GOE 234 (MVA CA5) AIRFOIL (goe234-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 234 (MVA CA5) AIRFOIL (goe234-il) Reynolds number: 500,000 Max Cl/Cd: 108.38 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe234-il-500000-n5.txt Download as CSV file: xf-goe234-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 234 (MVA CA5) 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3627 0.06103 0.05776 -0.1122 0.8715 0.0249
-11.500 -0.3842 0.05365 0.05011 -0.1190 0.8594 0.0251
-11.250 -0.3811 0.04903 0.04534 -0.1251 0.8505 0.0254
-10.750 -0.3468 0.04364 0.03980 -0.1341 0.8378 0.0261
-10.500 -0.3251 0.04104 0.03711 -0.1393 0.8320 0.0265
-10.250 -0.3005 0.03833 0.03427 -0.1451 0.8269 0.0269
-10.000 -0.2722 0.03572 0.03153 -0.1514 0.8223 0.0274
-9.750 -0.2409 0.03326 0.02894 -0.1579 0.8176 0.0281
-9.500 -0.2065 0.03090 0.02640 -0.1646 0.8131 0.0288
-9.250 -0.1708 0.02896 0.02428 -0.1705 0.8090 0.0293
-9.000 -0.1352 0.02743 0.02263 -0.1753 0.8054 0.0298
-8.750 -0.1000 0.02625 0.02141 -0.1794 0.8013 0.0304
-8.500 -0.0635 0.02509 0.02019 -0.1837 0.7970 0.0310
-8.250 -0.0273 0.02407 0.01908 -0.1876 0.7930 0.0316
-7.750 0.0447 0.02229 0.01714 -0.1943 0.7854 0.0329
-7.500 0.0805 0.02152 0.01630 -0.1973 0.7810 0.0335
-7.250 0.1163 0.02080 0.01547 -0.2003 0.7766 0.0342
-7.000 0.1512 0.02021 0.01482 -0.2027 0.7726 0.0349
-6.750 0.1869 0.01959 0.01417 -0.2055 0.7685 0.0357
-6.500 0.2228 0.01896 0.01351 -0.2082 0.7637 0.0364
-6.250 0.2585 0.01838 0.01287 -0.2108 0.7586 0.0373
-6.000 0.2939 0.01785 0.01226 -0.2132 0.7541 0.0382
-5.750 0.3294 0.01731 0.01167 -0.2156 0.7494 0.0391
-5.500 0.3646 0.01680 0.01109 -0.2179 0.7438 0.0401
-5.250 0.4014 0.01618 0.01042 -0.2208 0.7380 0.0415
-5.000 0.4372 0.01562 0.00981 -0.2233 0.7325 0.0429
-4.750 0.4727 0.01508 0.00921 -0.2256 0.7264 0.0445
-4.500 0.5077 0.01458 0.00862 -0.2278 0.7199 0.0461
-4.250 0.5441 0.01395 0.00791 -0.2304 0.7134 0.0482
-4.000 0.5793 0.01338 0.00727 -0.2327 0.7056 0.0508
-3.750 0.6130 0.01295 0.00673 -0.2344 0.6985 0.0537
-3.500 0.6480 0.01235 0.00606 -0.2365 0.6910 0.0577
-3.000 0.7137 0.01155 0.00507 -0.2394 0.6754 0.0668
-2.500 0.7797 0.01067 0.00412 -0.2424 0.6577 0.1303
-2.250 0.8125 0.01015 0.00367 -0.2440 0.6487 0.2093
-2.000 0.8419 0.01015 0.00374 -0.2443 0.6398 0.2552
-1.750 0.8704 0.01028 0.00378 -0.2443 0.6312 0.2678
-1.500 0.8990 0.01041 0.00390 -0.2442 0.6221 0.2758
-1.250 0.9273 0.01054 0.00392 -0.2442 0.6133 0.2821
-1.000 0.9559 0.01065 0.00402 -0.2442 0.6047 0.2862
-0.750 0.9837 0.01083 0.00413 -0.2440 0.5955 0.2895
-0.500 1.0118 0.01097 0.00422 -0.2439 0.5842 0.2932
-0.250 1.0397 0.01112 0.00427 -0.2438 0.5740 0.2974
0.000 1.0676 0.01127 0.00440 -0.2437 0.5658 0.3009
0.250 1.0953 0.01146 0.00457 -0.2435 0.5599 0.3036
0.500 1.1237 0.01155 0.00466 -0.2435 0.5538 0.3053
0.750 1.1516 0.01166 0.00474 -0.2435 0.5473 0.3069
1.000 1.1795 0.01177 0.00481 -0.2434 0.5412 0.3083
