GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Reynolds number: 200,000 Max Cl/Cd: 69.03 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe318-il-200000.txt Download as CSV file: xf-goe318-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4396 0.10791 0.10493 0.0092 1.0000 0.0375
-8.500 -0.4383 0.10498 0.10208 0.0021 1.0000 0.0381
-8.250 -0.4328 0.10131 0.09849 -0.0053 1.0000 0.0383
-8.000 -0.4225 0.09517 0.09238 -0.0100 0.9450 0.0387
-7.750 -0.4129 0.09177 0.08888 -0.0037 0.9046 0.0397
-7.500 -0.4072 0.08914 0.08615 -0.0027 0.8789 0.0406
-7.250 -0.3998 0.08608 0.08301 -0.0043 0.8608 0.0417
-7.000 -0.3904 0.08266 0.07952 -0.0073 0.8468 0.0429
-6.750 -0.3787 0.07897 0.07573 -0.0113 0.8350 0.0445
-6.500 -0.3504 0.07417 0.07071 -0.0251 0.8235 0.0477
-6.250 -0.3243 0.07006 0.06627 -0.0329 0.8144 0.0483
-6.000 -0.3212 0.06418 0.06050 -0.0312 0.8065 0.0495
-5.750 -0.3078 0.06168 0.05799 -0.0302 0.7978 0.0509
-5.500 -0.2898 0.05889 0.05509 -0.0313 0.7904 0.0532
-5.250 -0.2655 0.05536 0.05141 -0.0347 0.7824 0.0566
-5.000 -0.2311 0.04999 0.04549 -0.0412 0.7763 0.0613
-4.750 -0.2136 0.04710 0.04266 -0.0412 0.7691 0.0627
-4.500 -0.1927 0.04495 0.04044 -0.0415 0.7622 0.0655
-4.250 -0.1591 0.04172 0.03662 -0.0445 0.7563 0.0748
-4.000 -0.1385 0.03905 0.03402 -0.0448 0.7493 0.0768
-3.750 -0.1149 0.03721 0.03205 -0.0449 0.7439 0.0809
-3.500 -0.0844 0.03463 0.02911 -0.0464 0.7369 0.0902
-3.250 -0.0605 0.03290 0.02733 -0.0465 0.7310 0.0945
-3.000 -0.0323 0.03105 0.02520 -0.0472 0.7249 0.1061
-2.750 -0.0035 0.02987 0.02369 -0.0476 0.7181 0.1195
-2.500 0.0210 0.02795 0.02179 -0.0476 0.7122 0.1246
-2.250 0.0490 0.02648 0.02016 -0.0481 0.7043 0.1384
-2.000 0.0755 0.02520 0.01868 -0.0480 0.6980 0.1536
-1.750 0.1177 0.02155 0.01393 -0.0471 0.6906 0.0859
-1.500 0.1481 0.01948 0.01138 -0.0463 0.6840 0.0723
-1.250 0.1770 0.01809 0.00982 -0.0462 0.6761 0.0699
-1.000 0.2054 0.01711 0.00864 -0.0458 0.6688 0.0686
-0.750 0.2340 0.01635 0.00777 -0.0456 0.6604 0.0684
-0.500 0.2619 0.01583 0.00712 -0.0451 0.6528 0.0706
-0.250 0.2903 0.01530 0.00656 -0.0450 0.6444 0.0718
0.000 0.3182 0.01483 0.00602 -0.0447 0.6379 0.0727
0.250 0.3466 0.01441 0.00562 -0.0446 0.6305 0.0741
0.500 0.3745 0.01395 0.00517 -0.0444 0.6234 0.0780
0.750 0.4029 0.01373 0.00496 -0.0444 0.6157 0.0841
1.000 0.4312 0.01349 0.00473 -0.0443 0.6080 0.0985
1.250 0.4580 0.01096 0.00456 -0.0439 0.6002 1.0000
1.500 0.4861 0.01102 0.00439 -0.0436 0.5921 1.0000
1.750 0.5144 0.01108 0.00436 -0.0435 0.5831 1.0000
2.000 0.5423 0.01115 0.00427 -0.0433 0.5753 1.0000
2.250 0.5707 0.01121 0.00429 -0.0434 0.5653 1.0000
2.500 0.5987 0.01127 0.00426 -0.0432 0.5564 1.0000
2.750 0.6267 0.01132 0.00425 -0.0432 0.5463 1.0000
3.000 0.6549 0.01138 0.00428 -0.0431 0.5350 1.0000
3.250 0.6829 0.01145 0.00429 -0.0431 0.5235 1.0000
3.500 0.7108 0.01152 0.00430 -0.0430 0.5112 1.0000
3.750 0.7386 0.01161 0.00434 -0.0429 0.4975 1.0000
4.000 0.7664 0.01172 0.00440 -0.0429 0.4820 1.0000
4.250 0.7940 0.01187 0.00450 -0.0428 0.4645 1.0000
