GOE 326 (PFALZ 55) AIRFOIL (goe326-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 326 (PFALZ 55) AIRFOIL (goe326-il) Reynolds number: 200,000 Max Cl/Cd: 77.16 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe326-il-200000-n5.txt Download as CSV file: xf-goe326-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 326 (PFALZ 55) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3219 0.09324 0.08995 -0.0279 1.0000 0.0242
-7.750 -0.3213 0.09030 0.08708 -0.0287 1.0000 0.0242
-7.500 -0.3170 0.08719 0.08401 -0.0273 1.0000 0.0235
-7.250 -0.3134 0.08409 0.08095 -0.0283 0.9974 0.0224
-7.000 -0.2919 0.07901 0.07585 -0.0355 0.9836 0.0216
-6.750 -0.2686 0.07389 0.07070 -0.0431 0.9689 0.0214
-6.500 -0.2428 0.06888 0.06563 -0.0507 0.9552 0.0219
-6.250 -0.2106 0.06261 0.05924 -0.0612 0.9416 0.0237
-6.000 -0.1786 0.05606 0.05252 -0.0702 0.9288 0.0241
-5.750 -0.1499 0.05030 0.04657 -0.0764 0.9169 0.0250
-5.500 -0.1300 0.04974 0.04599 -0.0762 0.9058 0.0266
-5.250 -0.1043 0.04681 0.04292 -0.0789 0.8934 0.0289
-5.000 -0.0760 0.04228 0.03814 -0.0826 0.8822 0.0297
-4.750 -0.0457 0.03741 0.03291 -0.0858 0.8723 0.0310
-4.500 -0.0156 0.03214 0.02710 -0.0883 0.8630 0.0334
-4.250 0.0085 0.03014 0.02494 -0.0888 0.8524 0.0342
-4.000 0.0339 0.02835 0.02296 -0.0891 0.8425 0.0352
-3.750 0.0598 0.02700 0.02141 -0.0893 0.8328 0.0373
-3.500 0.0873 0.02467 0.01872 -0.0896 0.8226 0.0383
-3.250 0.1150 0.02255 0.01621 -0.0897 0.8127 0.0387
-3.000 0.1426 0.02084 0.01413 -0.0895 0.8030 0.0393
-2.750 0.1703 0.01965 0.01260 -0.0893 0.7925 0.0410
-2.500 0.1979 0.01848 0.01110 -0.0891 0.7820 0.0416
-2.250 0.2254 0.01743 0.00976 -0.0888 0.7716 0.0418
-2.000 0.2529 0.01660 0.00865 -0.0885 0.7608 0.0422
-1.750 0.2804 0.01593 0.00776 -0.0882 0.7494 0.0427
-1.500 0.3078 0.01540 0.00704 -0.0879 0.7383 0.0432
-1.250 0.3350 0.01470 0.00619 -0.0876 0.7273 0.0438
-1.000 0.3619 0.01406 0.00549 -0.0873 0.7160 0.0456
-0.750 0.3891 0.01373 0.00511 -0.0871 0.7039 0.0475
-0.500 0.4163 0.01337 0.00470 -0.0868 0.6915 0.0484
-0.250 0.4434 0.01304 0.00432 -0.0865 0.6783 0.0492
0.000 0.4704 0.01277 0.00400 -0.0863 0.6638 0.0504
0.250 0.4975 0.01254 0.00373 -0.0860 0.6480 0.0519
0.500 0.5245 0.01237 0.00350 -0.0857 0.6301 0.0539
0.750 0.5514 0.01227 0.00331 -0.0854 0.6111 0.0559
1.000 0.5782 0.01214 0.00310 -0.0851 0.5910 0.0603
1.250 0.6048 0.01213 0.00299 -0.0848 0.5723 0.0676
1.500 0.6314 0.01212 0.00292 -0.0845 0.5559 0.0834
1.750 0.6573 0.01019 0.00302 -0.0843 0.5417 1.0000
2.000 0.6839 0.01039 0.00305 -0.0840 0.5286 1.0000
2.250 0.7103 0.01061 0.00312 -0.0837 0.5161 1.0000
2.500 0.7367 0.01083 0.00321 -0.0833 0.5032 1.0000
2.750 0.7630 0.01107 0.00334 -0.0830 0.4909 1.0000
3.000 0.7895 0.01128 0.00347 -0.0828 0.4786 1.0000
3.250 0.8160 0.01148 0.00362 -0.0825 0.4671 1.0000
3.500 0.8424 0.01170 0.00379 -0.0823 0.4562 1.0000
3.750 0.8686 0.01193 0.00396 -0.0820 0.4445 1.0000
4.000 0.8947 0.01215 0.00414 -0.0817 0.4317 1.0000
4.250 0.9209 0.01237 0.00435 -0.0815 0.4192 1.0000
