GOE 704 AIRFOIL (goe704-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 704 AIRFOIL (goe704-il) Reynolds number: 50,000 Max Cl/Cd: 31.57 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe704-il-50000-n5.txt Download as CSV file: xf-goe704-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 704 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5767 0.09757 0.09054 -0.0246 1.0000 0.0787
-10.750 -0.6029 0.08747 0.08054 -0.0315 1.0000 0.0795
-10.500 -0.6391 0.07586 0.06898 -0.0399 1.0000 0.0793
-10.250 -0.6759 0.06824 0.06129 -0.0423 1.0000 0.0790
-10.000 -0.7109 0.06217 0.05504 -0.0413 1.0000 0.0793
-9.750 -0.7426 0.05590 0.04835 -0.0392 1.0000 0.0805
-9.500 -0.7189 0.05654 0.04916 -0.0381 1.0000 0.0851
-9.250 -0.7248 0.05316 0.04552 -0.0361 1.0000 0.0890
-9.000 -0.7419 0.04801 0.03971 -0.0329 1.0000 0.0932
-8.750 -0.7206 0.04814 0.04003 -0.0319 1.0000 0.0981
-8.500 -0.7187 0.04547 0.03696 -0.0294 1.0000 0.1038
-8.250 -0.7119 0.04354 0.03480 -0.0270 1.0000 0.1091
-8.000 -0.7009 0.04234 0.03349 -0.0248 1.0000 0.1145
-7.750 -0.7001 0.03982 0.03037 -0.0214 1.0000 0.1209
-7.500 -0.6865 0.03926 0.02996 -0.0193 1.0000 0.1258
-7.250 -0.6789 0.03795 0.02841 -0.0165 1.0000 0.1319
-7.000 -0.6718 0.03654 0.02669 -0.0136 1.0000 0.1379
-6.750 -0.6608 0.03586 0.02599 -0.0113 1.0000 0.1437
-6.500 -0.6515 0.03460 0.02427 -0.0087 1.0000 0.1508
-6.250 -0.6384 0.03385 0.02353 -0.0067 1.0000 0.1564
-6.000 -0.6100 0.03273 0.02202 -0.0076 0.9943 0.1664
-5.750 -0.5765 0.03183 0.02108 -0.0095 0.9869 0.1748
-5.500 -0.5431 0.03088 0.01981 -0.0112 0.9797 0.1851
-5.250 -0.5081 0.03014 0.01894 -0.0131 0.9731 0.1950
-5.000 -0.4753 0.02943 0.01812 -0.0146 0.9657 0.2043
-4.750 -0.4378 0.02873 0.01717 -0.0169 0.9598 0.2149
-4.500 -0.4057 0.02819 0.01659 -0.0181 0.9524 0.2243
-4.250 -0.3667 0.02760 0.01589 -0.0206 0.9468 0.2344
-4.000 -0.3305 0.02714 0.01527 -0.0224 0.9403 0.2461
-3.750 -0.2927 0.02671 0.01480 -0.0247 0.9341 0.2589
-3.500 -0.2496 0.02623 0.01429 -0.0278 0.9296 0.2732
-3.250 -0.2179 0.02587 0.01393 -0.0289 0.9218 0.2889
-3.000 -0.1809 0.02545 0.01356 -0.0309 0.9159 0.3113
-2.750 -0.1494 0.02504 0.01326 -0.0319 0.9090 0.3371
-2.500 -0.1197 0.02460 0.01300 -0.0325 0.9017 0.3720
-2.250 -0.0899 0.02402 0.01275 -0.0331 0.8953 0.4277
-2.000 0.0236 0.02292 0.01348 -0.0467 0.8990 0.8335
-1.750 0.0479 0.02349 0.01384 -0.0453 0.8902 0.9195
-1.500 0.1248 0.02374 0.01383 -0.0544 0.8871 0.9731
-1.250 0.2056 0.02341 0.01327 -0.0651 0.8831 1.0000
-1.000 0.2301 0.02350 0.01321 -0.0648 0.8715 1.0000
-0.750 0.2557 0.02355 0.01313 -0.0644 0.8602 1.0000
-0.500 0.2827 0.02352 0.01298 -0.0641 0.8493 1.0000
-0.250 0.3054 0.02359 0.01296 -0.0631 0.8362 1.0000
0.000 0.3278 0.02367 0.01295 -0.0619 0.8231 1.0000
0.250 0.3504 0.02374 0.01294 -0.0607 0.8104 1.0000
0.500 0.3737 0.02377 0.01290 -0.0596 0.7985 1.0000
0.750 0.3971 0.02378 0.01285 -0.0584 0.7869 1.0000
1.000 0.4185 0.02391 0.01294 -0.0571 0.7736 1.0000
