GOE 79 (PFALZ 11) AIRFOIL (goe79-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 79 (PFALZ 11) AIRFOIL (goe79-il) Reynolds number: 500,000 Max Cl/Cd: 97.35 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe79-il-500000-n5.txt Download as CSV file: xf-goe79-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 79 (PFALZ 11) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2363 0.10129 0.09909 -0.0183 1.0000 0.0162
-9.250 -0.2318 0.09812 0.09593 -0.0193 1.0000 0.0162
-9.000 -0.2276 0.09499 0.09282 -0.0202 1.0000 0.0162
-8.750 -0.2222 0.09184 0.08968 -0.0206 1.0000 0.0163
-8.500 -0.2162 0.08895 0.08682 -0.0208 0.9997 0.0164
-8.250 -0.2029 0.08540 0.08327 -0.0234 0.9723 0.0167
-8.000 -0.1852 0.08147 0.07930 -0.0272 0.9337 0.0173
-7.750 -0.1749 0.07817 0.07592 -0.0291 0.9039 0.0180
-7.500 -0.1687 0.07524 0.07291 -0.0300 0.8820 0.0183
-7.000 -0.1568 0.06940 0.06694 -0.0326 0.8476 0.0186
-6.750 -0.1459 0.06609 0.06358 -0.0355 0.8327 0.0186
-6.500 -0.1326 0.06268 0.06012 -0.0390 0.8184 0.0187
-6.000 -0.1056 0.05581 0.05314 -0.0435 0.7910 0.0189
-5.750 -0.1227 0.06724 0.06447 -0.0501 0.8231 0.0188
-5.500 -0.1028 0.06450 0.06166 -0.0525 0.8075 0.0190
-5.250 -0.0800 0.06181 0.05888 -0.0556 0.7892 0.0192
-5.000 -0.0551 0.05912 0.05609 -0.0590 0.7684 0.0196
-4.750 -0.0284 0.05642 0.05325 -0.0625 0.7465 0.0201
-4.500 0.0008 0.05365 0.05033 -0.0665 0.7255 0.0209
-4.250 0.0389 0.05066 0.04716 -0.0722 0.7055 0.0213
-4.000 0.0768 0.04771 0.04402 -0.0774 0.6869 0.0214
-3.750 0.1127 0.04485 0.04095 -0.0816 0.6708 0.0215
-3.500 0.1393 0.04220 0.03818 -0.0836 0.6554 0.0215
-3.000 0.1908 0.03796 0.03375 -0.0867 0.6266 0.0219
-2.750 0.2210 0.03602 0.03168 -0.0887 0.6137 0.0223
-2.500 0.2521 0.03418 0.02970 -0.0906 0.6017 0.0229
-2.250 0.2864 0.03231 0.02768 -0.0927 0.5911 0.0241
-2.000 0.3247 0.03039 0.02553 -0.0948 0.5825 0.0244
-1.750 0.3602 0.02849 0.02341 -0.0964 0.5736 0.0245
-1.500 0.3933 0.02673 0.02145 -0.0975 0.5648 0.0246
-1.250 0.4225 0.02485 0.01946 -0.0987 0.5550 0.0247
-1.000 0.4505 0.02347 0.01801 -0.0996 0.5463 0.0250
-0.750 0.4791 0.02239 0.01683 -0.1004 0.5368 0.0255
-0.500 0.5093 0.02132 0.01563 -0.1011 0.5250 0.0263
-0.250 0.5403 0.02024 0.01435 -0.1015 0.5098 0.0271
0.250 0.5884 0.00646 0.00021 -0.0971 0.4693 0.0282
0.750 0.6633 0.01633 0.00950 -0.1025 0.4383 0.0287
1.000 0.6912 0.01582 0.00881 -0.1027 0.4077 0.0292
1.250 0.7191 0.01545 0.00819 -0.1028 0.3753 0.0299
1.500 0.7481 0.01572 0.00805 -0.1022 0.3502 0.0325
1.750 0.7762 0.01476 0.00698 -0.1025 0.3311 0.0331
2.000 0.8048 0.01408 0.00613 -0.1024 0.3172 0.0274
2.250 0.8330 0.01371 0.00564 -0.1023 0.3064 0.0269
2.500 0.8610 0.01341 0.00522 -0.1022 0.2971 0.0268
2.750 0.8887 0.01320 0.00490 -0.1020 0.2866 0.0269
3.000 0.9164 0.01304 0.00466 -0.1019 0.2771 0.0274
3.250 0.9438 0.01307 0.00458 -0.1017 0.2689 0.0282