4.500 0.9470 0.01259 0.00456 -0.0812 0.4083 1.0000
4.750 0.9729 0.01284 0.00479 -0.0809 0.3976 1.0000
5.250 1.0243 0.01335 0.00531 -0.0803 0.3760 1.0000
5.500 1.0496 0.01363 0.00559 -0.0799 0.3635 1.0000
5.750 1.0746 0.01393 0.00590 -0.0795 0.3514 1.0000
6.000 1.0995 0.01425 0.00622 -0.0791 0.3395 1.0000
6.500 1.1481 0.01494 0.00693 -0.0781 0.3130 1.0000
6.750 1.1711 0.01538 0.00733 -0.0775 0.2880 1.0000
7.000 1.1928 0.01593 0.00776 -0.0768 0.2575 1.0000
7.250 1.2141 0.01653 0.00825 -0.0760 0.2265 1.0000
7.500 1.2330 0.01737 0.00888 -0.0749 0.1814 1.0000
7.750 1.2487 0.01855 0.00974 -0.0736 0.1345 1.0000
8.000 1.2662 0.01953 0.01062 -0.0723 0.1149 1.0000
8.250 1.2852 0.02031 0.01140 -0.0713 0.1017 1.0000
8.500 1.3036 0.02111 0.01218 -0.0701 0.0851 1.0000
9.000 1.3234 0.02407 0.01468 -0.0659 0.0211 1.0000
9.250 1.3371 0.02510 0.01583 -0.0641 0.0186 1.0000
9.500 1.3492 0.02616 0.01705 -0.0621 0.0171 1.0000
9.750 1.3567 0.02737 0.01839 -0.0595 0.0158 1.0000
10.000 1.3619 0.02883 0.02000 -0.0568 0.0145 1.0000
10.250 1.3656 0.03046 0.02180 -0.0544 0.0137 1.0000
10.500 1.3720 0.03196 0.02346 -0.0524 0.0133 1.0000
10.750 1.3767 0.03367 0.02534 -0.0506 0.0129 1.0000
11.000 1.3795 0.03565 0.02748 -0.0490 0.0126 1.0000
11.250 1.3808 0.03788 0.02987 -0.0476 0.0122 1.0000
11.500 1.3807 0.04036 0.03253 -0.0465 0.0119 1.0000
11.750 1.3797 0.04308 0.03540 -0.0457 0.0115 1.0000
12.000 1.3774 0.04606 0.03852 -0.0451 0.0111 1.0000
12.250 1.3740 0.04930 0.04188 -0.0448 0.0108 1.0000
12.500 1.3690 0.05282 0.04552 -0.0446 0.0104 1.0000
12.750 1.3625 0.05663 0.04944 -0.0447 0.0102 1.0000
13.000 1.3546 0.06071 0.05363 -0.0450 0.0100 1.0000
13.250 1.3463 0.06488 0.05789 -0.0452 0.0098 1.0000
13.500 1.3394 0.06887 0.06195 -0.0453 0.0096 1.0000
13.750 1.3374 0.07241 0.06563 -0.0456 0.0095 1.0000
14.000 1.3355 0.07602 0.06936 -0.0460 0.0094 1.0000
14.250 1.3336 0.07968 0.07315 -0.0465 0.0093 1.0000
14.500 1.3316 0.08338 0.07698 -0.0470 0.0091 1.0000
14.750 1.3294 0.08713 0.08086 -0.0475 0.0090 1.0000
15.000 1.3270 0.09100 0.08487 -0.0482 0.0089 1.0000
15.250 1.3243 0.09498 0.08901 -0.0490 0.0088 1.0000
15.500 1.3212 0.09909 0.09326 -0.0499 0.0087 1.0000
15.750 1.3174 0.10339 0.09772 -0.0511 0.0086 1.0000
16.000 1.3129 0.10793 0.10241 -0.0525 0.0085 1.0000
16.250 1.3077 0.11273 0.10736 -0.0543 0.0083 1.0000
16.500 1.3018 0.11776 0.11255 -0.0564 0.0082 1.0000
16.750 1.2955 0.12298 0.11792 -0.0587 0.0081 1.0000
17.000 1.2887 0.12845 0.12354 -0.0614 0.0080 1.0000
17.250 1.2817 0.13412 0.12936 -0.0643 0.0079 1.0000
17.500 1.2744 0.14001 0.13540 -0.0675 0.0078 1.0000
17.750 1.2673 0.14602 0.14155 -0.0710 0.0077 1.0000
18.000 1.2593 0.15243 0.14811 -0.0748 0.0076 1.0000
18.250 1.2510 0.15912 0.15494 -0.0789 0.0076 1.0000
18.500 1.2420 0.16627 0.16224 -0.0835 0.0075 1.0000
18.750 1.2318 0.17413 0.17026 -0.0886 0.0075 1.0000
19.000 1.2197 0.18304 0.17934 -0.0945 0.0076 1.0000
19.250 1.2031 0.19426 0.19074 -0.1019 0.0078 1.0000
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