GOE 448 AIRFOIL (goe448-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 448 AIRFOIL (goe448-il) Reynolds number: 500,000 Max Cl/Cd: 119.35 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe448-il-500000.txt Download as CSV file: xf-goe448-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 448 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.2146 0.09771 0.09432 -0.1345 0.7879 0.0276
-9.750 0.2162 0.09503 0.09159 -0.1383 0.7834 0.0288
-9.500 0.2254 0.09181 0.08835 -0.1393 0.7794 0.0290
-9.250 0.2388 0.08942 0.08596 -0.1394 0.7749 0.0293
-9.000 0.2509 0.08741 0.08393 -0.1402 0.7706 0.0298
-8.750 0.2624 0.08541 0.08188 -0.1412 0.7666 0.0305
-8.500 0.2734 0.08325 0.07971 -0.1426 0.7625 0.0317
-8.250 0.2722 0.08079 0.07728 -0.1484 0.7573 0.0336
-8.000 0.2869 0.07754 0.07400 -0.1477 0.7536 0.0339
-7.750 0.3008 0.07554 0.07194 -0.1479 0.7498 0.0343
-7.500 0.3136 0.07368 0.07009 -0.1488 0.7457 0.0349
-7.250 0.3255 0.07178 0.06820 -0.1499 0.7415 0.0359
-7.000 0.3350 0.06986 0.06626 -0.1513 0.7374 0.0375
-6.750 0.3486 0.06616 0.06249 -0.1601 0.7333 0.0391
-6.500 0.3629 0.06418 0.06053 -0.1594 0.7295 0.0395
-6.250 0.3793 0.06238 0.05872 -0.1604 0.7254 0.0401
-6.000 0.3973 0.06048 0.05680 -0.1626 0.7216 0.0410
-5.750 0.4399 0.05620 0.05238 -0.1798 0.7177 0.0446
-5.500 0.4508 0.05369 0.04989 -0.1783 0.7142 0.0450
-5.250 0.4671 0.05201 0.04821 -0.1780 0.7103 0.0454
-5.000 0.4874 0.05033 0.04650 -0.1793 0.7065 0.0461
-4.750 0.5116 0.04848 0.04458 -0.1821 0.7030 0.0473
-4.500 0.5722 0.04282 0.03871 -0.1998 0.6996 0.0511
-4.250 0.5883 0.04106 0.03697 -0.1992 0.6959 0.0516
-4.000 0.6092 0.03967 0.03556 -0.1997 0.6922 0.0520
-3.750 0.6342 0.03820 0.03404 -0.2012 0.6886 0.0528
-3.500 0.6643 0.03651 0.03223 -0.2042 0.6852 0.0542
-3.250 0.7270 0.02769 0.02301 -0.2191 0.6822 0.0517
-3.000 0.7546 0.02641 0.02168 -0.2205 0.6786 0.0522
-2.750 0.7760 0.02756 0.02287 -0.2191 0.6749 0.0566
-2.500 0.8328 0.01699 0.01110 -0.2300 0.6723 0.0592
-2.250 0.8603 0.01726 0.01140 -0.2302 0.6688 0.0603
-2.000 0.8865 0.01710 0.01124 -0.2302 0.6654 0.0627
-1.750 0.9156 0.01608 0.00990 -0.2309 0.6618 0.0679
-1.500 0.9419 0.01612 0.01002 -0.2309 0.6583 0.0699
-1.250 0.9709 0.01573 0.00942 -0.2314 0.6550 0.0736
-1.000 0.9992 0.01523 0.00876 -0.2320 0.6516 0.0781
-0.750 1.0245 0.01524 0.00886 -0.2318 0.6480 0.0816
-0.500 1.0519 0.01491 0.00839 -0.2319 0.6443 0.0843
-0.250 1.0729 0.01655 0.01043 -0.2314 0.6403 0.1152
0.000 1.0995 0.01640 0.01026 -0.2316 0.6361 0.1191
0.250 1.1324 0.01380 0.00696 -0.2322 0.6317 0.0906
0.500 1.1582 0.01352 0.00661 -0.2320 0.6270 0.0909
0.750 1.1854 0.01338 0.00638 -0.2320 0.6230 0.0920
1.000 1.2123 0.01327 0.00622 -0.2321 0.6195 0.0928