3.500 0.9714 0.01289 0.00443 -0.1016 0.2624 0.0292
3.750 0.9988 0.01284 0.00436 -0.1015 0.2551 0.0294
4.000 1.0261 0.01284 0.00434 -0.1014 0.2489 0.0297
4.250 1.0535 0.01285 0.00436 -0.1013 0.2423 0.0302
4.750 1.1077 0.01302 0.00451 -0.1010 0.2279 0.0318
5.000 1.1345 0.01315 0.00464 -0.1008 0.2201 0.0337
5.250 1.1614 0.01327 0.00477 -0.1007 0.2141 0.0350
5.500 1.1880 0.01344 0.00493 -0.1005 0.2068 0.0363
5.750 1.2144 0.01363 0.00511 -0.1002 0.2001 0.0379
6.000 1.2406 0.01384 0.00530 -0.1000 0.1915 0.0420
6.250 1.2665 0.01410 0.00553 -0.0997 0.1805 0.0518
6.500 1.2880 0.01323 0.00595 -0.0988 0.1655 1.0000
6.750 1.3122 0.01372 0.00630 -0.0983 0.1437 1.0000
7.250 1.3568 0.01520 0.00741 -0.0969 0.0904 1.0000
7.500 1.3808 0.01566 0.00787 -0.0964 0.0865 1.0000
7.750 1.4046 0.01613 0.00833 -0.0958 0.0830 1.0000
8.000 1.4288 0.01651 0.00874 -0.0953 0.0815 1.0000
8.250 1.4528 0.01689 0.00917 -0.0948 0.0801 1.0000
8.500 1.4763 0.01731 0.00965 -0.0942 0.0785 1.0000
8.750 1.4993 0.01777 0.01015 -0.0936 0.0769 1.0000
9.000 1.5217 0.01828 0.01070 -0.0928 0.0754 1.0000
9.250 1.5431 0.01887 0.01133 -0.0920 0.0733 1.0000
9.500 1.5630 0.01957 0.01206 -0.0909 0.0705 1.0000
9.750 1.5860 0.01991 0.01247 -0.0903 0.0691 1.0000
10.000 1.6080 0.02034 0.01296 -0.0896 0.0672 1.0000
10.250 1.6291 0.02082 0.01350 -0.0887 0.0650 1.0000
10.500 1.6489 0.02139 0.01409 -0.0877 0.0625 1.0000
10.750 1.6667 0.02211 0.01484 -0.0864 0.0603 1.0000
11.000 1.6868 0.02256 0.01539 -0.0855 0.0588 1.0000
11.250 1.7060 0.02306 0.01596 -0.0844 0.0565 1.0000
11.500 1.7237 0.02365 0.01659 -0.0831 0.0538 1.0000
11.750 1.7390 0.02436 0.01731 -0.0815 0.0511 1.0000
12.000 1.7539 0.02500 0.01804 -0.0798 0.0488 1.0000
12.250 1.7650 0.02575 0.01883 -0.0776 0.0457 1.0000
12.500 1.7743 0.02666 0.01977 -0.0753 0.0426 1.0000
12.750 1.7829 0.02768 0.02085 -0.0731 0.0391 1.0000
13.000 1.7893 0.02895 0.02215 -0.0710 0.0356 1.0000
13.250 1.7947 0.03042 0.02367 -0.0691 0.0321 1.0000
13.500 1.7982 0.03217 0.02548 -0.0674 0.0291 1.0000
13.750 1.8002 0.03419 0.02757 -0.0659 0.0262 1.0000
14.000 1.8013 0.03645 0.02992 -0.0647 0.0238 1.0000
14.250 1.8004 0.03906 0.03261 -0.0638 0.0217 1.0000
14.500 1.7984 0.04195 0.03559 -0.0632 0.0201 1.0000
14.750 1.7954 0.04511 0.03885 -0.0628 0.0188 1.0000
15.000 1.7900 0.04871 0.04256 -0.0628 0.0177 1.0000
15.250 1.7831 0.05262 0.04658 -0.0631 0.0169 1.0000
15.500 1.7762 0.05666 0.05075 -0.0635 0.0163 1.0000
15.750 1.7671 0.06107 0.05529 -0.0641 0.0157 1.0000
16.000 1.7556 0.06587 0.06022 -0.0649 0.0153 1.0000
16.250 1.7422 0.07108 0.06557 -0.0660 0.0149 1.0000
16.500 1.7275 0.07667 0.07129 -0.0674 0.0145 1.0000
16.750 1.7113 0.08263 0.07738 -0.0690 0.0143 1.0000
17.000 1.6940 0.08898 0.08387 -0.0710 0.0140 1.0000
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Polar data table (+)
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