4.500 0.8214 0.01208 0.00464 -0.0428 0.4458 1.0000
4.750 0.8484 0.01236 0.00480 -0.0427 0.4266 1.0000
5.000 0.8753 0.01269 0.00505 -0.0427 0.4071 1.0000
5.250 0.9022 0.01307 0.00536 -0.0426 0.3897 1.0000
5.500 0.9289 0.01347 0.00569 -0.0426 0.3757 1.0000
5.750 0.9555 0.01392 0.00604 -0.0426 0.3648 1.0000
6.000 0.9825 0.01431 0.00645 -0.0426 0.3552 1.0000
6.250 1.0091 0.01476 0.00689 -0.0426 0.3480 1.0000
6.500 1.0360 0.01517 0.00734 -0.0426 0.3414 1.0000
7.000 1.0893 0.01608 0.00832 -0.0425 0.3310 1.0000
7.250 1.1157 0.01648 0.00876 -0.0425 0.3249 1.0000
7.500 1.1417 0.01689 0.00922 -0.0424 0.3176 1.0000
7.750 1.1670 0.01725 0.00955 -0.0423 0.3075 1.0000
8.000 1.1920 0.01749 0.00990 -0.0422 0.2949 1.0000
8.250 1.2168 0.01781 0.01032 -0.0420 0.2833 1.0000
8.500 1.2412 0.01820 0.01077 -0.0419 0.2729 1.0000
8.750 1.2651 0.01862 0.01125 -0.0416 0.2616 1.0000
9.000 1.2884 0.01903 0.01174 -0.0414 0.2475 1.0000
9.250 1.3114 0.01939 0.01227 -0.0412 0.2262 1.0000
9.500 1.3225 0.02117 0.01346 -0.0406 0.1101 1.0000
9.750 1.3183 0.02489 0.01670 -0.0386 0.0540 1.0000
10.000 1.3247 0.02694 0.01885 -0.0373 0.0457 1.0000
10.250 1.3277 0.02899 0.02105 -0.0358 0.0416 1.0000
10.500 1.3284 0.03112 0.02329 -0.0346 0.0389 1.0000
10.750 1.3270 0.03386 0.02613 -0.0343 0.0371 1.0000
11.000 1.3210 0.03724 0.02959 -0.0342 0.0357 1.0000
11.250 1.3158 0.04061 0.03303 -0.0339 0.0347 1.0000
11.500 1.3177 0.04324 0.03578 -0.0336 0.0337 1.0000
11.750 1.3192 0.04592 0.03857 -0.0333 0.0325 1.0000
12.000 1.3204 0.04862 0.04135 -0.0329 0.0313 1.0000
12.250 1.3216 0.05133 0.04412 -0.0327 0.0302 1.0000
12.500 1.3222 0.05405 0.04689 -0.0323 0.0292 1.0000
12.750 1.3241 0.05647 0.04929 -0.0310 0.0282 1.0000
13.000 1.3321 0.05823 0.05107 -0.0287 0.0274 1.0000
13.250 1.3385 0.06047 0.05345 -0.0279 0.0270 1.0000
13.500 1.3453 0.06273 0.05585 -0.0270 0.0265 1.0000
13.750 1.3515 0.06513 0.05840 -0.0260 0.0261 1.0000
14.000 1.3556 0.06784 0.06128 -0.0254 0.0256 1.0000
14.250 1.3573 0.07086 0.06447 -0.0252 0.0251 1.0000
14.500 1.3574 0.07409 0.06785 -0.0252 0.0245 1.0000
14.750 1.3565 0.07742 0.07133 -0.0255 0.0240 1.0000
15.000 1.3552 0.08087 0.07491 -0.0258 0.0235 1.0000
15.250 1.3511 0.08482 0.07903 -0.0264 0.0233 1.0000
15.500 1.3451 0.08920 0.08360 -0.0272 0.0232 1.0000
15.750 1.3366 0.09409 0.08869 -0.0285 0.0232 1.0000
16.000 1.3242 0.09976 0.09460 -0.0306 0.0233 1.0000
16.250 1.3066 0.10653 0.10163 -0.0337 0.0234 1.0000
16.500 1.2859 0.11425 0.10961 -0.0378 0.0237 1.0000
16.750 1.2632 0.12285 0.11848 -0.0427 0.0240 1.0000
17.000 1.2395 0.13215 0.12802 -0.0484 0.0244 1.0000
17.250 1.2152 0.14222 0.13832 -0.0549 0.0248 1.0000
17.500 1.1898 0.15330 0.14959 -0.0623 0.0253 1.0000
17.750 1.1629 0.16561 0.16205 -0.0705 0.0259 1.0000
18.000 1.1369 0.17867 0.17522 -0.0791 0.0267 1.0000
18.250 1.1243 0.18784 0.18439 -0.0841 0.0275 1.0000
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Polar data table (+)
Polar graphs
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