GOE 647 AIRFOIL (goe647-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 647 AIRFOIL (goe647-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.34 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe647-il-1000000-n5.txt Download as CSV file: xf-goe647-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 647 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
------ -------- --------- --------- -------- -------- --------
-17.750 -0.7154 0.09961 0.09703 -0.0638 1.0000 0.0207
-17.500 -0.7438 0.09144 0.08877 -0.0685 1.0000 0.0208
-17.250 -0.7727 0.08350 0.08072 -0.0732 1.0000 0.0209
-17.000 -0.7969 0.07662 0.07377 -0.0772 1.0000 0.0211
-16.750 -0.8244 0.06972 0.06677 -0.0813 1.0000 0.0211
-16.500 -0.8539 0.06299 0.05994 -0.0852 1.0000 0.0211
-16.250 -0.8864 0.05608 0.05293 -0.0891 1.0000 0.0212
-16.000 -0.9175 0.04955 0.04630 -0.0927 1.0000 0.0212
-15.750 -0.9434 0.04371 0.04036 -0.0957 1.0000 0.0213
-15.250 -0.9603 0.03080 0.02714 -0.1110 0.9967 0.0214
-15.000 -0.9503 0.02776 0.02398 -0.1155 0.9892 0.0216
-14.500 -0.9191 0.02486 0.02091 -0.1175 0.9745 0.0220
-14.250 -0.8956 0.02376 0.01974 -0.1187 0.9688 0.0222
-14.000 -0.8700 0.02274 0.01865 -0.1199 0.9609 0.0224
-13.750 -0.8355 0.02174 0.01756 -0.1227 0.9562 0.0227
-13.500 -0.8018 0.02093 0.01667 -0.1249 0.9487 0.0231
-13.000 -0.7348 0.01934 0.01488 -0.1291 0.9265 0.0236
-12.750 -0.7088 0.01873 0.01416 -0.1295 0.9110 0.0237
-12.500 -0.6875 0.01820 0.01350 -0.1287 0.8947 0.0239
-12.250 -0.6677 0.01774 0.01293 -0.1276 0.8804 0.0240
-12.000 -0.6517 0.01711 0.01219 -0.1259 0.8660 0.0243
-11.750 -0.6334 0.01662 0.01161 -0.1244 0.8529 0.0246
-11.500 -0.6134 0.01619 0.01112 -0.1232 0.8414 0.0248
-11.250 -0.5931 0.01579 0.01063 -0.1219 0.8304 0.0250
-11.000 -0.5717 0.01543 0.01020 -0.1207 0.8197 0.0252
-10.750 -0.5500 0.01508 0.00977 -0.1196 0.8098 0.0255
-10.500 -0.5279 0.01475 0.00937 -0.1185 0.7991 0.0257
-10.250 -0.5052 0.01443 0.00898 -0.1175 0.7893 0.0260
-10.000 -0.4822 0.01416 0.00863 -0.1165 0.7786 0.0263
-9.750 -0.4589 0.01385 0.00826 -0.1156 0.7682 0.0266
-9.500 -0.4359 0.01356 0.00788 -0.1146 0.7574 0.0268
-9.250 -0.4123 0.01328 0.00752 -0.1137 0.7454 0.0270
-9.000 -0.3886 0.01303 0.00719 -0.1127 0.7329 0.0273
-8.750 -0.3650 0.01280 0.00687 -0.1118 0.7177 0.0275
-8.500 -0.3415 0.01262 0.00657 -0.1108 0.6992 0.0276
-8.250 -0.3188 0.01240 0.00624 -0.1096 0.6772 0.0279
-8.000 -0.2962 0.01213 0.00587 -0.1085 0.6573 0.0282
-7.750 -0.2722 0.01191 0.00557 -0.1076 0.6433 0.0286
-7.500 -0.2477 0.01173 0.00532 -0.1068 0.6314 0.0290
-7.250 -0.2222 0.01154 0.00509 -0.1061 0.6214 0.0295
-7.000 -0.1970 0.01139 0.00487 -0.1054 0.6115 0.0299
-6.750 -0.1712 0.01122 0.00464 -0.1048 0.6024 0.0303
