GOE 547 AIRFOIL (goe547-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 547 AIRFOIL (goe547-il) Reynolds number: 100,000 Max Cl/Cd: 60.36 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe547-il-100000.txt Download as CSV file: xf-goe547-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 547 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4331 0.09820 0.09374 -0.0278 1.0000 0.1221
-7.500 -0.4692 0.09770 0.09338 -0.0264 1.0000 0.1230
-7.250 -0.5041 0.09515 0.09091 -0.0329 1.0000 0.1238
-7.000 -0.4747 0.09196 0.08773 -0.0218 1.0000 0.1267
-6.750 -0.4749 0.09003 0.08583 -0.0193 1.0000 0.1300
-6.500 -0.4878 0.08770 0.08355 -0.0203 1.0000 0.1353
-6.250 -0.5042 0.08319 0.07906 -0.0263 1.0000 0.1394
-6.000 -0.4958 0.08219 0.07811 -0.0193 1.0000 0.1435
-5.750 -0.5015 0.07720 0.07303 -0.0283 0.9996 0.1536
-5.500 -0.4780 0.07550 0.07138 -0.0245 0.9957 0.1593
-5.250 -0.4518 0.07083 0.06661 -0.0316 0.9889 0.1719
-5.000 -0.4178 0.06641 0.06185 -0.0439 0.9809 0.1968
-4.750 -0.3997 0.06328 0.05885 -0.0416 0.9760 0.2011
-4.500 -0.3397 0.04452 0.03803 -0.0645 0.9718 0.1237
-4.250 -0.3212 0.04450 0.03868 -0.0635 0.9649 0.1427
-4.000 -0.2764 0.03453 0.02653 -0.0679 0.9621 0.0960
-3.750 -0.2409 0.03247 0.02410 -0.0700 0.9578 0.0969
-3.500 -0.2142 0.03103 0.02245 -0.0704 0.9512 0.0987
-3.250 -0.1768 0.02967 0.02070 -0.0722 0.9467 0.0988
-3.000 -0.1478 0.02867 0.01949 -0.0726 0.9404 0.1002
-2.750 -0.1146 0.02780 0.01847 -0.0737 0.9348 0.1028
-2.500 -0.0746 0.02722 0.01768 -0.0759 0.9312 0.1082
-2.250 -0.0538 0.02651 0.01705 -0.0750 0.9233 0.1142
-2.000 -0.0175 0.02600 0.01651 -0.0766 0.9186 0.1231
-1.750 0.0079 0.02553 0.01616 -0.0763 0.9123 0.1365
-1.500 0.0364 0.02497 0.01592 -0.0767 0.9064 0.1805
-1.250 0.0719 0.02385 0.01604 -0.0784 0.9027 0.4417
-1.000 0.0893 0.02382 0.01636 -0.0767 0.8950 0.5547
-0.750 0.1503 0.02278 0.01645 -0.0825 0.8926 1.0000
-0.500 0.1910 0.02308 0.01641 -0.0853 0.8883 1.0000
-0.250 0.2099 0.02352 0.01665 -0.0842 0.8800 1.0000
0.000 0.2446 0.02384 0.01676 -0.0858 0.8748 1.0000
0.250 0.2718 0.02426 0.01702 -0.0862 0.8685 1.0000
0.500 0.2977 0.02465 0.01728 -0.0862 0.8615 1.0000
0.750 0.3387 0.02488 0.01737 -0.0887 0.8577 1.0000
1.000 0.3506 0.02551 0.01792 -0.0865 0.8485 1.0000
1.250 0.3881 0.02574 0.01806 -0.0884 0.8439 1.0000
1.500 0.4052 0.02635 0.01860 -0.0870 0.8356 1.0000
1.750 0.4390 0.02659 0.01878 -0.0882 0.8300 1.0000
2.000 0.4640 0.02705 0.01921 -0.0880 0.8230 1.0000
2.250 0.4930 0.02733 0.01946 -0.0883 0.8157 1.0000
2.500 0.5238 0.02749 0.01960 -0.0887 0.8077 1.0000
2.750 0.5679 0.02702 0.01913 -0.0907 0.7997 1.0000
3.000 0.5964 0.02695 0.01906 -0.0904 0.7888 1.0000
3.250 0.6504 0.02603 0.01817 -0.0937 0.7841 1.0000
3.500 0.6689 0.02642 0.01860 -0.0921 0.7734 1.0000
