GOE 326 (PFALZ 55) AIRFOIL (goe326-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 326 (PFALZ 55) AIRFOIL (goe326-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.94 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe326-il-1000000.txt Download as CSV file: xf-goe326-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3465 0.09212 0.09059 -0.0198 1.0000 0.0147
-8.000 -0.3456 0.08788 0.08638 -0.0237 1.0000 0.0155
-7.750 -0.3435 0.08424 0.08278 -0.0267 0.9989 0.0155
-7.500 -0.3208 0.07853 0.07704 -0.0356 0.9785 0.0156
-7.250 -0.3041 0.07129 0.06976 -0.0443 0.9496 0.0158
-7.000 -0.2900 0.06931 0.06769 -0.0448 0.9257 0.0161
-6.750 -0.2743 0.06694 0.06524 -0.0468 0.9079 0.0165
-6.500 -0.2562 0.06409 0.06232 -0.0499 0.8930 0.0170
-6.250 -0.2355 0.06055 0.05867 -0.0541 0.8789 0.0182
-6.000 -0.2012 0.05297 0.05091 -0.0645 0.8655 0.0196
-5.250 -0.1330 0.04059 0.03813 -0.0738 0.8266 0.0209
-5.000 -0.1084 0.03871 0.03614 -0.0750 0.8130 0.0219
-4.750 -0.0720 0.03329 0.03036 -0.0780 0.8012 0.0246
-4.500 -0.0481 0.02368 0.02009 -0.0804 0.7911 0.0250
-4.250 -0.0242 0.02484 0.02131 -0.0806 0.7784 0.0261
-4.000 0.0015 0.02439 0.02080 -0.0808 0.7673 0.0270
-3.250 0.0843 0.01631 0.01170 -0.0811 0.7423 0.0295
-3.000 0.1125 0.01505 0.01004 -0.0809 0.7345 0.0316
-2.750 0.1405 0.01408 0.00892 -0.0808 0.7270 0.0314
-2.250 0.1963 0.01219 0.00670 -0.0807 0.7116 0.0313
-2.000 0.2236 0.01042 0.00468 -0.0807 0.7037 0.0323
-1.750 0.2517 0.00989 0.00411 -0.0807 0.6949 0.0330
-1.500 0.2797 0.00954 0.00370 -0.0806 0.6856 0.0336
-1.250 0.3077 0.00921 0.00330 -0.0806 0.6748 0.0340
-1.000 0.3358 0.00890 0.00294 -0.0805 0.6620 0.0345
-0.750 0.3637 0.00864 0.00262 -0.0804 0.6467 0.0351
-0.500 0.3916 0.00844 0.00235 -0.0803 0.6259 0.0358
-0.250 0.4191 0.00837 0.00217 -0.0802 0.5965 0.0370
0.000 0.4465 0.00834 0.00200 -0.0801 0.5668 0.0381
0.500 0.5015 0.00840 0.00187 -0.0799 0.5253 0.0394
1.000 0.5573 0.00815 0.00150 -0.0798 0.5015 0.0441
1.250 0.5853 0.00816 0.00148 -0.0798 0.4910 0.0470
1.500 0.6132 0.00821 0.00149 -0.0798 0.4800 0.0499
1.750 0.6413 0.00817 0.00144 -0.0798 0.4699 0.0591
2.000 0.6693 0.00804 0.00148 -0.0799 0.4602 0.1427
2.250 0.6940 0.00630 0.00167 -0.0798 0.4500 1.0000
2.500 0.7218 0.00640 0.00171 -0.0797 0.4398 1.0000
2.750 0.7496 0.00652 0.00177 -0.0797 0.4293 1.0000
3.000 0.7772 0.00665 0.00184 -0.0797 0.4181 1.0000
3.250 0.8047 0.00679 0.00192 -0.0796 0.4063 1.0000
3.500 0.8322 0.00693 0.00200 -0.0795 0.3943 1.0000
3.750 0.8596 0.00708 0.00210 -0.0795 0.3814 1.0000
4.000 0.8869 0.00724 0.00221 -0.0794 0.3689 1.0000
4.250 0.9140 0.00742 0.00233 -0.0793 0.3564 1.0000
4.500 0.9411 0.00760 0.00246 -0.0793 0.3448 1.0000
4.750 0.9680 0.00781 0.00261 -0.0791 0.3300 1.0000
5.000 0.9945 0.00805 0.00277 -0.0790 0.3116 1.0000
5.250 1.0210 0.00829 0.00294 -0.0788 0.2955 1.0000
5.500 1.0472 0.00856 0.00314 -0.0787 0.2779 1.0000
