GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Reynolds number: 100,000 Max Cl/Cd: 45.4 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe344-il-100000.txt Download as CSV file: xf-goe344-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 344 (PFALZ 71) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4892 0.10227 0.09703 -0.0079 1.0000 0.0999
-8.250 -0.5044 0.10046 0.09534 -0.0122 1.0000 0.1022
-8.000 -0.5186 0.09870 0.09357 -0.0218 1.0000 0.1032
-7.750 -0.5016 0.09227 0.08722 -0.0148 1.0000 0.1049
-7.500 -0.4905 0.08878 0.08372 -0.0125 1.0000 0.1076
-7.250 -0.4852 0.08560 0.08056 -0.0132 1.0000 0.1111
-7.000 -0.4886 0.08352 0.07834 -0.0248 1.0000 0.1173
-6.750 -0.4808 0.07815 0.07306 -0.0218 1.0000 0.1188
-6.500 -0.4700 0.07501 0.06998 -0.0180 1.0000 0.1224
-6.250 -0.4601 0.07197 0.06690 -0.0197 1.0000 0.1291
-6.000 -0.4503 0.06775 0.06255 -0.0238 1.0000 0.1339
-5.750 -0.4393 0.06458 0.05943 -0.0215 1.0000 0.1368
-5.500 -0.4209 0.06166 0.05614 -0.0269 1.0000 0.1477
-5.250 -0.4107 0.05782 0.05246 -0.0240 1.0000 0.1500
-4.750 -0.3796 0.05194 0.04641 -0.0238 1.0000 0.1659
-4.500 -0.3592 0.04932 0.04353 -0.0252 1.0000 0.1785
-4.250 -0.3443 0.04633 0.04060 -0.0236 1.0000 0.1820
-4.000 -0.3041 0.03625 0.02916 -0.0284 1.0000 0.1163
-3.750 -0.2836 0.03307 0.02585 -0.0278 1.0000 0.1127
-3.500 -0.2562 0.02809 0.01977 -0.0273 1.0000 0.1026
-3.250 -0.2320 0.02581 0.01708 -0.0266 1.0000 0.1028
-3.000 -0.2086 0.02410 0.01528 -0.0259 1.0000 0.1062
-2.750 -0.1846 0.02306 0.01413 -0.0252 1.0000 0.1108
-2.500 -0.1585 0.02166 0.01238 -0.0244 1.0000 0.1145
-2.250 -0.1323 0.02038 0.01085 -0.0238 1.0000 0.1196
-2.000 -0.1072 0.01967 0.01010 -0.0232 1.0000 0.1291
-1.750 -0.0819 0.01893 0.00935 -0.0226 1.0000 0.1431
-1.500 -0.0557 0.01813 0.00847 -0.0220 1.0000 0.1625
-1.250 -0.0302 0.01747 0.00800 -0.0218 1.0000 0.1874
-1.000 -0.0049 0.01705 0.00772 -0.0214 1.0000 0.2141
-0.750 0.0199 0.01678 0.00758 -0.0210 1.0000 0.2425
-0.500 0.0449 0.01653 0.00744 -0.0206 1.0000 0.2704
-0.250 0.0702 0.01625 0.00734 -0.0202 1.0000 0.2999
0.000 0.0958 0.01595 0.00730 -0.0200 1.0000 0.3430
0.250 0.1351 0.01399 0.00720 -0.0217 1.0000 1.0000
0.500 0.1552 0.01433 0.00734 -0.0207 1.0000 1.0000
0.750 0.1791 0.01473 0.00764 -0.0207 0.9982 1.0000
1.000 0.2429 0.01488 0.00768 -0.0283 0.9838 1.0000
1.250 0.3010 0.01476 0.00752 -0.0345 0.9641 1.0000
1.500 0.3610 0.01447 0.00725 -0.0407 0.9455 1.0000
