GOE 677 (= M 6) AIRFOIL (goe677-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 677 (= M 6) AIRFOIL (goe677-il) Reynolds number: 200,000 Max Cl/Cd: 63.34 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe677-il-200000-n5.txt Download as CSV file: xf-goe677-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 677 (= M 6) 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6222 0.08853 0.08492 -0.0185 1.0000 0.0328
-10.500 -0.6293 0.08272 0.07914 -0.0226 1.0000 0.0331
-10.250 -0.7478 0.05632 0.05238 -0.0374 1.0000 0.0329
-10.000 -0.7537 0.05354 0.04947 -0.0359 1.0000 0.0332
-9.750 -0.7562 0.05062 0.04638 -0.0344 1.0000 0.0337
-9.500 -0.7556 0.04773 0.04331 -0.0328 1.0000 0.0342
-9.250 -0.7547 0.04453 0.03987 -0.0309 1.0000 0.0349
-9.000 -0.7519 0.04132 0.03637 -0.0289 1.0000 0.0359
-8.750 -0.7500 0.03762 0.03225 -0.0265 1.0000 0.0370
-8.500 -0.7455 0.03409 0.02822 -0.0239 1.0000 0.0381
-8.250 -0.7360 0.03136 0.02503 -0.0216 1.0000 0.0388
-8.000 -0.7225 0.02943 0.02273 -0.0196 1.0000 0.0396
-7.750 -0.7054 0.02801 0.02122 -0.0183 0.9993 0.0404
-7.500 -0.6740 0.02692 0.02004 -0.0198 0.9846 0.0413
-7.250 -0.6435 0.02569 0.01863 -0.0209 0.9664 0.0421
-7.000 -0.6123 0.02442 0.01714 -0.0221 0.9470 0.0430
-6.750 -0.5812 0.02321 0.01570 -0.0230 0.9270 0.0440
-6.500 -0.5523 0.02214 0.01439 -0.0233 0.9058 0.0450
-6.250 -0.5255 0.02130 0.01333 -0.0231 0.8846 0.0462
-6.000 -0.4998 0.02058 0.01238 -0.0225 0.8642 0.0474
-5.750 -0.4744 0.01992 0.01150 -0.0219 0.8452 0.0482
-5.500 -0.4497 0.01893 0.01042 -0.0214 0.8280 0.0493
-5.250 -0.4248 0.01830 0.00971 -0.0208 0.8119 0.0504
-5.000 -0.3997 0.01779 0.00911 -0.0202 0.7966 0.0516
-4.750 -0.3745 0.01732 0.00853 -0.0196 0.7823 0.0530
-4.500 -0.3492 0.01688 0.00797 -0.0190 0.7692 0.0546
-4.250 -0.3237 0.01648 0.00745 -0.0184 0.7577 0.0565
-4.000 -0.2975 0.01616 0.00701 -0.0180 0.7478 0.0586
-3.750 -0.2727 0.01564 0.00646 -0.0175 0.7393 0.0612
-3.500 -0.2470 0.01528 0.00607 -0.0171 0.7304 0.0639
-3.250 -0.2212 0.01498 0.00569 -0.0166 0.7224 0.0670
-3.000 -0.1951 0.01471 0.00534 -0.0162 0.7141 0.0702
-2.750 -0.1696 0.01438 0.00497 -0.0157 0.7073 0.0741
-2.500 -0.1435 0.01411 0.00470 -0.0154 0.7009 0.0798
-2.250 -0.1171 0.01391 0.00444 -0.0151 0.6952 0.0861
-2.000 -0.0910 0.01365 0.00423 -0.0148 0.6894 0.0948
-1.750 -0.0646 0.01343 0.00405 -0.0145 0.6834 0.1077
-1.500 -0.0384 0.01322 0.00389 -0.0142 0.6782 0.1303
-1.250 -0.0124 0.01295 0.00373 -0.0139 0.6729 0.1624
-1.000 0.0112 0.01241 0.00359 -0.0133 0.6671 0.2558
-0.750 0.0295 0.01148 0.00340 -0.0118 0.6620 0.4555
-0.500 0.0562 0.01044 0.00388 -0.0103 0.6562 0.8470
-0.250 0.0890 0.01070 0.00413 -0.0105 0.6501 0.8999
0.250 0.1565 0.01124 0.00453 -0.0118 0.6382 0.9437
0.500 0.2060 0.01155 0.00475 -0.0159 0.6313 0.9578
0.750 0.2570 0.01174 0.00488 -0.0205 0.6237 0.9677
1.000 0.3013 0.01185 0.00493 -0.0239 0.6164 0.9762
1.250 0.3390 0.01193 0.00495 -0.0260 0.6088 0.9830
1.500 0.3794 0.01192 0.00490 -0.0288 0.6002 0.9872
1.750 0.4153 0.01192 0.00487 -0.0306 0.5914 0.9909
2.000 0.4474 0.01193 0.00482 -0.0316 0.5813 0.9939
2.250 0.4800 0.01188 0.00476 -0.0328 0.5682 0.9955
2.500 0.5120 0.01186 0.00471 -0.0338 0.5547 0.9974
2.750 0.5438 0.01185 0.00469 -0.0348 0.5413 0.9993
3.000 0.5717 0.01187 0.00469 -0.0350 0.5279 1.0000
3.250 0.5967 0.01190 0.00468 -0.0345 0.5126 1.0000
