GOE 615 AIRFOIL (goe615-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 615 AIRFOIL (goe615-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.74 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe615-il-1000000-n5.txt Download as CSV file: xf-goe615-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 615 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.8551 0.02796 0.02486 -0.1259 0.9708 0.0211
-14.000 -0.8329 0.02656 0.02338 -0.1273 0.9626 0.0213
-13.750 -0.7992 0.02551 0.02226 -0.1302 0.9580 0.0215
-13.500 -0.7666 0.02450 0.02117 -0.1327 0.9508 0.0218
-13.250 -0.7302 0.02358 0.02016 -0.1358 0.9436 0.0220
-13.000 -0.6970 0.02270 0.01918 -0.1381 0.9314 0.0223
-12.750 -0.6686 0.02196 0.01832 -0.1392 0.9170 0.0226
-12.500 -0.6465 0.02126 0.01748 -0.1390 0.9028 0.0229
-12.250 -0.6282 0.02050 0.01655 -0.1381 0.8883 0.0231
-12.000 -0.6107 0.01976 0.01565 -0.1368 0.8746 0.0233
-11.750 -0.5928 0.01905 0.01480 -0.1356 0.8625 0.0235
-11.500 -0.5729 0.01849 0.01411 -0.1345 0.8527 0.0238
-11.250 -0.5526 0.01798 0.01345 -0.1333 0.8419 0.0240
-11.000 -0.5318 0.01744 0.01278 -0.1323 0.8319 0.0241
-10.750 -0.5111 0.01690 0.01211 -0.1312 0.8232 0.0243
-10.500 -0.4912 0.01615 0.01127 -0.1301 0.8156 0.0245
-10.250 -0.4695 0.01565 0.01068 -0.1291 0.8077 0.0248
-10.000 -0.4462 0.01526 0.01023 -0.1283 0.8006 0.0250
-9.750 -0.4223 0.01496 0.00986 -0.1276 0.7923 0.0253
-9.500 -0.3984 0.01463 0.00945 -0.1268 0.7849 0.0255
-9.250 -0.3743 0.01429 0.00904 -0.1261 0.7768 0.0257
-9.000 -0.3502 0.01397 0.00864 -0.1253 0.7696 0.0260
-8.750 -0.3256 0.01362 0.00822 -0.1247 0.7622 0.0262
-8.500 -0.3014 0.01330 0.00782 -0.1239 0.7547 0.0265
-8.250 -0.2765 0.01296 0.00741 -0.1233 0.7476 0.0267
-8.000 -0.2518 0.01265 0.00701 -0.1226 0.7396 0.0270
-7.750 -0.2267 0.01236 0.00665 -0.1219 0.7323 0.0273
-7.500 -0.2015 0.01208 0.00630 -0.1213 0.7240 0.0275
-7.250 -0.1764 0.01182 0.00596 -0.1206 0.7161 0.0277
-7.000 -0.1506 0.01162 0.00569 -0.1201 0.7071 0.0280
-6.750 -0.1254 0.01137 0.00536 -0.1194 0.6983 0.0282
-6.500 -0.1009 0.01105 0.00498 -0.1187 0.6877 0.0287
-6.250 -0.0756 0.01082 0.00469 -0.1180 0.6770 0.0290
-6.000 -0.0504 0.01065 0.00446 -0.1173 0.6651 0.0293
-5.750 -0.0248 0.01051 0.00425 -0.1167 0.6524 0.0296
-5.500 0.0009 0.01037 0.00406 -0.1161 0.6398 0.0300
-5.250 0.0264 0.01025 0.00386 -0.1154 0.6267 0.0304
-5.000 0.0518 0.01014 0.00368 -0.1148 0.6133 0.0308
-4.500 0.1030 0.00995 0.00335 -0.1135 0.5876 0.0316