1.750 0.4160 0.01401 0.00683 -0.0455 0.9219 1.0000
2.000 0.4676 0.01351 0.00637 -0.0493 0.8929 1.0000
2.250 0.5126 0.01308 0.00596 -0.0515 0.8495 1.0000
2.500 0.5509 0.01282 0.00558 -0.0521 0.7879 1.0000
2.750 0.5839 0.01292 0.00535 -0.0517 0.7184 1.0000
3.000 0.6084 0.01340 0.00548 -0.0501 0.6519 1.0000
3.250 0.6307 0.01397 0.00569 -0.0484 0.5946 1.0000
3.500 0.6531 0.01455 0.00598 -0.0468 0.5474 1.0000
3.750 0.6760 0.01512 0.00636 -0.0456 0.5093 1.0000
4.000 0.6994 0.01568 0.00675 -0.0445 0.4789 1.0000
4.250 0.7231 0.01622 0.00715 -0.0435 0.4533 1.0000
4.500 0.7467 0.01672 0.00755 -0.0425 0.4292 1.0000
4.750 0.7698 0.01719 0.00796 -0.0414 0.4049 1.0000
5.000 0.7929 0.01769 0.00833 -0.0404 0.3822 1.0000
5.250 0.8161 0.01819 0.00882 -0.0394 0.3603 1.0000
5.500 0.8393 0.01874 0.00934 -0.0384 0.3399 1.0000
5.750 0.8624 0.01935 0.00985 -0.0375 0.3200 1.0000
6.000 0.8848 0.01986 0.01046 -0.0364 0.2974 1.0000
6.250 0.9065 0.02042 0.01093 -0.0353 0.2740 1.0000
6.500 0.9272 0.02090 0.01148 -0.0339 0.2454 1.0000
6.750 0.9466 0.02150 0.01205 -0.0323 0.2116 1.0000
7.000 0.9662 0.02237 0.01283 -0.0307 0.1797 1.0000
7.250 0.9862 0.02341 0.01370 -0.0294 0.1576 1.0000
7.500 1.0071 0.02457 0.01487 -0.0281 0.1406 1.0000
7.750 1.0283 0.02588 0.01613 -0.0270 0.1278 1.0000
8.000 1.0494 0.02719 0.01741 -0.0259 0.1164 1.0000
8.250 1.0702 0.02857 0.01899 -0.0246 0.1065 1.0000
8.500 1.0908 0.03035 0.02086 -0.0235 0.0981 1.0000
8.750 1.1115 0.03211 0.02256 -0.0226 0.0900 1.0000
9.000 1.1296 0.03423 0.02509 -0.0209 0.0839 1.0000
9.250 1.1488 0.03623 0.02706 -0.0200 0.0777 1.0000
9.500 1.1623 0.03905 0.03037 -0.0179 0.0736 1.0000
9.750 1.1745 0.04177 0.03352 -0.0158 0.0701 1.0000
10.000 1.1890 0.04405 0.03589 -0.0144 0.0664 1.0000
10.250 1.1956 0.04812 0.04024 -0.0126 0.0638 1.0000
10.500 1.1933 0.05147 0.04419 -0.0093 0.0627 1.0000
10.750 1.1865 0.05546 0.04869 -0.0062 0.0621 1.0000
11.000 1.1741 0.05969 0.05333 -0.0031 0.0619 1.0000
11.250 1.1559 0.06392 0.05790 -0.0001 0.0619 1.0000
11.500 1.1322 0.06796 0.06218 0.0029 0.0622 1.0000
11.750 1.1071 0.07266 0.06709 0.0040 0.0625 1.0000
12.000 1.0812 0.07831 0.07292 0.0030 0.0630 1.0000
12.250 1.0559 0.08511 0.07985 -0.0001 0.0636 1.0000
12.500 1.0342 0.09279 0.08758 -0.0039 0.0642 1.0000
12.750 0.9316 0.12478 0.11971 -0.0278 0.0771 1.0000
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Polar data table (+)
Polar graphs
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