GOE 440 AIRFOIL (goe440-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 440 AIRFOIL (goe440-il) Reynolds number: 100,000 Max Cl/Cd: 52.87 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe440-il-100000-n5.txt Download as CSV file: xf-goe440-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 440 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 0.2359 0.11476 0.11047 -0.1164 0.8241 0.0195
-9.000 0.2415 0.11307 0.10879 -0.1176 0.8131 0.0196
-8.750 0.2483 0.11117 0.10687 -0.1188 0.8027 0.0196
-8.500 0.2564 0.10898 0.10465 -0.1200 0.7933 0.0197
-8.250 0.2642 0.10678 0.10244 -0.1211 0.7831 0.0197
-8.000 0.2790 0.10019 0.09583 -0.1197 0.7747 0.0204
-7.500 0.2995 0.09378 0.08929 -0.1198 0.7561 0.0221
-7.250 0.3081 0.09136 0.08683 -0.1204 0.7466 0.0229
-7.000 0.3172 0.08897 0.08437 -0.1211 0.7380 0.0238
-6.750 0.3251 0.08679 0.08218 -0.1218 0.7279 0.0248
-6.500 0.3331 0.08462 0.07997 -0.1226 0.7188 0.0260
-6.250 0.3411 0.08255 0.07785 -0.1235 0.7100 0.0273
-6.000 0.3463 0.08096 0.07626 -0.1243 0.7003 0.0284
-5.750 0.3527 0.07962 0.07490 -0.1261 0.6917 0.0291
-5.500 0.3641 0.07803 0.07329 -0.1298 0.6825 0.0295
-5.250 0.3791 0.07606 0.07131 -0.1343 0.6733 0.0297
-5.000 0.3999 0.07356 0.06873 -0.1400 0.6651 0.0298
-4.750 0.3962 0.06968 0.06488 -0.1321 0.6558 0.0319
-4.500 0.4097 0.06727 0.06242 -0.1337 0.6470 0.0339
-4.250 0.4278 0.06477 0.05985 -0.1374 0.6381 0.0362
-4.000 0.4678 0.06207 0.05706 -0.1502 0.6280 0.0390
-3.750 0.4896 0.05828 0.05322 -0.1543 0.6197 0.0404
-3.500 0.4963 0.05594 0.05085 -0.1516 0.6103 0.0429
-3.250 0.5239 0.05296 0.04778 -0.1565 0.6007 0.0465
-3.000 0.5908 0.04761 0.04210 -0.1740 0.5913 0.0530
-2.750 0.6103 0.04504 0.03949 -0.1746 0.5814 0.0557
-2.500 0.6679 0.04072 0.03481 -0.1864 0.5714 0.0676
-2.000 0.7803 0.03241 0.02541 -0.2012 0.5526 0.0217
-1.750 0.8266 0.02999 0.02241 -0.2057 0.5432 0.0180
-1.500 0.8715 0.02779 0.01959 -0.2097 0.5345 0.0167
-1.250 0.9107 0.02621 0.01748 -0.2121 0.5253 0.0160
-1.000 0.9468 0.02495 0.01570 -0.2135 0.5177 0.0161
-0.750 0.9780 0.02421 0.01464 -0.2140 0.5093 0.0187
-0.500 1.0103 0.02346 0.01367 -0.2150 0.5021 0.0224
-0.250 1.0425 0.02313 0.01304 -0.2161 0.4944 0.0304
0.000 1.0838 0.02191 0.01277 -0.2198 0.4879 0.4740
0.250 1.1081 0.02209 0.01288 -0.2193 0.4810 0.5663
0.500 1.1317 0.02222 0.01293 -0.2186 0.4754 0.6554
0.750 1.1516 0.02230 0.01304 -0.2172 0.4694 0.7474
1.000 1.1648 0.02219 0.01289 -0.2144 0.4640 1.0000
1.250 1.1917 0.02261 0.01296 -0.2147 0.4592 1.0000
1.500 1.2159 0.02307 0.01328 -0.2147 0.4534 1.0000
1.750 1.2406 0.02351 0.01356 -0.2147 0.4483 1.0000
2.000 1.2662 0.02395 0.01380 -0.2148 0.4439 1.0000
2.250 1.2741 0.02446 0.01418 -0.2119 0.4244 1.0000
2.500 1.2870 0.02501 0.01458 -0.2100 0.4108 1.0000
2.750 1.2875 0.02576 0.01517 -0.2060 0.3888 1.0000
3.000 1.2902 0.02671 0.01595 -0.2027 0.3667 1.0000
3.250 1.2938 0.02784 0.01690 -0.1998 0.3416 1.0000
3.500 1.2902 0.02957 0.01828 -0.1963 0.2985 1.0000
3.750 1.2884 0.03152 0.01987 -0.1933 0.2585 1.0000
4.250 1.2384 0.03998 0.02720 -0.1836 0.0996 1.0000
4.750 1.2453 0.04423 0.03149 -0.1803 0.0276 1.0000
5.000 1.2549 0.04586 0.03319 -0.1793 0.0272 1.0000
5.250 1.2636 0.04762 0.03501 -0.1783 0.0273 1.0000
5.500 1.2712 0.04951 0.03700 -0.1773 0.0275 1.0000
5.750 1.2774 0.05160 0.03919 -0.1762 0.0268 1.0000
6.000 1.2827 0.05385 0.04156 -0.1753 0.0266 1.0000
6.250 1.2871 0.05627 0.04415 -0.1744 0.0279 1.0000
6.500 1.2917 0.05872 0.04670 -0.1736 0.0295 1.0000
6.750 1.2958 0.06128 0.04937 -0.1728 0.0315 1.0000
7.000 1.2995 0.06398 0.05216 -0.1722 0.0333 1.0000
7.250 1.3026 0.06680 0.05509 -0.1716 0.0354 1.0000
7.500 1.3078 0.06940 0.05777 -0.1712 0.0376 1.0000
7.750 1.3101 0.07244 0.06092 -0.1707 0.0394 1.0000
8.000 1.3135 0.07536 0.06396 -0.1704 0.0415 1.0000
8.250 1.3123 0.07898 0.06771 -0.1701 0.0425 1.0000
8.500 1.3096 0.08290 0.07178 -0.1698 0.0429 1.0000
8.750 1.3061 0.08701 0.07605 -0.1696 0.0431 1.0000
9.000 1.3015 0.09133 0.08054 -0.1696 0.0430 1.0000
9.250 1.2961 0.09585 0.08524 -0.1696 0.0427 1.0000
9.500 1.2910 0.10035 0.08992 -0.1697 0.0423 1.0000
9.750 1.2855 0.10501 0.09476 -0.1699 0.0417 1.0000
10.000 1.2794 0.10981 0.09975 -0.1702 0.0410 1.0000
10.250 1.2728 0.11472 0.10486 -0.1706 0.0404 1.0000
10.500 1.2645 0.11995 0.11030 -0.1712 0.0397 1.0000
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Polar data table (+)
Polar graphs
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