GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Reynolds number: 500,000 Max Cl/Cd: 98.96 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe188-il-500000-n5.txt Download as CSV file: xf-goe188-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 188 (SCHTTE-LANZ 3U10) 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3304 0.09796 0.09584 -0.0220 1.0000 0.0053
-8.000 -0.3259 0.09482 0.09273 -0.0238 1.0000 0.0053
-7.750 -0.3210 0.09161 0.08955 -0.0259 0.9964 0.0053
-7.500 -0.3033 0.08707 0.08499 -0.0326 0.9446 0.0054
-7.250 -0.2863 0.08268 0.08046 -0.0390 0.8897 0.0054
-7.000 -0.2736 0.07894 0.07657 -0.0432 0.8585 0.0054
-6.750 -0.2587 0.07507 0.07259 -0.0475 0.8395 0.0054
-6.500 -0.2508 0.07091 0.06836 -0.0489 0.8255 0.0055
-6.000 -0.2207 0.06362 0.06091 -0.0545 0.8025 0.0057
-5.750 -0.2017 0.05990 0.05710 -0.0580 0.7923 0.0058
-5.500 -0.1810 0.05623 0.05331 -0.0612 0.7808 0.0059
-5.250 -0.1588 0.05262 0.04955 -0.0642 0.7679 0.0060
-5.000 -0.1353 0.04911 0.04588 -0.0668 0.7546 0.0062
-4.750 -0.1106 0.04569 0.04230 -0.0691 0.7423 0.0064
-4.500 -0.0848 0.04239 0.03883 -0.0710 0.7316 0.0066
-4.250 -0.0583 0.03926 0.03551 -0.0725 0.7212 0.0069
-4.000 -0.0308 0.03631 0.03234 -0.0735 0.7109 0.0072
-3.750 -0.0009 0.03366 0.02945 -0.0740 0.7014 0.0078
-3.500 0.0304 0.03161 0.02713 -0.0740 0.6932 0.0082
-3.250 0.0586 0.02937 0.02464 -0.0741 0.6850 0.0083
-2.250 0.1698 0.01959 0.01375 -0.0745 0.6554 0.0090
-2.000 0.1967 0.01854 0.01258 -0.0750 0.6479 0.0106
-1.750 0.2264 0.01890 0.01278 -0.0745 0.6405 0.0134
-1.250 0.2855 0.01428 0.00750 -0.0739 0.6264 0.0078
-1.000 0.3143 0.01315 0.00618 -0.0737 0.6183 0.0075
-0.500 0.3711 0.01150 0.00426 -0.0733 0.6023 0.0076
-0.250 0.3993 0.01105 0.00369 -0.0732 0.5941 0.0082
0.000 0.4271 0.01051 0.00313 -0.0733 0.5844 0.0101
0.250 0.4553 0.01012 0.00268 -0.0733 0.5737 0.0106
0.500 0.4835 0.00985 0.00232 -0.0734 0.5612 0.0117
0.750 0.5116 0.00976 0.00216 -0.0734 0.5472 0.0136
1.000 0.5398 0.00958 0.00182 -0.0735 0.5314 0.0168
1.250 0.5677 0.00958 0.00169 -0.0735 0.5121 0.0230
1.500 0.5874 0.00765 0.00184 -0.0727 0.4923 0.8467
2.000 0.6434 0.00782 0.00184 -0.0727 0.4417 1.0000
2.250 0.6704 0.00803 0.00192 -0.0726 0.4240 1.0000
2.500 0.6977 0.00823 0.00200 -0.0727 0.4099 1.0000
2.750 0.7249 0.00842 0.00211 -0.0727 0.3967 1.0000
3.000 0.7521 0.00860 0.00221 -0.0727 0.3851 1.0000
3.250 0.7793 0.00878 0.00233 -0.0728 0.3746 1.0000
3.500 0.8065 0.00897 0.00246 -0.0728 0.3650 1.0000
3.750 0.8339 0.00913 0.00260 -0.0729 0.3572 1.0000
4.000 0.8610 0.00931 0.00274 -0.0729 0.3502 1.0000
4.250 0.8884 0.00946 0.00290 -0.0730 0.3442 1.0000
4.500 0.9155 0.00964 0.00307 -0.0730 0.3377 1.0000