-4.250 0.1285 0.00987 0.00320 -0.1129 0.5749 0.0320
-4.000 0.1540 0.00982 0.00306 -0.1122 0.5626 0.0323
-3.750 0.1796 0.00972 0.00291 -0.1116 0.5520 0.0330
-3.500 0.2056 0.00963 0.00279 -0.1111 0.5444 0.0337
-3.250 0.2320 0.00956 0.00269 -0.1106 0.5373 0.0343
-3.000 0.2580 0.00952 0.00261 -0.1100 0.5307 0.0350
-2.750 0.2849 0.00944 0.00252 -0.1097 0.5257 0.0358
-2.500 0.3115 0.00939 0.00244 -0.1092 0.5204 0.0366
-2.250 0.3379 0.00935 0.00237 -0.1088 0.5157 0.0372
-2.000 0.3644 0.00929 0.00229 -0.1083 0.5112 0.0382
-1.750 0.3912 0.00922 0.00223 -0.1080 0.5061 0.0395
-1.500 0.4177 0.00920 0.00219 -0.1075 0.5012 0.0408
-1.250 0.4439 0.00920 0.00216 -0.1070 0.4962 0.0423
-1.000 0.4709 0.00915 0.00211 -0.1067 0.4924 0.0437
-0.750 0.4977 0.00910 0.00208 -0.1063 0.4883 0.0458
-0.500 0.5244 0.00909 0.00205 -0.1059 0.4842 0.0477
-0.250 0.5506 0.00910 0.00204 -0.1055 0.4799 0.0495
0.000 0.5771 0.00907 0.00202 -0.1051 0.4759 0.0526
0.250 0.6039 0.00904 0.00201 -0.1047 0.4713 0.0560
0.500 0.6301 0.00903 0.00201 -0.1043 0.4662 0.0621
0.750 0.6552 0.00898 0.00202 -0.1036 0.4607 0.0929
1.000 0.6803 0.00879 0.00204 -0.1031 0.4549 0.1697
1.250 0.7046 0.00878 0.00209 -0.1023 0.4439 0.2131
1.500 0.7285 0.00882 0.00215 -0.1015 0.4263 0.2471
1.750 0.7509 0.00892 0.00223 -0.1004 0.4007 0.2838
2.000 0.7712 0.00907 0.00237 -0.0990 0.3715 0.3374
2.250 0.7910 0.00921 0.00255 -0.0974 0.3477 0.4034
2.750 0.8290 0.00921 0.00292 -0.0941 0.3146 0.6203
3.000 0.8438 0.00903 0.00309 -0.0914 0.3023 0.7681
3.500 0.9573 0.00934 0.00365 -0.1043 0.2755 1.0000
3.750 0.9781 0.00956 0.00380 -0.1029 0.2663 1.0000
4.000 0.9997 0.00973 0.00393 -0.1016 0.2591 1.0000
4.250 1.0201 0.00996 0.00409 -0.1002 0.2499 1.0000
4.500 1.0414 0.01014 0.00424 -0.0989 0.2438 1.0000
4.750 1.0619 0.01035 0.00440 -0.0974 0.2362 1.0000
5.000 1.0821 0.01057 0.00457 -0.0959 0.2290 1.0000
5.250 1.1005 0.01081 0.00476 -0.0941 0.2199 1.0000
5.500 1.1177 0.01105 0.00496 -0.0921 0.2118 1.0000
5.750 1.1336 0.01134 0.00518 -0.0898 0.2018 1.0000
6.000 1.1506 0.01162 0.00541 -0.0878 0.1924 1.0000
6.250 1.1674 0.01192 0.00566 -0.0858 0.1839 1.0000
6.500 1.1832 0.01228 0.00595 -0.0837 0.1732 1.0000
6.750 1.1987 0.01268 0.00628 -0.0815 0.1612 1.0000
7.000 1.2133 0.01313 0.00665 -0.0793 0.1484 1.0000
7.250 1.2257 0.01370 0.00712 -0.0769 0.1327 1.0000
7.500 1.2308 0.01462 0.00786 -0.0734 0.1036 1.0000
7.750 1.2303 0.01588 0.00892 -0.0693 0.0654 1.0000
8.000 1.2443 0.01649 0.00950 -0.0674 0.0590 1.0000