1.250 0.4402 0.02402 0.01302 -0.0557 0.7606 1.0000
1.500 0.4624 0.02409 0.01306 -0.0543 0.7478 1.0000
1.750 0.4849 0.02411 0.01306 -0.0529 0.7350 1.0000
2.000 0.5078 0.02408 0.01300 -0.0514 0.7222 1.0000
2.250 0.5288 0.02416 0.01307 -0.0498 0.7072 1.0000
2.500 0.5499 0.02421 0.01313 -0.0482 0.6918 1.0000
2.750 0.5710 0.02423 0.01317 -0.0465 0.6759 1.0000
3.000 0.5921 0.02424 0.01317 -0.0448 0.6594 1.0000
3.250 0.6128 0.02425 0.01320 -0.0431 0.6420 1.0000
3.500 0.6322 0.02436 0.01334 -0.0413 0.6223 1.0000
3.750 0.6523 0.02440 0.01341 -0.0395 0.6025 1.0000
4.000 0.6731 0.02440 0.01341 -0.0378 0.5830 1.0000
4.250 0.6935 0.02447 0.01347 -0.0360 0.5624 1.0000
4.500 0.7134 0.02459 0.01359 -0.0343 0.5406 1.0000
4.750 0.7343 0.02468 0.01364 -0.0325 0.5201 1.0000
5.000 0.7541 0.02492 0.01384 -0.0308 0.4989 1.0000
5.250 0.7739 0.02521 0.01407 -0.0292 0.4788 1.0000
5.500 0.7938 0.02555 0.01434 -0.0276 0.4602 1.0000
5.750 0.8136 0.02596 0.01471 -0.0260 0.4430 1.0000
6.000 0.8330 0.02644 0.01514 -0.0245 0.4268 1.0000
6.250 0.8522 0.02699 0.01566 -0.0229 0.4115 1.0000
6.500 0.8710 0.02759 0.01626 -0.0214 0.3972 1.0000
6.750 0.8899 0.02825 0.01697 -0.0200 0.3843 1.0000
7.000 0.9091 0.02892 0.01768 -0.0186 0.3725 1.0000
7.250 0.9286 0.02958 0.01832 -0.0172 0.3611 1.0000
7.500 0.9468 0.03027 0.01905 -0.0157 0.3493 1.0000
7.750 0.9633 0.03106 0.01997 -0.0141 0.3377 1.0000
8.000 0.9805 0.03180 0.02076 -0.0125 0.3268 1.0000
8.250 0.9988 0.03246 0.02139 -0.0110 0.3160 1.0000
8.500 1.0115 0.03332 0.02242 -0.0089 0.3046 1.0000
8.750 1.0259 0.03416 0.02336 -0.0071 0.2944 1.0000
9.000 1.0440 0.03488 0.02413 -0.0056 0.2855 1.0000
9.250 1.0552 0.03594 0.02541 -0.0035 0.2763 1.0000
9.500 1.0722 0.03676 0.02628 -0.0020 0.2681 1.0000
9.750 1.0824 0.03785 0.02759 0.0001 0.2593 1.0000
10.000 1.0957 0.03883 0.02869 0.0020 0.2511 1.0000
10.250 1.1067 0.03993 0.02995 0.0040 0.2429 1.0000
10.500 1.1179 0.04114 0.03136 0.0059 0.2355 1.0000
10.750 1.1280 0.04237 0.03277 0.0078 0.2280 1.0000
11.000 1.1362 0.04375 0.03433 0.0099 0.2207 1.0000
11.250 1.1424 0.04508 0.03583 0.0122 0.2131 1.0000
11.500 1.1417 0.04657 0.03747 0.0151 0.2055 1.0000
11.750 1.1421 0.04765 0.03860 0.0178 0.1969 1.0000
12.000 1.1305 0.04977 0.04092 0.0206 0.1889 1.0000
12.250 1.1280 0.05090 0.04201 0.0227 0.1792 1.0000
12.500 1.1114 0.05392 0.04528 0.0243 0.1710 1.0000
12.750 1.1012 0.05635 0.04775 0.0252 0.1619 1.0000
13.000 1.0891 0.05935 0.05086 0.0256 0.1528 1.0000
13.250 1.0728 0.06357 0.05526 0.0253 0.1450 1.0000
13.500 1.0656 0.06661 0.05830 0.0250 0.1366 1.0000
13.750 1.0451 0.07242 0.06441 0.0234 0.1307 1.0000
14.000 1.0378 0.07608 0.06810 0.0226 0.1233 1.0000
14.250 1.0132 0.08329 0.07556 0.0199 0.1186 1.0000
14.500 1.0070 0.08714 0.07941 0.0186 0.1108 1.0000
14.750 0.9787 0.09586 0.08834 0.0149 0.1072 1.0000
15.000 0.9781 0.09893 0.09134 0.0138 0.0981 1.0000
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