594 0.9148 0.0196
-3.000 0.0030 0.00977 0.00393 -0.0601 0.8617 0.0210
-2.750 0.0287 0.00929 0.00317 -0.0591 0.8224 0.0239
-2.500 0.0542 0.00904 0.00269 -0.0582 0.7903 0.0279
-2.250 0.0799 0.00883 0.00226 -0.0573 0.7566 0.0358
-2.000 0.1049 0.00854 0.00217 -0.0566 0.7196 0.1273
-1.750 0.1312 0.00871 0.00218 -0.0560 0.6870 0.1385
-1.500 0.1579 0.00887 0.00217 -0.0555 0.6617 0.1451
-1.250 0.1846 0.00896 0.00219 -0.0551 0.6415 0.1531
-1.000 0.2118 0.00912 0.00221 -0.0547 0.6230 0.1591
-0.750 0.2385 0.00905 0.00207 -0.0543 0.6053 0.1631
-0.500 0.2653 0.00904 0.00200 -0.0539 0.5863 0.1665
-0.250 0.2923 0.00904 0.00192 -0.0536 0.5641 0.1704
0.000 0.3192 0.00905 0.00182 -0.0532 0.5379 0.1745
0.250 0.3458 0.00905 0.00174 -0.0528 0.5056 0.1802
0.500 0.3722 0.00916 0.00170 -0.0524 0.4720 0.1867
0.750 0.3985 0.00924 0.00169 -0.0520 0.4451 0.1940
1.000 0.4253 0.00937 0.00171 -0.0516 0.4238 0.2018
1.250 0.4519 0.00943 0.00173 -0.0513 0.4065 0.2107
1.500 0.4787 0.00951 0.00177 -0.0510 0.3910 0.2196
1.750 0.5056 0.00960 0.00182 -0.0508 0.3764 0.2291
2.250 0.5593 0.00971 0.00193 -0.0502 0.3468 0.2527
2.750 0.6122 0.00964 0.00213 -0.0498 0.3162 0.3670
3.000 0.6441 0.00839 0.00226 -0.0507 0.2994 1.0000
3.250 0.6704 0.00860 0.00237 -0.0503 0.2834 1.0000
3.500 0.6966 0.00882 0.00251 -0.0499 0.2678 1.0000
3.750 0.7227 0.00906 0.00268 -0.0495 0.2537 1.0000
4.000 0.7487 0.00930 0.00284 -0.0492 0.2400 1.0000
4.250 0.7745 0.00957 0.00300 -0.0488 0.2234 1.0000
4.500 0.8007 0.00979 0.00318 -0.0484 0.2128 1.0000
4.750 0.8268 0.01002 0.00339 -0.0481 0.2035 1.0000
5.000 0.8528 0.01027 0.00358 -0.0477 0.1918 1.0000
5.250 0.8786 0.01052 0.00378 -0.0474 0.1794 1.0000
5.500 0.9045 0.01078 0.00398 -0.0470 0.1644 1.0000
5.750 0.9292 0.01122 0.00424 -0.0466 0.1317 1.0000
6.000 0.9459 0.01300 0.00537 -0.0452 0.0198 1.0000
6.250 0.9712 0.01339 0.00585 -0.0446 0.0175 1.0000
6.500 0.9960 0.01386 0.00645 -0.0440 0.0162 1.0000
6.750 1.0201 0.01445 0.00717 -0.0433 0.0151 1.0000
7.000 1.0425 0.01531 0.00820 -0.0424 0.0134 1.0000
7.250 1.0632 0.01641 0.00947 -0.0413 0.0126 1.0000
7.500 1.0811 0.01783 0.01105 -0.0399 0.0122 1.0000
7.750 1.1015 0.01878 0.01210 -0.0388 0.0118 1.0000
8.000 1.1203 0.01989 0.01332 -0.0375 0.0116 1.0000
8.250 1.1369 0.02122 0.01476 -0.0360 0.0115 1.0000
8.500 1.1505 0.02294 0.01656 -0.0341 0.0117 1.0000
8.750 1.1628 0.02510 0.01876 -0.0321 0.0123 1.0000
9.000 1.1794 0.02689 0.02059 -0.0307 0.0123 1.0000
9.250 1.1979 0.02841 0.02217 -0.0295 0.0124 1.0000
9.500 1.2179 0.02879 0.02267 -0.0283 0.0129 1.0000
9.750 1.1978 0.02006 0.01459 -0.0237 0.0173 1.0000
10.000 1.2112 0.02235 0.01702 -0.0221 0.0170 1.0000
10.250 1.2209 0.02452 0.01935 -0.0204 0.0160 1.0000
10.500 1.2275 0.02693 0.02189 -0.0185 0.0153 1.0000
10.750 1.2295 0.02939 0.02448 -0.0161 0.0147 1.0000
11.000 1.2308 0.03217 0.02735 -0.0140 0.0142 1.0000
11.250 1.2343 0.03534 0.03063 -0.0125 0.0137 1.0000
11.500 1.2300 0.03870 0.03412 -0.0108 0.0134 1.0000
11.750 1.2226 0.04257 0.03814 -0.0095 0.0131 1.0000
14.250 1.0425 0.10072 0.09787 -0.0291 0.0126 1.0000
14.500 1.0238 0.10673 0.10403 -0.0339 0.0129 1.0000
14.750 0.9976 0.11339 0.11088 -0.0394 0.0133 1.0000
15.000 0.9735 0.12070 0.11834 -0.0449 0.0133 1.0000
15.250 0.9416 0.13059 0.12841 -0.0527 0.0137 1.0000
15.500 0.9016 0.14362 0.14168 -0.0625 0.0147 1.0000
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Polar data table (+)
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