3.750 0.7192 0.02565 0.01790 -0.0950 0.7695 1.0000
4.000 0.7375 0.02603 0.01833 -0.0933 0.7590 1.0000
4.250 0.7952 0.02485 0.01727 -0.0972 0.7547 1.0000
4.500 0.8191 0.02484 0.01733 -0.0960 0.7438 1.0000
4.750 0.8801 0.02325 0.01588 -0.0999 0.7385 1.0000
5.000 0.9064 0.02298 0.01570 -0.0988 0.7262 1.0000
5.250 0.9393 0.02243 0.01526 -0.0986 0.7144 1.0000
5.500 0.9782 0.02164 0.01461 -0.0993 0.7027 1.0000
5.750 1.0168 0.02093 0.01401 -0.1000 0.6901 1.0000
6.000 1.0459 0.02043 0.01361 -0.0991 0.6730 1.0000
6.250 1.0770 0.01981 0.01306 -0.0983 0.6525 1.0000
6.500 1.1034 0.01934 0.01266 -0.0968 0.6281 1.0000
6.750 1.1268 0.01906 0.01240 -0.0949 0.6007 1.0000
7.000 1.1439 0.01904 0.01242 -0.0921 0.5705 1.0000
7.250 1.1558 0.01915 0.01254 -0.0884 0.5341 1.0000
7.500 1.1649 0.01937 0.01268 -0.0843 0.4895 1.0000
7.750 1.1706 0.01985 0.01289 -0.0798 0.4371 1.0000
8.000 1.1714 0.02066 0.01337 -0.0747 0.3850 1.0000
8.250 1.1698 0.02173 0.01409 -0.0696 0.3375 1.0000
8.500 1.1678 0.02295 0.01502 -0.0648 0.2927 1.0000
8.750 1.1659 0.02427 0.01611 -0.0604 0.2493 1.0000
9.000 1.1641 0.02574 0.01734 -0.0563 0.2060 1.0000
9.250 1.1607 0.02747 0.01877 -0.0522 0.1608 1.0000
9.500 1.1547 0.02969 0.02063 -0.0482 0.1265 1.0000
9.750 1.1488 0.03231 0.02298 -0.0442 0.1005 1.0000
10.000 1.1517 0.03437 0.02497 -0.0414 0.0824 1.0000
10.250 1.1590 0.03619 0.02675 -0.0391 0.0721 1.0000
10.500 1.1722 0.03814 0.02854 -0.0375 0.0657 1.0000
10.750 1.1938 0.03986 0.03039 -0.0364 0.0606 1.0000
11.000 1.2265 0.04229 0.03266 -0.0369 0.0550 1.0000
11.250 1.2468 0.04426 0.03495 -0.0359 0.0522 1.0000
11.500 1.2751 0.04691 0.03785 -0.0358 0.0501 1.0000
11.750 1.2969 0.04985 0.04105 -0.0352 0.0487 1.0000
12.000 1.3100 0.05287 0.04435 -0.0339 0.0478 1.0000
12.250 1.3175 0.05584 0.04755 -0.0322 0.0468 1.0000
12.500 1.3259 0.05964 0.05155 -0.0310 0.0457 1.0000
13.000 1.3115 0.06792 0.06041 -0.0263 0.0448 1.0000
13.250 1.2956 0.07123 0.06402 -0.0236 0.0447 1.0000
13.500 1.2795 0.07514 0.06820 -0.0216 0.0447 1.0000
13.750 1.2663 0.07957 0.07290 -0.0203 0.0450 1.0000
14.000 1.2465 0.08341 0.07700 -0.0191 0.0451 1.0000
14.250 1.2245 0.08721 0.08107 -0.0186 0.0455 1.0000
14.500 1.1937 0.09246 0.08664 -0.0193 0.0462 1.0000
14.750 1.1168 0.10471 0.09943 -0.0253 0.0487 1.0000
15.000 1.0667 0.11754 0.11251 -0.0329 0.0517 1.0000
15.250 1.0349 0.12886 0.12393 -0.0399 0.0533 1.0000
15.500 1.0175 0.13820 0.13328 -0.0450 0.0545 1.0000
15.750 1.0127 0.14500 0.14007 -0.0476 0.0553 1.0000
16.000 0.7643 0.17819 0.17384 -0.0653 0.1187 1.0000
16.250 0.7632 0.18304 0.17868 -0.0674 0.1180 1.0000
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Polar data table (+)
Polar graphs
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