8.250 1.2607 0.01700 0.01001 -0.0659 0.0563 1.0000
8.500 1.2775 0.01750 0.01052 -0.0645 0.0551 1.0000
8.750 1.2938 0.01805 0.01107 -0.0632 0.0540 1.0000
9.000 1.3101 0.01862 0.01166 -0.0619 0.0531 1.0000
9.250 1.3255 0.01925 0.01230 -0.0605 0.0518 1.0000
9.500 1.3408 0.01992 0.01298 -0.0592 0.0505 1.0000
9.750 1.3556 0.02064 0.01372 -0.0579 0.0492 1.0000
10.000 1.3716 0.02129 0.01441 -0.0568 0.0489 1.0000
10.250 1.3872 0.02198 0.01512 -0.0558 0.0484 1.0000
10.500 1.4023 0.02273 0.01590 -0.0547 0.0476 1.0000
10.750 1.4170 0.02353 0.01672 -0.0536 0.0472 1.0000
11.000 1.4308 0.02440 0.01763 -0.0526 0.0466 1.0000
11.250 1.4438 0.02534 0.01860 -0.0515 0.0458 1.0000
11.500 1.4565 0.02634 0.01962 -0.0504 0.0452 1.0000
11.750 1.4681 0.02744 0.02074 -0.0494 0.0444 1.0000
12.000 1.4786 0.02864 0.02198 -0.0483 0.0435 1.0000
12.250 1.4892 0.02985 0.02323 -0.0473 0.0428 1.0000
12.500 1.4996 0.03111 0.02453 -0.0463 0.0421 1.0000
12.750 1.5112 0.03230 0.02576 -0.0455 0.0417 1.0000
13.000 1.5222 0.03357 0.02707 -0.0448 0.0413 1.0000
13.250 1.5322 0.03493 0.02848 -0.0440 0.0402 1.0000
13.500 1.5408 0.03645 0.03002 -0.0433 0.0387 1.0000
13.750 1.5486 0.03809 0.03169 -0.0425 0.0375 1.0000
14.000 1.5550 0.03990 0.03352 -0.0418 0.0360 1.0000
14.250 1.5620 0.04169 0.03535 -0.0413 0.0339 1.0000
14.500 1.5618 0.04420 0.03783 -0.0405 0.0253 1.0000
14.750 1.5457 0.04849 0.04211 -0.0396 0.0144 1.0000
15.000 1.5432 0.05148 0.04519 -0.0392 0.0127 1.0000
15.250 1.5428 0.05430 0.04808 -0.0389 0.0119 1.0000
15.500 1.5426 0.05715 0.05100 -0.0387 0.0112 1.0000
15.750 1.5429 0.05999 0.05392 -0.0387 0.0108 1.0000
16.000 1.5415 0.06307 0.05707 -0.0387 0.0102 1.0000
16.250 1.5395 0.06622 0.06031 -0.0387 0.0100 1.0000
16.500 1.5346 0.06979 0.06396 -0.0389 0.0095 1.0000
16.750 1.5316 0.07315 0.06740 -0.0391 0.0093 1.0000
17.000 1.5286 0.07656 0.07088 -0.0394 0.0091 1.0000
17.250 1.5241 0.08017 0.07458 -0.0397 0.0088 1.0000
17.500 1.5184 0.08399 0.07848 -0.0402 0.0086 1.0000
17.750 1.5125 0.08788 0.08246 -0.0407 0.0084 1.0000
18.000 1.5062 0.09187 0.08654 -0.0414 0.0082 1.0000
18.250 1.4983 0.09611 0.09086 -0.0422 0.0081 1.0000
18.500 1.4894 0.10054 0.09537 -0.0431 0.0080 1.0000
18.750 1.4791 0.10523 0.10016 -0.0441 0.0077 1.0000
19.000 1.4695 0.10990 0.10492 -0.0453 0.0076 1.0000
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Polar data table (+)
Polar graphs
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