1.250 1.2075 0.01186 0.00487 -0.2434 0.5343 0.3097
1.500 1.2349 0.01199 0.00496 -0.2433 0.5268 0.3113
1.750 1.2625 0.01211 0.00504 -0.2432 0.5194 0.3131
2.000 1.2896 0.01226 0.00514 -0.2430 0.5109 0.3148
2.250 1.3165 0.01240 0.00529 -0.2428 0.5031 0.3164
2.500 1.3432 0.01256 0.00544 -0.2425 0.4945 0.3176
2.750 1.3696 0.01274 0.00560 -0.2422 0.4863 0.3189
3.000 1.3957 0.01293 0.00577 -0.2418 0.4767 0.3202
3.250 1.4216 0.01312 0.00595 -0.2415 0.4672 0.3214
3.500 1.4466 0.01336 0.00615 -0.2409 0.4562 0.3228
3.750 1.4718 0.01358 0.00634 -0.2404 0.4442 0.3242
4.000 1.4956 0.01388 0.00658 -0.2397 0.4290 0.3257
4.250 1.5178 0.01426 0.00687 -0.2387 0.4093 0.3271
4.750 1.5590 0.01519 0.00757 -0.2361 0.3684 0.3296
5.000 1.5789 0.01566 0.00796 -0.2347 0.3509 0.3308
5.250 1.5975 0.01618 0.00841 -0.2331 0.3331 0.3320
5.500 1.6143 0.01675 0.00890 -0.2312 0.3153 0.3331
5.750 1.6302 0.01732 0.00942 -0.2291 0.3006 0.3344
6.000 1.6458 0.01785 0.00992 -0.2269 0.2890 0.3358
6.250 1.6586 0.01833 0.01041 -0.2241 0.2809 0.3372
6.500 1.6727 0.01889 0.01096 -0.2218 0.2731 0.3386
6.750 1.6888 0.01944 0.01152 -0.2198 0.2668 0.3401
7.000 1.7054 0.01998 0.01208 -0.2180 0.2608 0.3416
7.250 1.7196 0.02068 0.01277 -0.2159 0.2539 0.3430
7.500 1.7352 0.02132 0.01342 -0.2140 0.2470 0.3443
7.750 1.7487 0.02210 0.01418 -0.2119 0.2393 0.3455
8.000 1.7625 0.02287 0.01497 -0.2099 0.2331 0.3467
8.250 1.7777 0.02358 0.01572 -0.2081 0.2274 0.3480
8.500 1.7914 0.02440 0.01658 -0.2062 0.2227 0.3492
8.750 1.8037 0.02533 0.01753 -0.2041 0.2179 0.3506
9.000 1.8187 0.02610 0.01837 -0.2025 0.2134 0.3521
9.250 1.8316 0.02704 0.01935 -0.2006 0.2079 0.3538
9.500 1.8412 0.02825 0.02055 -0.1985 0.2015 0.3553
9.750 1.8541 0.02922 0.02158 -0.1967 0.1941 0.3569
10.000 1.8623 0.03060 0.02295 -0.1946 0.1844 0.3583
10.250 1.8692 0.03212 0.02443 -0.1924 0.1694 0.3595
10.500 1.8535 0.03557 0.02757 -0.1881 0.1237 0.3602
10.750 1.8401 0.03899 0.03084 -0.1842 0.0974 0.3608
11.000 1.8349 0.04179 0.03359 -0.1814 0.0811 0.3616
11.250 1.8186 0.04577 0.03742 -0.1779 0.0490 0.3622
11.500 1.8132 0.04888 0.04051 -0.1755 0.0385 0.3631
11.750 1.8150 0.05133 0.04302 -0.1738 0.0354 0.3641
12.000 1.8177 0.05372 0.04549 -0.1722 0.0332 0.3652
12.250 1.8218 0.05603 0.04789 -0.1708 0.0319 0.3665
12.500 1.8246 0.05853 0.05047 -0.1695 0.0308 0.3679
12.750 1.8263 0.06120 0.05323 -0.1681 0.0297 0.3694
13.000 1.8268 0.06406 0.05618 -0.1669 0.0287 0.3708
13.250 1.8271 0.06699 0.05920 -0.1657 0.0278 0.3722
13.500 1.8296 0.06973 0.06204 -0.1647 0.0272 0.3736
13.750 1.8311 0.07260 0.06501 -0.1638 0.0266 0.3748
14.000 1.8316 0.07565 0.06815 -0.1630 0.0259 0.3759
14.250 1.8305 0.07896 0.07155 -0.1622 0.0252 0.3769
14.500 1.8279 0.08248 0.07517 -0.1615 0.0246 0.3779
14.750 1.8241 0.08620 0.07900 -0.1609 0.0239 0.3790
15.000 1.8180 0.09032 0.08322 -0.1604 0.0233 0.3799
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