4.750 0.9425 0.00981 0.00324 -0.0731 0.3316 1.0000
5.000 0.9693 0.01001 0.00344 -0.0731 0.3230 1.0000
5.250 0.9961 0.01021 0.00364 -0.0731 0.3135 1.0000
5.500 1.0225 0.01044 0.00385 -0.0731 0.3033 1.0000
5.750 1.0491 0.01065 0.00409 -0.0731 0.2945 1.0000
6.000 1.0754 0.01087 0.00432 -0.0730 0.2841 1.0000
6.250 1.1014 0.01113 0.00457 -0.0729 0.2718 1.0000
6.500 1.1271 0.01141 0.00486 -0.0728 0.2570 1.0000
6.750 1.1526 0.01171 0.00515 -0.0727 0.2424 1.0000
7.000 1.1774 0.01208 0.00549 -0.0725 0.2232 1.0000
7.250 1.1980 0.01291 0.00605 -0.0717 0.1766 1.0000
7.500 1.2180 0.01379 0.00673 -0.0709 0.1368 1.0000
7.750 1.2323 0.01528 0.00778 -0.0694 0.0665 1.0000
8.000 1.2522 0.01611 0.00852 -0.0685 0.0461 1.0000
8.250 1.2673 0.01740 0.00958 -0.0669 0.0105 1.0000
8.500 1.2862 0.01825 0.01051 -0.0658 0.0061 1.0000
8.750 1.3047 0.01909 0.01145 -0.0646 0.0048 1.0000
9.000 1.3238 0.01980 0.01228 -0.0635 0.0039 1.0000
9.250 1.3397 0.02076 0.01337 -0.0620 0.0033 1.0000
9.500 1.3562 0.02160 0.01434 -0.0606 0.0030 1.0000
9.750 1.3703 0.02257 0.01543 -0.0589 0.0027 1.0000
10.000 1.3816 0.02364 0.01663 -0.0568 0.0025 1.0000
10.250 1.3879 0.02479 0.01788 -0.0539 0.0023 1.0000
10.500 1.3910 0.02620 0.01942 -0.0509 0.0022 1.0000
10.750 1.3897 0.02807 0.02142 -0.0479 0.0021 1.0000
11.000 1.3903 0.03002 0.02351 -0.0457 0.0020 1.0000
11.250 1.3939 0.03190 0.02553 -0.0443 0.0019 1.0000
11.500 1.3962 0.03408 0.02785 -0.0431 0.0018 1.0000
11.750 1.3979 0.03644 0.03034 -0.0422 0.0016 1.0000
12.000 1.3986 0.03903 0.03307 -0.0416 0.0015 1.0000
12.250 1.3970 0.04197 0.03614 -0.0411 0.0015 1.0000
12.500 1.3942 0.04517 0.03947 -0.0409 0.0014 1.0000
12.750 1.3901 0.04862 0.04305 -0.0408 0.0014 1.0000
13.000 1.3850 0.05230 0.04686 -0.0409 0.0013 1.0000
13.250 1.3787 0.05622 0.05094 -0.0412 0.0013 1.0000
13.500 1.3709 0.06040 0.05525 -0.0417 0.0013 1.0000
13.750 1.3620 0.06483 0.05981 -0.0423 0.0012 1.0000
14.000 1.3513 0.06962 0.06473 -0.0431 0.0012 1.0000
14.250 1.3401 0.07464 0.06987 -0.0440 0.0012 1.0000
14.500 1.3329 0.07936 0.07475 -0.0452 0.0012 1.0000
14.750 1.3248 0.08430 0.07985 -0.0465 0.0011 1.0000
15.000 1.3165 0.08941 0.08511 -0.0480 0.0011 1.0000
15.250 1.3076 0.09471 0.09056 -0.0497 0.0011 1.0000
15.500 1.2984 0.10023 0.09624 -0.0515 0.0011 1.0000
15.750 1.2885 0.10591 0.10207 -0.0536 0.0011 1.0000
16.000 1.2784 0.11175 0.10807 -0.0558 0.0011 1.0000
16.250 1.2679 0.11787 0.11434 -0.0583 0.0011 1.0000
16.500 1.2576 0.12405 0.12066 -0.0610 0.0011 1.0000
16.750 1.2468 0.13048 0.12724 -0.0639 0.0011 1.0000
17.000 1.2360 0.13708 0.13399 -0.0671 0.0011 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il)