GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Reynolds number: 200,000 Max Cl/Cd: 70.01 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe318-il-200000-n5.txt Download as CSV file: xf-goe318-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 318 (HANSA-BRANDENBURG VI.5) 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4529 0.11711 0.11396 0.0123 0.8907 0.0263
-9.250 -0.4521 0.11385 0.11059 0.0108 0.8537 0.0263
-9.000 -0.4489 0.11022 0.10690 0.0092 0.8324 0.0264
-8.750 -0.4450 0.10647 0.10309 0.0074 0.8163 0.0264
-8.500 -0.4408 0.10264 0.09921 0.0055 0.8028 0.0264
-8.250 -0.4359 0.09875 0.09526 0.0036 0.7910 0.0264
-7.750 -0.4256 0.09108 0.08752 -0.0001 0.7710 0.0262
-7.250 -0.4078 0.08462 0.08099 -0.0023 0.7537 0.0285
-7.000 -0.3933 0.07703 0.07328 -0.0141 0.7468 0.0262
-6.750 -0.3804 0.07283 0.06902 -0.0170 0.7396 0.0260
-6.500 -0.3632 0.06757 0.06363 -0.0223 0.7330 0.0260
-6.250 -0.3487 0.06577 0.06181 -0.0225 0.7256 0.0285
-6.000 -0.3288 0.06290 0.05884 -0.0252 0.7193 0.0312
-5.750 -0.3057 0.05802 0.05380 -0.0300 0.7129 0.0320
-5.500 -0.2830 0.05313 0.04870 -0.0338 0.7075 0.0311
-5.250 -0.2577 0.04836 0.04370 -0.0372 0.7017 0.0312
-5.000 -0.2290 0.04344 0.03844 -0.0404 0.6961 0.0330
-4.750 -0.2025 0.03895 0.03359 -0.0423 0.6914 0.0332
-4.500 -0.1747 0.03462 0.02884 -0.0438 0.6859 0.0336
-4.250 -0.1472 0.03040 0.02407 -0.0449 0.6807 0.0354
-4.000 -0.1206 0.02772 0.02100 -0.0453 0.6759 0.0356
-3.750 -0.0932 0.02551 0.01847 -0.0457 0.6703 0.0359
-3.500 -0.0657 0.02381 0.01650 -0.0459 0.6648 0.0364
-3.250 -0.0386 0.02287 0.01540 -0.0461 0.6601 0.0377
-3.000 -0.0102 0.02165 0.01395 -0.0463 0.6544 0.0387
-2.750 0.0185 0.02021 0.01219 -0.0463 0.6490 0.0388
-2.500 0.0470 0.01908 0.01075 -0.0462 0.6437 0.0391
-2.250 0.0758 0.01811 0.00958 -0.0463 0.6365 0.0396
-2.000 0.1041 0.01732 0.00855 -0.0461 0.6301 0.0401
-1.750 0.1328 0.01662 0.00771 -0.0461 0.6224 0.0406
-1.500 0.1611 0.01611 0.00707 -0.0460 0.6155 0.0420
-1.250 0.1896 0.01564 0.00650 -0.0460 0.6083 0.0432
-1.000 0.2179 0.01514 0.00591 -0.0459 0.6013 0.0437
-0.750 0.2462 0.01469 0.00540 -0.0459 0.5941 0.0441
-0.500 0.2745 0.01430 0.00496 -0.0458 0.5859 0.0446
-0.250 0.3028 0.01398 0.00460 -0.0458 0.5772 0.0452
0.000 0.3309 0.01355 0.00415 -0.0458 0.5690 0.0464
0.250 0.3594 0.01326 0.00387 -0.0458 0.5610 0.0481
0.500 0.3877 0.01308 0.00364 -0.0459 0.5536 0.0501
0.750 0.4164 0.01294 0.00349 -0.0460 0.5450 0.0540
1.000 0.4448 0.01284 0.00333 -0.0460 0.5372 0.0582
1.250 0.4735 0.01269 0.00323 -0.0461 0.5282 0.0657
1.500 0.5018 0.01243 0.00320 -0.0462 0.5195 0.1443