5.750 1.0731 0.00885 0.00334 -0.0785 0.2585 1.0000
6.000 1.0987 0.00919 0.00357 -0.0782 0.2361 1.0000
6.250 1.1231 0.00966 0.00388 -0.0778 0.2047 1.0000
6.500 1.1434 0.01065 0.00447 -0.0770 0.1357 1.0000
6.750 1.1667 0.01124 0.00492 -0.0764 0.1124 1.0000
7.000 1.1916 0.01161 0.00526 -0.0761 0.1019 1.0000
7.250 1.2164 0.01197 0.00558 -0.0757 0.0912 1.0000
7.500 1.2389 0.01260 0.00603 -0.0751 0.0645 1.0000
7.750 1.2554 0.01393 0.00704 -0.0736 0.0181 1.0000
8.000 1.2783 0.01447 0.00762 -0.0729 0.0148 1.0000
8.250 1.3018 0.01490 0.00810 -0.0724 0.0140 1.0000
8.500 1.3245 0.01541 0.00867 -0.0717 0.0131 1.0000
8.750 1.3461 0.01601 0.00932 -0.0709 0.0122 1.0000
9.000 1.3653 0.01683 0.01022 -0.0697 0.0113 1.0000
9.250 1.3852 0.01753 0.01099 -0.0686 0.0107 1.0000
9.500 1.4061 0.01807 0.01159 -0.0678 0.0103 1.0000
9.750 1.4256 0.01871 0.01229 -0.0667 0.0098 1.0000
10.000 1.4439 0.01942 0.01306 -0.0655 0.0094 1.0000
10.250 1.4608 0.02020 0.01389 -0.0641 0.0090 1.0000
10.500 1.4754 0.02110 0.01485 -0.0624 0.0086 1.0000
10.750 1.4835 0.02231 0.01615 -0.0598 0.0083 1.0000
11.000 1.4776 0.02416 0.01815 -0.0553 0.0080 1.0000
11.250 1.4838 0.02539 0.01947 -0.0528 0.0079 1.0000
11.500 1.4928 0.02653 0.02068 -0.0510 0.0078 1.0000
11.750 1.5003 0.02785 0.02209 -0.0492 0.0076 1.0000
12.000 1.5068 0.02934 0.02366 -0.0477 0.0074 1.0000
12.250 1.5131 0.03096 0.02536 -0.0463 0.0072 1.0000
12.500 1.5184 0.03274 0.02723 -0.0452 0.0070 1.0000
12.750 1.5231 0.03470 0.02928 -0.0442 0.0068 1.0000
13.000 1.5258 0.03695 0.03162 -0.0434 0.0066 1.0000
13.250 1.5276 0.03941 0.03417 -0.0429 0.0065 1.0000
13.500 1.5278 0.04215 0.03700 -0.0425 0.0064 1.0000
13.750 1.5269 0.04508 0.04002 -0.0422 0.0062 1.0000
14.000 1.5242 0.04831 0.04335 -0.0422 0.0061 1.0000
14.250 1.5196 0.05186 0.04698 -0.0423 0.0061 1.0000
14.500 1.5130 0.05577 0.05099 -0.0426 0.0060 1.0000
14.750 1.5044 0.06006 0.05538 -0.0431 0.0059 1.0000
15.000 1.4937 0.06471 0.06013 -0.0438 0.0058 1.0000
15.250 1.4813 0.06963 0.06516 -0.0445 0.0057 1.0000
15.500 1.4675 0.07460 0.07023 -0.0448 0.0056 1.0000
15.750 1.4574 0.07923 0.07497 -0.0453 0.0056 1.0000
16.000 1.4528 0.08365 0.07952 -0.0468 0.0055 1.0000
16.250 1.4469 0.08821 0.08418 -0.0482 0.0055 1.0000
16.500 1.4405 0.09292 0.08900 -0.0498 0.0055 1.0000
16.750 1.4334 0.09778 0.09397 -0.0514 0.0054 1.0000
17.000 1.4260 0.10276 0.09906 -0.0531 0.0054 1.0000
17.250 1.4183 0.10789 0.10430 -0.0551 0.0054 1.0000
17.500 1.4102 0.11312 0.10965 -0.0571 0.0053 1.0000
17.750 1.4020 0.11848 0.11512 -0.0594 0.0053 1.0000
18.000 1.3939 0.12397 0.12071 -0.0618 0.0053 1.0000
18.250 1.3851 0.12960 0.12646 -0.0644 0.0052 1.0000
18.500 1.3763 0.13536 0.13233 -0.0672 0.0052 1.0000
18.750 1.3671 0.14128 0.13837 -0.0701 0.0052 1.0000
19.000 1.3580 0.14738 0.14458 -0.0734 0.0052 1.0000
19.250 1.3487 0.15368 0.15099 -0.0770 0.0051 1.0000
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