GOE 79 (PFALZ 11) AIRFOIL (goe79-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 79 (PFALZ 11) AIRFOIL (goe79-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.11 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe79-il-1000000.txt Download as CSV file: xf-goe79-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.1771 0.07152 0.07001 -0.0284 0.9407 0.0164
-7.000 -0.1699 0.06850 0.06684 -0.0305 0.8996 0.0167
-6.750 -0.2444 0.08126 0.07973 -0.0248 0.9856 0.0162
-6.500 -0.2045 0.07652 0.07493 -0.0353 0.9513 0.0167
-6.250 -0.1730 0.07269 0.07092 -0.0433 0.9072 0.0168
-6.000 -0.1468 0.06932 0.06740 -0.0493 0.8819 0.0168
-5.750 -0.1249 0.06571 0.06370 -0.0529 0.8634 0.0169
-5.500 -0.1104 0.06274 0.06066 -0.0533 0.8464 0.0170
-5.250 -0.0900 0.06012 0.05796 -0.0554 0.8291 0.0171
-5.000 -0.0661 0.05757 0.05532 -0.0583 0.8113 0.0174
-4.750 -0.0398 0.05494 0.05260 -0.0616 0.7926 0.0177
-4.500 -0.0117 0.05227 0.04982 -0.0651 0.7721 0.0182
-4.250 0.0183 0.04954 0.04696 -0.0688 0.7504 0.0189
-4.000 0.0567 0.04670 0.04394 -0.0737 0.7289 0.0195
-3.750 0.0957 0.04388 0.04092 -0.0785 0.7071 0.0196
-3.500 0.1333 0.04097 0.03780 -0.0825 0.6859 0.0196
-3.250 0.1597 0.03792 0.03463 -0.0845 0.6676 0.0197
-3.000 0.1842 0.03584 0.03246 -0.0857 0.6513 0.0199
-2.750 0.2122 0.03398 0.03050 -0.0873 0.6386 0.0201
-2.500 0.2421 0.03220 0.02861 -0.0890 0.6266 0.0204
-2.250 0.2734 0.03041 0.02671 -0.0907 0.6157 0.0209
-2.000 0.3054 0.02866 0.02482 -0.0922 0.6057 0.0215
-1.750 0.3413 0.02695 0.02295 -0.0936 0.5968 0.0224
-1.500 0.3783 0.02522 0.02099 -0.0947 0.5881 0.0226
-1.250 0.4110 0.02349 0.01907 -0.0955 0.5788 0.0226
0.000 0.5605 0.01723 0.01215 -0.0987 0.5249 0.0257
0.250 0.5923 0.01644 0.01112 -0.0986 0.5143 0.0259
0.500 0.6224 0.01489 0.00941 -0.0993 0.5027 0.0262
0.750 0.6510 0.01418 0.00860 -0.0997 0.4888 0.0265
1.000 0.6797 0.01361 0.00792 -0.0999 0.4711 0.0269
1.250 0.7084 0.01314 0.00727 -0.1000 0.4457 0.0276
1.500 0.7377 0.01318 0.00694 -0.0994 0.4115 0.0297
1.750 0.7660 0.01226 0.00579 -0.0997 0.3746 0.0304
2.000 0.7934 0.01208 0.00546 -0.0998 0.3463 0.0313
2.250 0.8213 0.01236 0.00551 -0.0994 0.3266 0.0340
2.500 0.8496 0.01169 0.00474 -0.0995 0.3136 0.0350
2.750 0.8775 0.01147 0.00450 -0.0996 0.3031 0.0364
4.000 1.0171 0.01080 0.00357 -0.0990 0.2612 0.0368
4.250 1.0450 0.01076 0.00349 -0.0989 0.2535 0.0348
4.500 1.0725 0.01079 0.00350 -0.0989 0.2454 0.0356
4.750 1.1002 0.01083 0.00354 -0.0988 0.2383 0.0362
5.000 1.1275 0.01093 0.00361 -0.0987 0.2303 0.0365
5.250 1.1550 0.01101 0.00369 -0.0986 0.2234 0.0377
5.500 1.1819 0.01117 0.00382 -0.0984 0.2152 0.0393
5.750 1.2091 0.01128 0.00393 -0.0983 0.2077 0.0428
6.000 1.2357 0.01149 0.00409 -0.0981 0.1962 0.0490