-6.500 -0.1456 0.01107 0.00444 -0.1042 0.5938 0.0306
-6.250 -0.1196 0.01092 0.00424 -0.1036 0.5844 0.0311
-6.000 -0.0939 0.01080 0.00405 -0.1030 0.5753 0.0314
-5.750 -0.0675 0.01067 0.00388 -0.1024 0.5665 0.0317
-5.500 -0.0419 0.01053 0.00368 -0.1018 0.5582 0.0323
-5.250 -0.0157 0.01037 0.00350 -0.1013 0.5496 0.0330
-5.000 0.0101 0.01028 0.00335 -0.1006 0.5396 0.0337
-4.750 0.0365 0.01018 0.00322 -0.1001 0.5295 0.0345
-4.500 0.0626 0.01011 0.00309 -0.0995 0.5200 0.0354
-4.250 0.0891 0.01004 0.00298 -0.0990 0.5099 0.0363
-4.000 0.1150 0.00996 0.00286 -0.0984 0.4997 0.0378
-3.750 0.1408 0.00992 0.00277 -0.0978 0.4876 0.0394
-3.500 0.1669 0.00988 0.00268 -0.0973 0.4744 0.0413
-3.250 0.1927 0.00983 0.00260 -0.0967 0.4632 0.0445
-3.000 0.2183 0.00980 0.00253 -0.0960 0.4512 0.0489
-2.750 0.2439 0.00976 0.00246 -0.0954 0.4381 0.0562
-2.500 0.2691 0.00973 0.00242 -0.0947 0.4244 0.0669
-2.250 0.2941 0.00970 0.00238 -0.0940 0.4110 0.0809
-2.000 0.3193 0.00970 0.00236 -0.0933 0.3987 0.0924
-1.750 0.3449 0.00970 0.00234 -0.0927 0.3877 0.1023
-1.500 0.3702 0.00970 0.00232 -0.0921 0.3773 0.1130
-1.250 0.3948 0.00968 0.00230 -0.0913 0.3660 0.1337
-1.000 0.4191 0.00956 0.00232 -0.0905 0.3566 0.1845
-0.750 0.4441 0.00961 0.00235 -0.0898 0.3472 0.2001
-0.500 0.4700 0.00963 0.00238 -0.0893 0.3405 0.2116
-0.250 0.4951 0.00966 0.00242 -0.0886 0.3336 0.2288
0.000 0.5205 0.00969 0.00246 -0.0880 0.3281 0.2456
0.250 0.5463 0.00972 0.00250 -0.0875 0.3230 0.2570
0.500 0.5715 0.00976 0.00255 -0.0868 0.3177 0.2705
0.750 0.5966 0.00983 0.00261 -0.0861 0.3125 0.2820
1.000 0.6221 0.00986 0.00266 -0.0856 0.3087 0.2947
1.250 0.6472 0.00991 0.00273 -0.0849 0.3041 0.3086
1.500 0.6717 0.00998 0.00280 -0.0842 0.2995 0.3264
1.750 0.6961 0.01002 0.00289 -0.0834 0.2956 0.3510
2.000 0.7209 0.01003 0.00296 -0.0827 0.2930 0.3768
2.250 0.7455 0.01007 0.00305 -0.0820 0.2900 0.4002
2.500 0.7697 0.01012 0.00315 -0.0812 0.2868 0.4244
2.750 0.7934 0.01019 0.00325 -0.0803 0.2835 0.4503
3.000 0.8168 0.01028 0.00336 -0.0794 0.2800 0.4702
3.250 0.8408 0.01034 0.00346 -0.0786 0.2778 0.4879
3.500 0.8645 0.01039 0.00356 -0.0777 0.2753 0.5066
3.750 0.8873 0.01044 0.00367 -0.0767 0.2725 0.5304
4.000 0.9079 0.01046 0.00379 -0.0753 0.2694 0.5713
4.250 0.9195 0.01019 0.00395 -0.0720 0.2665 0.7376
4.750 1.0613 0.01039 0.00460 -0.0908 0.2595 1.0000
5.000 1.0832 0.01053 0.00473 -0.0896 0.2574 1.0000
5.250 1.1048 0.01069 0.00487 -0.0884 0.2551 1.0000
5.500 1.1254 0.01086 0.00503 -0.0870 0.2527 1.0000
5.750 1.1442 0.01104 0.00519 -0.0852 0.2502 1.0000
6.000 1.1623 0.01123 0.00536 -0.0834 0.2477 1.0000
6.250 1.1820 0.01139 0.00552 -0.0818 0.2462 1.0000
