GOE 55 AIRFOIL (goe55-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 55 AIRFOIL (goe55-il) Reynolds number: 200,000 Max Cl/Cd: 51.9 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe55-il-200000-n5.txt Download as CSV file: xf-goe55-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6284 0.10872 0.10508 0.0376 1.0000 0.0352
-8.500 -0.6315 0.10429 0.10069 0.0316 1.0000 0.0378
-8.250 -0.6313 0.09985 0.09628 0.0276 1.0000 0.0379
-7.250 -0.5982 0.08303 0.07948 0.0181 1.0000 0.0359
-7.000 -0.5862 0.07701 0.07342 0.0119 1.0000 0.0340
-6.750 -0.5695 0.06930 0.06561 0.0028 1.0000 0.0329
-6.500 -0.5501 0.06546 0.06172 -0.0009 1.0000 0.0341
-6.250 -0.5277 0.06014 0.05628 -0.0064 1.0000 0.0349
-6.000 -0.5029 0.05382 0.04976 -0.0122 1.0000 0.0347
-5.750 -0.4759 0.04756 0.04324 -0.0173 1.0000 0.0346
-5.500 -0.4474 0.04195 0.03732 -0.0213 1.0000 0.0355
-5.250 -0.4170 0.03564 0.03055 -0.0250 1.0000 0.0363
-5.000 -0.3869 0.03026 0.02464 -0.0274 1.0000 0.0366
-4.750 -0.3565 0.02575 0.01953 -0.0291 1.0000 0.0372
-4.500 -0.3262 0.02304 0.01620 -0.0299 1.0000 0.0383
-4.250 -0.2975 0.02087 0.01377 -0.0306 1.0000 0.0388
-4.000 -0.2688 0.01940 0.01211 -0.0309 1.0000 0.0393
-3.750 -0.2401 0.01824 0.01080 -0.0310 1.0000 0.0398
-3.500 -0.2114 0.01726 0.00969 -0.0311 1.0000 0.0405
-3.250 -0.1827 0.01637 0.00870 -0.0312 1.0000 0.0412
-3.000 -0.1540 0.01559 0.00784 -0.0311 1.0000 0.0421
-2.750 -0.1255 0.01497 0.00715 -0.0311 1.0000 0.0436
-2.500 -0.0968 0.01433 0.00647 -0.0310 1.0000 0.0450
-2.250 -0.0659 0.01413 0.00588 -0.0307 0.7804 0.0459
-2.000 -0.0441 0.01434 0.00539 -0.0287 0.6127 0.0466
-1.750 -0.0173 0.01422 0.00481 -0.0284 0.5030 0.0477
-1.500 0.0109 0.01403 0.00442 -0.0284 0.4555 0.0493
-1.250 0.0393 0.01386 0.00412 -0.0283 0.4290 0.0512
-1.000 0.0679 0.01372 0.00388 -0.0283 0.4113 0.0542
-0.750 0.0965 0.01358 0.00366 -0.0283 0.3987 0.0579
-0.500 0.1253 0.01343 0.00350 -0.0283 0.3891 0.0628
-0.250 0.1541 0.01333 0.00337 -0.0283 0.3815 0.0698
0.000 0.1828 0.01325 0.00333 -0.0282 0.3747 0.0832
0.250 0.2115 0.01323 0.00329 -0.0282 0.3689 0.1033
0.500 0.2402 0.01311 0.00325 -0.0282 0.3623 0.1261
0.750 0.2689 0.01291 0.00328 -0.0284 0.3546 0.2052
1.250 0.3165 0.01087 0.00320 -0.0261 0.3379 1.0000
1.500 0.3452 0.01099 0.00325 -0.0260 0.3299 1.0000
1.750 0.3737 0.01115 0.00331 -0.0259 0.3236 1.0000
2.000 0.4023 0.01131 0.00340 -0.0258 0.3173 1.0000
2.250 0.4307 0.01144 0.00347 -0.0257 0.3072 1.0000
