GOE 79 (PFALZ 11) AIRFOIL (goe79-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 79 (PFALZ 11) AIRFOIL (goe79-il) Reynolds number: 200,000 Max Cl/Cd: 75.69 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe79-il-200000.txt Download as CSV file: xf-goe79-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3043 0.10096 0.09742 -0.0143 1.0000 0.0261
-7.750 -0.2964 0.09751 0.09401 -0.0141 1.0000 0.0263
-7.500 -0.2897 0.09474 0.09127 -0.0146 1.0000 0.0266
-7.250 -0.2814 0.09203 0.08861 -0.0158 1.0000 0.0269
-7.000 -0.2727 0.08941 0.08603 -0.0172 1.0000 0.0273
-6.750 -0.2639 0.08687 0.08353 -0.0186 1.0000 0.0278
-6.500 -0.2553 0.08443 0.08114 -0.0200 1.0000 0.0284
-6.250 -0.2472 0.08215 0.07892 -0.0215 1.0000 0.0289
-6.000 -0.2430 0.08042 0.07724 -0.0223 1.0000 0.0293
-5.750 -0.2380 0.07919 0.07606 -0.0242 0.9992 0.0296
-5.500 -0.1850 0.07467 0.07144 -0.0379 0.9931 0.0299
-5.250 -0.1616 0.07003 0.06682 -0.0398 0.9872 0.0302
-5.000 -0.1265 0.06597 0.06273 -0.0458 0.9806 0.0308
-4.750 -0.0856 0.06212 0.05883 -0.0531 0.9733 0.0318
-4.500 -0.0392 0.05844 0.05507 -0.0616 0.9648 0.0334
-4.250 0.0320 0.05514 0.05150 -0.0759 0.9566 0.0342
-4.000 0.0557 0.05102 0.04743 -0.0776 0.9448 0.0346
-3.750 0.0896 0.04777 0.04413 -0.0814 0.9309 0.0354
-3.500 0.1266 0.04495 0.04120 -0.0856 0.9146 0.0366
-3.250 0.1635 0.04257 0.03863 -0.0891 0.8959 0.0383
-3.000 0.2054 0.04051 0.03627 -0.0930 0.8763 0.0396
-2.750 0.2255 0.03812 0.03383 -0.0931 0.8563 0.0404
-2.500 0.2518 0.03620 0.03178 -0.0939 0.8372 0.0415
-2.250 0.2815 0.03444 0.02984 -0.0950 0.8187 0.0432
-2.000 0.3256 0.03365 0.02857 -0.0972 0.8019 0.0456
-1.750 0.3469 0.03098 0.02591 -0.0976 0.7861 0.0464
-1.500 0.3734 0.02932 0.02414 -0.0982 0.7712 0.0480
-1.250 0.4135 0.02952 0.02380 -0.0988 0.7571 0.0526
-1.000 0.4372 0.02658 0.02090 -0.0997 0.7433 0.0539
-0.750 0.4644 0.02526 0.01949 -0.1002 0.7291 0.0574
-0.500 0.4972 0.02422 0.01816 -0.1007 0.7158 0.0628
-0.250 0.5244 0.02299 0.01684 -0.1011 0.7029 0.0664
0.000 0.5556 0.02217 0.01572 -0.1013 0.6906 0.0736
0.250 0.5835 0.02126 0.01472 -0.1016 0.6774 0.0802
0.500 0.6126 0.02029 0.01361 -0.1019 0.6644 0.0884
0.750 0.6415 0.01955 0.01270 -0.1020 0.6518 0.1003
1.000 0.6698 0.01885 0.01185 -0.1021 0.6389 0.1153
1.250 0.6976 0.01815 0.01101 -0.1023 0.6254 0.1414
1.500 0.7244 0.01766 0.01048 -0.1023 0.6106 0.1825
2.500 0.8393 0.01589 0.00801 -0.1006 0.5409 0.1851
3.000 0.8976 0.01529 0.00688 -0.0983 0.4982 0.0823
3.250 0.9242 0.01491 0.00639 -0.0977 0.4735 0.0765
3.500 0.9507 0.01480 0.00619 -0.0972 0.4455 0.0767
3.750 0.9768 0.01479 0.00603 -0.0966 0.4199 0.0738
4.000 1.0028 0.01490 0.00602 -0.0961 0.3978 0.0725