6.500 1.2022 0.01155 0.00569 -0.0804 0.2448 1.0000
6.750 1.2224 0.01172 0.00587 -0.0790 0.2432 1.0000
7.000 1.2427 0.01191 0.00606 -0.0777 0.2412 1.0000
7.250 1.2626 0.01212 0.00627 -0.0763 0.2389 1.0000
7.500 1.2825 0.01235 0.00649 -0.0750 0.2369 1.0000
7.750 1.3019 0.01261 0.00674 -0.0737 0.2346 1.0000
8.000 1.3210 0.01289 0.00702 -0.0723 0.2323 1.0000
8.250 1.3412 0.01314 0.00728 -0.0711 0.2309 1.0000
8.500 1.3618 0.01338 0.00755 -0.0701 0.2299 1.0000
8.750 1.3822 0.01363 0.00782 -0.0690 0.2286 1.0000
9.000 1.4023 0.01391 0.00812 -0.0680 0.2272 1.0000
9.250 1.4220 0.01420 0.00844 -0.0669 0.2258 1.0000
9.500 1.4415 0.01453 0.00877 -0.0658 0.2241 1.0000
9.750 1.4602 0.01489 0.00915 -0.0647 0.2224 1.0000
10.000 1.4786 0.01528 0.00955 -0.0636 0.2206 1.0000
10.250 1.4959 0.01573 0.01001 -0.0623 0.2183 1.0000
10.500 1.5131 0.01620 0.01050 -0.0612 0.2163 1.0000
10.750 1.5327 0.01657 0.01090 -0.0603 0.2149 1.0000
11.000 1.5516 0.01698 0.01134 -0.0594 0.2126 1.0000
11.250 1.5695 0.01745 0.01184 -0.0585 0.2106 1.0000
11.500 1.5862 0.01800 0.01240 -0.0574 0.2080 1.0000
11.750 1.6023 0.01859 0.01301 -0.0563 0.2059 1.0000
12.000 1.6158 0.01935 0.01377 -0.0551 0.2020 1.0000
12.250 1.6336 0.01988 0.01435 -0.0543 0.2001 1.0000
12.500 1.6497 0.02053 0.01501 -0.0534 0.1960 1.0000
12.750 1.6632 0.02134 0.01584 -0.0523 0.1923 1.0000
13.000 1.6750 0.02229 0.01679 -0.0511 0.1886 1.0000
13.250 1.6903 0.02303 0.01758 -0.0503 0.1867 1.0000
13.500 1.7045 0.02386 0.01844 -0.0494 0.1834 1.0000
13.750 1.7152 0.02494 0.01953 -0.0484 0.1787 1.0000
14.000 1.7242 0.02617 0.02077 -0.0473 0.1744 1.0000
14.250 1.7347 0.02733 0.02196 -0.0463 0.1688 1.0000
14.500 1.7392 0.02898 0.02358 -0.0451 0.1617 1.0000
14.750 1.7465 0.03045 0.02508 -0.0441 0.1559 1.0000
15.000 1.7451 0.03267 0.02728 -0.0429 0.1458 1.0000
15.250 1.7353 0.03574 0.03029 -0.0414 0.1320 1.0000
15.500 1.7247 0.03900 0.03353 -0.0402 0.1206 1.0000
15.750 1.7119 0.04266 0.03717 -0.0393 0.1101 1.0000
16.000 1.7013 0.04622 0.04075 -0.0386 0.1029 1.0000
16.250 1.6893 0.05006 0.04462 -0.0381 0.0958 1.0000
16.500 1.6761 0.05416 0.04875 -0.0379 0.0887 1.0000
16.750 1.6571 0.05903 0.05365 -0.0378 0.0817 1.0000
17.000 1.6396 0.06390 0.05857 -0.0380 0.0763 1.0000
17.250 1.6248 0.06856 0.06330 -0.0383 0.0716 1.0000
17.500 1.5994 0.07466 0.06946 -0.0390 0.0657 1.0000
17.750 1.5809 0.08007 0.07495 -0.0398 0.0617 1.0000
18.000 1.5567 0.08629 0.08125 -0.0409 0.0574 1.0000
18.250 1.5327 0.09267 0.08771 -0.0421 0.0535 1.0000
18.500 1.5092 0.09911 0.09423 -0.0436 0.0502 1.0000
18.750 1.4777 0.10674 0.10194 -0.0455 0.0447 1.0000
19.000 1.4514 0.11381 0.10908 -0.0474 0.0404 1.0000
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