GOE 494 AIRFOIL (goe494-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 494 AIRFOIL (goe494-il) Reynolds number: 500,000 Max Cl/Cd: 135.38 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe494-il-500000.txt Download as CSV file: xf-goe494-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 494 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3471 0.10113 0.09889 -0.0282 1.0000 0.0150
-8.250 -0.3490 0.09910 0.09689 -0.0271 1.0000 0.0153
-8.000 -0.3541 0.09760 0.09543 -0.0255 1.0000 0.0159
-7.500 -0.2390 0.07429 0.07225 -0.0453 0.9887 0.0167
-7.250 -0.2311 0.06788 0.06585 -0.0469 0.9866 0.0174
-7.000 -0.2147 0.06405 0.06201 -0.0494 0.9845 0.0179
-6.750 -0.2010 0.06025 0.05821 -0.0526 0.9807 0.0184
-6.500 -0.1847 0.05618 0.05415 -0.0569 0.9758 0.0190
-6.250 -0.1634 0.05162 0.04957 -0.0629 0.9729 0.0200
-6.000 -0.1365 0.04660 0.04453 -0.0709 0.9709 0.0219
-5.750 -0.1802 0.06190 0.05969 -0.0728 0.9731 0.0201
-5.500 -0.1245 0.05622 0.05394 -0.0881 0.9710 0.0234
-5.250 -0.0332 0.03017 0.02791 -0.1016 0.9598 0.0239
-5.000 0.0094 0.01903 0.01654 -0.1180 0.9576 0.0247
-4.750 0.0328 0.01668 0.01413 -0.1203 0.9522 0.0260
-4.500 0.0632 0.01422 0.01155 -0.1241 0.9475 0.0281
-4.250 0.1063 0.01169 0.00861 -0.1297 0.9446 0.0340
-4.000 0.1413 0.00651 0.00282 -0.1365 0.9412 0.0363
-3.750 0.1655 0.01935 0.01540 -0.1425 0.9480 0.0381
-3.500 0.1997 0.01786 0.01368 -0.1444 0.9446 0.0430
-3.250 0.2305 0.01611 0.01161 -0.1457 0.9393 0.0504
-3.000 0.2599 0.01554 0.01092 -0.1461 0.9333 0.0568
-2.750 0.2901 0.01442 0.00969 -0.1472 0.9284 0.0674
-2.500 0.3219 0.01206 0.00673 -0.1465 0.9203 0.0452
-2.250 0.3513 0.01083 0.00531 -0.1467 0.9135 0.0433
-2.000 0.3787 0.01013 0.00448 -0.1464 0.9047 0.0429
-1.750 0.4062 0.00955 0.00381 -0.1461 0.8961 0.0426
-1.500 0.4341 0.00899 0.00316 -0.1459 0.8882 0.0414
-1.250 0.4610 0.00858 0.00271 -0.1455 0.8792 0.0411
-1.000 0.4889 0.00827 0.00234 -0.1454 0.8718 0.0418
-0.750 0.5161 0.00803 0.00207 -0.1452 0.8633 0.0433
-0.500 0.5437 0.00786 0.00187 -0.1450 0.8557 0.0446
-0.250 0.5711 0.00774 0.00171 -0.1448 0.8481 0.0456
0.000 0.5985 0.00766 0.00160 -0.1446 0.8405 0.0464
0.250 0.6260 0.00759 0.00149 -0.1444 0.8335 0.0502
0.500 0.6531 0.00754 0.00146 -0.1441 0.8246 0.0560
0.750 0.6802 0.00718 0.00147 -0.1440 0.8154 0.2160
1.000 0.7069 0.00697 0.00156 -0.1438 0.8060 0.3495
1.250 0.7334 0.00676 0.00169 -0.1436 0.7962 0.4721
1.500 0.7571 0.00583 0.00176 -0.1426 0.7839 1.0000
1.750 0.7826 0.00595 0.00176 -0.1418 0.7655 1.0000
2.000 0.8081 0.00609 0.00181 -0.1411 0.7474 1.0000
2.250 0.8336 0.00622 0.00188 -0.1404 0.7289 1.0000
2.500 0.8591 0.00637 0.00199 -0.1398 0.7104 1.0000
2.750 0.8840 0.00653 0.00209 -0.1389 0.6849 1.0000
3.000 0.9079 0.00672 0.00217 -0.1379 0.6451 1.0000
3.250 0.9253 0.00741 0.00234 -0.1357 0.5298 1.0000
3.500 0.9345 0.00933 0.00308 -0.1326 0.2971 1.0000
3.750 0.9436 0.01165 0.00413 -0.1299 0.0523 1.0000
4.000 0.9664 0.01232 0.00480 -0.1288 0.0336 1.0000
4.250 0.9897 0.01291 0.00543 -0.1279 0.0275 1.0000
4.500 1.0113 0.01373 0.00633 -0.1266 0.0233 1.0000
4.750 1.0342 0.01435 0.00700 -0.1256 0.0213 1.0000
5.000 1.0561 0.01509 0.00781 -0.1244 0.0194 1.0000
5.250 1.0772 0.01596 0.00872 -0.1231 0.0179 1.0000
5.500 1.0936 0.01774 0.01056 -0.1210 0.0161 1.0000
5.750 1.1148 0.01902 0.01191 -0.1197 0.0152 1.0000
6.000 1.1378 0.02015 0.01312 -0.1187 0.0145 1.0000
6.250 1.1615 0.02162 0.01468 -0.1177 0.0139 1.0000
6.500 1.1862 0.02363 0.01686 -0.1167 0.0135 1.0000
6.750 1.2117 0.02674 0.02021 -0.1157 0.0139 1.0000
7.000 1.2396 0.03262 0.02672 -0.1131 0.0205 1.0000
7.250 1.2590 0.03449 0.02880 -0.1117 0.0189 1.0000
7.500 1.2768 0.03687 0.03137 -0.1101 0.0180 1.0000
7.750 1.2939 0.03954 0.03415 -0.1089 0.0172 1.0000
8.000 1.3034 0.04473 0.03958 -0.1071 0.0163 1.0000
8.250 1.2927 0.05440 0.04986 -0.1029 0.0157 1.0000
8.500 1.2962 0.05801 0.05381 -0.1000 0.0156 1.0000
8.750 1.2971 0.06130 0.05741 -0.0969 0.0155 1.0000
9.000 1.3083 0.06055 0.05700 -0.0936 0.0146 1.0000
9.250 1.3090 0.06344 0.06019 -0.0903 0.0136 1.0000
9.500 1.3012 0.06725 0.06423 -0.0871 0.0131 1.0000
9.750 1.2862 0.07073 0.06790 -0.0832 0.0129 1.0000
10.000 1.2666 0.07417 0.07151 -0.0796 0.0129 1.0000
10.250 1.2456 0.07825 0.07573 -0.0773 0.0129 1.0000
10.500 1.2234 0.08306 0.08070 -0.0766 0.0129 1.0000
10.750 1.2006 0.08873 0.08651 -0.0775 0.0130 1.0000
11.000 1.1767 0.09551 0.09342 -0.0803 0.0132 1.0000
11.250 1.1531 0.10362 0.10161 -0.0850 0.0135 1.0000
11.500 1.1312 0.11304 0.11112 -0.0915 0.0141 1.0000
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Polar data table (+)
Polar graphs
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