6.250 1.2587 0.01048 0.00449 -0.0976 0.1842 1.0000
6.500 1.2846 0.01081 0.00472 -0.0973 0.1684 1.0000
6.750 1.3085 0.01142 0.00511 -0.0968 0.1330 1.0000
7.000 1.3302 0.01235 0.00576 -0.0960 0.0923 1.0000
7.250 1.3554 0.01273 0.00611 -0.0957 0.0886 1.0000
7.500 1.3803 0.01313 0.00650 -0.0952 0.0849 1.0000
7.750 1.4051 0.01353 0.00690 -0.0948 0.0816 1.0000
8.000 1.4301 0.01386 0.00726 -0.0944 0.0799 1.0000
8.250 1.4554 0.01414 0.00758 -0.0941 0.0785 1.0000
8.500 1.4802 0.01447 0.00794 -0.0937 0.0764 1.0000
8.750 1.5043 0.01486 0.00834 -0.0932 0.0741 1.0000
9.000 1.5278 0.01532 0.00881 -0.0926 0.0715 1.0000
9.250 1.5500 0.01592 0.00946 -0.0918 0.0684 1.0000
9.500 1.5747 0.01617 0.00975 -0.0915 0.0676 1.0000
9.750 1.5991 0.01644 0.01005 -0.0910 0.0665 1.0000
10.000 1.6231 0.01674 0.01039 -0.0906 0.0648 1.0000
10.250 1.6465 0.01708 0.01075 -0.0900 0.0626 1.0000
10.500 1.6688 0.01753 0.01120 -0.0894 0.0600 1.0000
10.750 1.6902 0.01805 0.01175 -0.0885 0.0574 1.0000
11.000 1.7138 0.01830 0.01205 -0.0880 0.0558 1.0000
11.250 1.7362 0.01866 0.01242 -0.0874 0.0527 1.0000
11.500 1.7566 0.01919 0.01292 -0.0865 0.0485 1.0000
11.750 1.7775 0.01963 0.01338 -0.0857 0.0449 1.0000
12.000 1.7958 0.02027 0.01399 -0.0845 0.0399 1.0000
12.250 1.8118 0.02107 0.01475 -0.0830 0.0342 1.0000
12.500 1.8258 0.02196 0.01564 -0.0813 0.0292 1.0000
12.750 1.8377 0.02290 0.01659 -0.0792 0.0254 1.0000
13.000 1.8464 0.02390 0.01764 -0.0766 0.0226 1.0000
13.250 1.8508 0.02497 0.01875 -0.0734 0.0208 1.0000
13.500 1.8541 0.02624 0.02008 -0.0704 0.0192 1.0000
13.750 1.8598 0.02748 0.02140 -0.0681 0.0183 1.0000
14.000 1.8631 0.02904 0.02303 -0.0659 0.0174 1.0000
14.250 1.8636 0.03101 0.02508 -0.0640 0.0165 1.0000
14.500 1.8628 0.03331 0.02748 -0.0625 0.0158 1.0000
14.750 1.8659 0.03538 0.02965 -0.0614 0.0154 1.0000
15.000 1.8670 0.03778 0.03217 -0.0606 0.0150 1.0000
15.250 1.8662 0.04055 0.03504 -0.0601 0.0146 1.0000
15.500 1.8628 0.04375 0.03834 -0.0598 0.0143 1.0000
15.750 1.8569 0.04743 0.04213 -0.0599 0.0139 1.0000
16.000 1.8478 0.05167 0.04648 -0.0603 0.0136 1.0000
16.250 1.8350 0.05652 0.05147 -0.0610 0.0134 1.0000
16.500 1.8179 0.06210 0.05718 -0.0620 0.0131 1.0000
16.750 1.7978 0.06819 0.06341 -0.0633 0.0129 1.0000
17.000 1.7820 0.07390 0.06925 -0.0647 0.0128 1.0000
17.250 1.7674 0.07956 0.07505 -0.0663 0.0127 1.0000
17.500 1.7501 0.08578 0.08140 -0.0681 0.0127 1.0000
17.750 1.7321 0.09230 0.08805 -0.0702 0.0126 1.0000
18.000 1.7136 0.09901 0.09490 -0.0725 0.0125 1.0000
18.250 1.6940 0.10604 0.10205 -0.0750 0.0124 1.0000
18.500 1.6763 0.11283 0.10896 -0.0776 0.0123 1.0000
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Polar data table (+)
Polar graphs
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