2.000 0.5560 0.01045 0.00317 -0.0458 0.4998 1.0000
2.250 0.5842 0.01055 0.00317 -0.0458 0.4891 1.0000
2.500 0.6123 0.01068 0.00318 -0.0458 0.4777 1.0000
2.750 0.6403 0.01081 0.00323 -0.0459 0.4651 1.0000
3.000 0.6684 0.01096 0.00331 -0.0459 0.4521 1.0000
3.250 0.6963 0.01113 0.00339 -0.0459 0.4385 1.0000
3.500 0.7240 0.01133 0.00351 -0.0460 0.4243 1.0000
3.750 0.7517 0.01154 0.00365 -0.0460 0.4094 1.0000
4.000 0.7792 0.01178 0.00381 -0.0461 0.3938 1.0000
4.250 0.8066 0.01204 0.00400 -0.0461 0.3778 1.0000
4.500 0.8339 0.01233 0.00422 -0.0462 0.3620 1.0000
4.750 0.8611 0.01262 0.00446 -0.0463 0.3473 1.0000
5.000 0.8882 0.01293 0.00472 -0.0463 0.3342 1.0000
5.250 0.9151 0.01325 0.00502 -0.0463 0.3228 1.0000
5.500 0.9419 0.01359 0.00533 -0.0464 0.3133 1.0000
5.750 0.9686 0.01393 0.00566 -0.0464 0.3049 1.0000
6.000 0.9952 0.01428 0.00602 -0.0464 0.2985 1.0000
6.250 1.0218 0.01462 0.00639 -0.0464 0.2926 1.0000
6.500 1.0480 0.01500 0.00679 -0.0464 0.2879 1.0000
6.750 1.0743 0.01537 0.00721 -0.0463 0.2841 1.0000
7.000 1.1006 0.01572 0.00764 -0.0463 0.2797 1.0000
7.250 1.1262 0.01614 0.00808 -0.0462 0.2740 1.0000
7.500 1.1518 0.01654 0.00853 -0.0461 0.2679 1.0000
7.750 1.1770 0.01695 0.00901 -0.0460 0.2592 1.0000
8.000 1.2018 0.01737 0.00948 -0.0459 0.2483 1.0000
8.250 1.2260 0.01786 0.00998 -0.0458 0.2375 1.0000
8.500 1.2500 0.01833 0.01051 -0.0456 0.2265 1.0000
8.750 1.2739 0.01880 0.01107 -0.0454 0.2125 1.0000
9.000 1.2969 0.01936 0.01166 -0.0452 0.1950 1.0000
9.500 1.3196 0.02315 0.01466 -0.0436 0.0612 1.0000
9.750 1.3307 0.02487 0.01631 -0.0425 0.0402 1.0000
10.000 1.3419 0.02640 0.01789 -0.0415 0.0298 1.0000
10.250 1.3516 0.02793 0.01949 -0.0404 0.0250 1.0000
10.500 1.3561 0.02963 0.02127 -0.0389 0.0223 1.0000
10.750 1.3586 0.03172 0.02347 -0.0381 0.0206 1.0000
11.000 1.3623 0.03396 0.02586 -0.0379 0.0193 1.0000
11.250 1.3641 0.03652 0.02856 -0.0378 0.0183 1.0000
11.500 1.3640 0.03940 0.03157 -0.0379 0.0176 1.0000
11.750 1.3613 0.04264 0.03494 -0.0382 0.0169 1.0000
12.000 1.3559 0.04628 0.03870 -0.0386 0.0164 1.0000
12.250 1.3476 0.05032 0.04287 -0.0391 0.0160 1.0000
12.500 1.3414 0.05416 0.04685 -0.0396 0.0156 1.0000
12.750 1.3367 0.05787 0.05070 -0.0402 0.0153 1.0000
13.000 1.3312 0.06172 0.05469 -0.0408 0.0149 1.0000
13.250 1.3253 0.06569 0.05878 -0.0414 0.0145 1.0000
13.500 1.3194 0.06973 0.06294 -0.0422 0.0141 1.0000
13.750 1.3137 0.07390 0.06723 -0.0431 0.0137 1.0000
14.000 1.3087 0.07810 0.07153 -0.0441 0.0134 1.0000
14.250 1.3038 0.08231 0.07584 -0.0451 0.0131 1.0000
14.500 1.2992 0.08649 0.08011 -0.0462 0.0128 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il)