3.500 0.6213 0.01196 0.00466 -0.0340 0.4928 1.0000
3.750 0.6455 0.01208 0.00467 -0.0334 0.4717 1.0000
4.000 0.6697 0.01223 0.00472 -0.0328 0.4531 1.0000
4.250 0.6938 0.01240 0.00482 -0.0323 0.4385 1.0000
4.500 0.7179 0.01258 0.00496 -0.0317 0.4265 1.0000
4.750 0.7419 0.01274 0.00512 -0.0311 0.4157 1.0000
5.000 0.7658 0.01291 0.00529 -0.0305 0.4061 1.0000
5.250 0.7891 0.01312 0.00549 -0.0298 0.3960 1.0000
5.500 0.8125 0.01330 0.00570 -0.0291 0.3840 1.0000
5.750 0.8354 0.01351 0.00592 -0.0283 0.3704 1.0000
6.000 0.8579 0.01372 0.00615 -0.0275 0.3555 1.0000
6.250 0.8800 0.01395 0.00639 -0.0265 0.3387 1.0000
6.500 0.9013 0.01423 0.00665 -0.0255 0.3181 1.0000
6.750 0.9218 0.01456 0.00693 -0.0243 0.2915 1.0000
7.000 0.9404 0.01502 0.00729 -0.0229 0.2604 1.0000
7.250 0.9573 0.01561 0.00774 -0.0213 0.2266 1.0000
7.500 0.9726 0.01630 0.00828 -0.0195 0.1934 1.0000
7.750 0.9869 0.01705 0.00888 -0.0175 0.1641 1.0000
8.000 1.0005 0.01778 0.00949 -0.0154 0.1396 1.0000
8.250 1.0144 0.01846 0.01010 -0.0133 0.1208 1.0000
8.500 1.0283 0.01908 0.01068 -0.0112 0.1097 1.0000
9.000 1.0555 0.02030 0.01190 -0.0070 0.0961 1.0000
9.250 1.0674 0.02096 0.01257 -0.0046 0.0909 1.0000
9.500 1.0796 0.02160 0.01325 -0.0024 0.0864 1.0000
9.750 1.0922 0.02221 0.01393 -0.0002 0.0807 1.0000
10.000 1.1007 0.02306 0.01478 0.0023 0.0754 1.0000
10.250 1.1153 0.02355 0.01539 0.0041 0.0702 1.0000
10.500 1.1241 0.02427 0.01614 0.0066 0.0635 1.0000
10.750 1.1355 0.02495 0.01687 0.0086 0.0525 1.0000
11.000 1.1411 0.02610 0.01790 0.0109 0.0372 1.0000
11.250 1.1434 0.02763 0.01938 0.0131 0.0293 1.0000
11.500 1.1476 0.02919 0.02098 0.0147 0.0259 1.0000
11.750 1.1507 0.03099 0.02281 0.0161 0.0237 1.0000
12.000 1.1562 0.03271 0.02464 0.0171 0.0223 1.0000
12.250 1.1608 0.03462 0.02666 0.0179 0.0210 1.0000
12.500 1.1638 0.03676 0.02889 0.0185 0.0200 1.0000
12.750 1.1646 0.03922 0.03143 0.0189 0.0191 1.0000
13.000 1.1655 0.04172 0.03405 0.0192 0.0184 1.0000
13.250 1.1677 0.04416 0.03664 0.0194 0.0179 1.0000
13.500 1.1683 0.04682 0.03942 0.0194 0.0174 1.0000
13.750 1.1677 0.04966 0.04239 0.0194 0.0170 1.0000
14.000 1.1661 0.05266 0.04552 0.0192 0.0166 1.0000
14.250 1.1636 0.05584 0.04881 0.0188 0.0163 1.0000
14.500 1.1601 0.05919 0.05228 0.0184 0.0160 1.0000
14.750 1.1562 0.06274 0.05594 0.0177 0.0157 1.0000
15.000 1.1515 0.06650 0.05981 0.0168 0.0154 1.0000
15.250 1.1465 0.07044 0.06386 0.0158 0.0152 1.0000
15.500 1.1409 0.07457 0.06809 0.0145 0.0149 1.0000
15.750 1.1345 0.07887 0.07248 0.0132 0.0147 1.0000
16.000 1.1279 0.08319 0.07687 0.0120 0.0144 1.0000
16.250 1.1245 0.08728 0.08109 0.0106 0.0142 1.0000
16.500 1.1208 0.09149 0.08545 0.0091 0.0140 1.0000
16.750 1.1164 0.09588 0.08998 0.0075 0.0137 1.0000
17.000 1.1115 0.10040 0.09463 0.0057 0.0135 1.0000
17.250 1.1061 0.10508 0.09944 0.0038 0.0133 1.0000
17.500 1.1006 0.10984 0.10433 0.0018 0.0132 1.0000
17.750 1.0946 0.11476 0.10937 -0.0003 0.0130 1.0000
18.000 1.0880 0.11989 0.11463 -0.0027 0.0129 1.0000
18.250 1.0813 0.12518 0.12006 -0.0052 0.0128 1.0000
18.500 1.0740 0.13070 0.12571 -0.0080 0.0127 1.0000
18.750 1.0661 0.13651 0.13165 -0.0110 0.0126 1.0000
19.000 1.0575 0.14264 0.13791 -0.0144 0.0125 1.0000
19.250 1.0478 0.14921 0.14463 -0.0181 0.0125 1.0000
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Polar data table (+)
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