2.500 0.4592 0.01155 0.00353 -0.0256 0.2949 1.0000
2.750 0.4877 0.01167 0.00360 -0.0255 0.2833 1.0000
3.000 0.5160 0.01181 0.00370 -0.0254 0.2731 1.0000
3.250 0.5445 0.01193 0.00381 -0.0253 0.2607 1.0000
3.500 0.5729 0.01206 0.00391 -0.0252 0.2448 1.0000
3.750 0.6012 0.01222 0.00405 -0.0251 0.2262 1.0000
4.000 0.6293 0.01245 0.00417 -0.0250 0.1977 1.0000
4.250 0.6571 0.01285 0.00437 -0.0250 0.1653 1.0000
4.500 0.6848 0.01331 0.00471 -0.0250 0.1419 1.0000
4.750 0.7125 0.01375 0.00507 -0.0250 0.1223 1.0000
5.000 0.7401 0.01426 0.00548 -0.0250 0.0986 1.0000
5.250 0.7675 0.01481 0.00591 -0.0250 0.0686 1.0000
5.500 0.7948 0.01547 0.00643 -0.0250 0.0536 1.0000
5.750 0.8222 0.01599 0.00697 -0.0249 0.0496 1.0000
6.000 0.8494 0.01655 0.00757 -0.0248 0.0470 1.0000
6.250 0.8764 0.01718 0.00826 -0.0247 0.0451 1.0000
6.500 0.9034 0.01775 0.00890 -0.0245 0.0440 1.0000
6.750 0.9301 0.01836 0.00960 -0.0244 0.0428 1.0000
7.000 0.9564 0.01902 0.01036 -0.0242 0.0416 1.0000
7.250 0.9824 0.01974 0.01117 -0.0240 0.0404 1.0000
7.500 1.0080 0.02053 0.01205 -0.0238 0.0396 1.0000
7.750 1.0331 0.02140 0.01301 -0.0236 0.0389 1.0000
8.000 1.0576 0.02238 0.01405 -0.0233 0.0382 1.0000
8.250 1.0814 0.02350 0.01523 -0.0230 0.0375 1.0000
8.500 1.1041 0.02489 0.01668 -0.0226 0.0367 1.0000
8.750 1.1275 0.02602 0.01794 -0.0222 0.0361 1.0000
9.000 1.1510 0.02707 0.01915 -0.0217 0.0355 1.0000
9.250 1.1736 0.02829 0.02052 -0.0213 0.0349 1.0000
9.500 1.1955 0.02963 0.02204 -0.0208 0.0343 1.0000
9.750 1.2167 0.03106 0.02366 -0.0203 0.0336 1.0000
10.000 1.2370 0.03253 0.02531 -0.0198 0.0328 1.0000
10.250 1.2564 0.03406 0.02701 -0.0193 0.0320 1.0000
10.500 1.2746 0.03571 0.02883 -0.0187 0.0313 1.0000
10.750 1.2913 0.03755 0.03082 -0.0181 0.0307 1.0000
11.000 1.3061 0.03964 0.03304 -0.0175 0.0300 1.0000
11.250 1.3157 0.04282 0.03639 -0.0168 0.0292 1.0000
11.500 1.3243 0.04512 0.03903 -0.0162 0.0288 1.0000
11.750 1.3287 0.04773 0.04199 -0.0155 0.0283 1.0000
12.000 1.3271 0.05085 0.04543 -0.0150 0.0279 1.0000
12.250 1.3162 0.05433 0.04918 -0.0143 0.0276 1.0000
12.500 1.2999 0.05920 0.05431 -0.0167 0.0275 1.0000
12.750 1.2816 0.06653 0.06190 -0.0234 0.0274 1.0000
13.000 1.2591 0.07582 0.07144 -0.0317 0.0274 1.0000
13.250 1.2300 0.08639 0.08221 -0.0399 0.0276 1.0000
13.500 1.1936 0.09833 0.09433 -0.0483 0.0278 1.0000
13.750 1.1448 0.11352 0.10967 -0.0583 0.0282 1.0000
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