1.250 1.2374 0.01313 0.00608 -0.2318 0.6157 0.0930
1.500 1.2629 0.01303 0.00596 -0.2315 0.6118 0.0933
1.750 1.2892 0.01298 0.00586 -0.2314 0.6081 0.0938
2.000 1.3165 0.01299 0.00582 -0.2316 0.6046 0.0945
2.250 1.3404 0.01297 0.00584 -0.2311 0.6010 0.0957
2.500 1.3649 0.01297 0.00586 -0.2306 0.5971 0.0965
2.750 1.3899 0.01299 0.00587 -0.2303 0.5933 0.0970
3.000 1.4167 0.01307 0.00590 -0.2304 0.5895 0.0976
3.250 1.4391 0.01312 0.00601 -0.2296 0.5856 0.0982
3.500 1.4614 0.01319 0.00611 -0.2288 0.5810 0.0987
3.750 1.4845 0.01326 0.00617 -0.2281 0.5763 0.0999
4.000 1.5075 0.01338 0.00629 -0.2275 0.5717 0.1015
4.250 1.5259 0.01348 0.00645 -0.2259 0.5666 0.1040
4.500 1.5448 0.01362 0.00661 -0.2244 0.5620 0.1071
4.750 1.5673 0.01381 0.00677 -0.2237 0.5578 0.1105
5.000 1.5865 0.01399 0.00704 -0.2224 0.5535 0.1175
5.250 1.6065 0.01417 0.00735 -0.2213 0.5488 0.1658
5.500 1.6272 0.01437 0.00766 -0.2204 0.5442 0.2369
5.750 1.6470 0.01380 0.00815 -0.2195 0.5397 1.0000
6.000 1.6645 0.01411 0.00848 -0.2179 0.5345 1.0000
6.250 1.6813 0.01447 0.00880 -0.2163 0.5286 1.0000
6.500 1.6969 0.01487 0.00921 -0.2144 0.5219 1.0000
6.750 1.7105 0.01534 0.00968 -0.2123 0.5139 1.0000
7.000 1.7246 0.01586 0.01018 -0.2104 0.5065 1.0000
7.250 1.7379 0.01642 0.01074 -0.2084 0.4983 1.0000
7.500 1.7511 0.01704 0.01135 -0.2064 0.4908 1.0000
7.750 1.7636 0.01771 0.01203 -0.2044 0.4822 1.0000
8.000 1.7740 0.01852 0.01283 -0.2021 0.4724 1.0000
8.500 1.7922 0.02040 0.01469 -0.1974 0.4515 1.0000
8.750 1.8002 0.02148 0.01575 -0.1950 0.4410 1.0000
9.000 1.8049 0.02279 0.01702 -0.1923 0.4294 1.0000
9.250 1.8087 0.02422 0.01842 -0.1895 0.4163 1.0000
9.500 1.8111 0.02582 0.01999 -0.1867 0.4018 1.0000
9.750 1.8117 0.02763 0.02175 -0.1838 0.3869 1.0000
10.000 1.8099 0.02968 0.02376 -0.1808 0.3713 1.0000
10.250 1.8070 0.03191 0.02593 -0.1778 0.3554 1.0000
10.500 1.8040 0.03423 0.02820 -0.1749 0.3401 1.0000
10.750 1.7991 0.03679 0.03070 -0.1720 0.3240 1.0000
11.000 1.7916 0.03966 0.03350 -0.1690 0.3065 1.0000
11.250 1.7835 0.04268 0.03644 -0.1661 0.2866 1.0000
11.500 1.7696 0.04632 0.03995 -0.1628 0.2610 1.0000
11.750 1.7479 0.05083 0.04428 -0.1592 0.2260 1.0000
12.000 1.7180 0.05630 0.04952 -0.1552 0.1852 1.0000
12.250 1.6945 0.06127 0.05435 -0.1520 0.1596 1.0000
12.500 1.6815 0.06532 0.05834 -0.1496 0.1412 1.0000
12.750 1.6657 0.06978 0.06268 -0.1473 0.1161 1.0000
13.000 1.6353 0.07598 0.06865 -0.1445 0.0759 1.0000
13.250 1.6073 0.08217 0.07470 -0.1421 0.0398 1.0000
13.500 1.5924 0.08693 0.07943 -0.1406 0.0224 1.0000
13.750 1.5910 0.09011 0.08268 -0.1396 0.0202 1.0000
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Polar data table (+)
Polar graphs
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