4.250 1.0286 0.01503 0.00604 -0.0957 0.3798 0.0727
4.500 1.0546 0.01524 0.00614 -0.0954 0.3649 0.0745
4.750 1.0805 0.01552 0.00636 -0.0950 0.3530 0.0812
5.000 1.1061 0.01588 0.00660 -0.0945 0.3432 0.0917
5.250 1.1286 0.01491 0.00691 -0.0934 0.3343 1.0000
5.500 1.1541 0.01539 0.00721 -0.0929 0.3264 1.0000
5.750 1.1801 0.01574 0.00755 -0.0925 0.3184 1.0000
6.000 1.2052 0.01628 0.00793 -0.0921 0.3113 1.0000
6.250 1.2310 0.01657 0.00829 -0.0917 0.3032 1.0000
6.750 1.2812 0.01734 0.00908 -0.0909 0.2877 1.0000
7.000 1.3060 0.01775 0.00947 -0.0904 0.2810 1.0000
7.250 1.3309 0.01813 0.00991 -0.0899 0.2743 1.0000
7.500 1.3553 0.01844 0.01028 -0.0894 0.2657 1.0000
7.750 1.3794 0.01877 0.01068 -0.0889 0.2567 1.0000
8.000 1.4028 0.01914 0.01105 -0.0882 0.2474 1.0000
8.250 1.4268 0.01939 0.01145 -0.0876 0.2361 1.0000
8.500 1.4497 0.01972 0.01186 -0.0869 0.2218 1.0000
8.750 1.4715 0.02014 0.01229 -0.0861 0.2032 1.0000
9.000 1.4923 0.02071 0.01284 -0.0852 0.1782 1.0000
9.250 1.5105 0.02158 0.01359 -0.0839 0.1532 1.0000
9.500 1.5278 0.02256 0.01450 -0.0826 0.1365 1.0000
9.750 1.5440 0.02359 0.01549 -0.0811 0.1264 1.0000
10.000 1.5584 0.02473 0.01657 -0.0794 0.1185 1.0000
10.250 1.5738 0.02573 0.01764 -0.0779 0.1119 1.0000
10.500 1.5840 0.02708 0.01895 -0.0758 0.1061 1.0000
10.750 1.5962 0.02823 0.02020 -0.0738 0.1014 1.0000
11.000 1.6052 0.02951 0.02154 -0.0715 0.0972 1.0000
11.250 1.6069 0.03122 0.02319 -0.0683 0.0934 1.0000
11.500 1.6139 0.03257 0.02469 -0.0659 0.0902 1.0000
11.750 1.6195 0.03407 0.02632 -0.0636 0.0868 1.0000
12.000 1.6228 0.03590 0.02819 -0.0614 0.0833 1.0000
12.250 1.6274 0.03811 0.03038 -0.0594 0.0796 1.0000
12.500 1.6305 0.03989 0.03239 -0.0577 0.0766 1.0000
12.750 1.6329 0.04192 0.03456 -0.0563 0.0731 1.0000
13.000 1.6353 0.04424 0.03685 -0.0548 0.0696 1.0000
13.250 1.6354 0.04678 0.03956 -0.0535 0.0664 1.0000
13.500 1.6336 0.04940 0.04241 -0.0529 0.0633 1.0000
13.750 1.6325 0.05209 0.04519 -0.0524 0.0604 1.0000
14.000 1.6317 0.05496 0.04802 -0.0515 0.0574 1.0000
14.250 1.6257 0.05848 0.05185 -0.0519 0.0551 1.0000
14.500 1.6213 0.06197 0.05550 -0.0523 0.0526 1.0000
14.750 1.6174 0.06545 0.05907 -0.0530 0.0506 1.0000
15.000 1.6135 0.06886 0.06246 -0.0529 0.0485 1.0000
15.250 1.6046 0.07333 0.06720 -0.0539 0.0469 1.0000
15.500 1.5973 0.07763 0.07169 -0.0549 0.0452 1.0000
15.750 1.5912 0.08182 0.07599 -0.0560 0.0437 1.0000
16.000 1.5858 0.08596 0.08021 -0.0572 0.0425 1.0000
16.250 1.5822 0.08960 0.08383 -0.0575 0.0411 1.0000
16.500 1.5718 0.09483 0.08928 -0.0592 0.0401 1.0000
16.750 1.5609 0.10031 0.09498 -0.0612 0.0392 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 79 (PFALZ 11) AIRFOIL (goe79-il)