GOE 274 (DAIMLER V) AIRFOIL (goe274-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 274 (DAIMLER V) AIRFOIL (goe274-il) Reynolds number: 100,000 Max Cl/Cd: 56.98 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe274-il-100000-n5.txt Download as CSV file: xf-goe274-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 274 (DAIMLER V) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3266 0.10840 0.10354 -0.0274 1.0000 0.0387
-8.250 -0.3387 0.10752 0.10276 -0.0265 1.0000 0.0390
-8.000 -0.3506 0.10642 0.10176 -0.0257 1.0000 0.0391
-7.750 -0.3554 0.10452 0.09993 -0.0272 1.0000 0.0392
-7.500 -0.3562 0.10215 0.09760 -0.0291 1.0000 0.0393
-7.250 -0.3547 0.09892 0.09443 -0.0299 1.0000 0.0395
-7.000 -0.3532 0.09457 0.09011 -0.0245 1.0000 0.0401
-6.750 -0.3513 0.09158 0.08717 -0.0223 1.0000 0.0407
-6.500 -0.3496 0.08889 0.08452 -0.0215 1.0000 0.0414
-6.250 -0.3469 0.08624 0.08190 -0.0216 1.0000 0.0423
-6.000 -0.3413 0.08346 0.07914 -0.0225 0.9998 0.0438
-5.750 -0.2969 0.07843 0.07396 -0.0365 0.9941 0.0484
-5.500 -0.2461 0.07260 0.06785 -0.0512 0.9877 0.0494
-5.250 -0.2280 0.06813 0.06344 -0.0514 0.9834 0.0506
-5.000 -0.1982 0.06425 0.05950 -0.0554 0.9775 0.0527
-4.750 -0.1345 0.05971 0.05443 -0.0701 0.9711 0.0599
-4.500 -0.1138 0.05544 0.05030 -0.0711 0.9657 0.0617
-4.000 -0.0292 0.04830 0.04262 -0.0832 0.9535 0.0728
-3.750 0.0032 0.04504 0.03939 -0.0863 0.9495 0.0765
-3.500 0.0392 0.04244 0.03651 -0.0901 0.9421 0.0882
-3.250 0.0797 0.04010 0.03389 -0.0944 0.9369 0.1025
-3.000 0.1135 0.03745 0.03125 -0.0970 0.9320 0.1102
-2.750 0.1468 0.03533 0.02898 -0.0994 0.9241 0.1255
-2.500 0.1871 0.03303 0.02653 -0.1034 0.9196 0.1517
-2.000 0.2807 0.02835 0.02047 -0.1071 0.9056 0.0703
-1.750 0.3143 0.02612 0.01807 -0.1083 0.8964 0.0634
-1.500 0.3546 0.02467 0.01623 -0.1099 0.8891 0.0574
-1.250 0.3861 0.02337 0.01475 -0.1103 0.8771 0.0555
-1.000 0.4191 0.02223 0.01340 -0.1109 0.8649 0.0540
-0.750 0.4526 0.02120 0.01217 -0.1114 0.8513 0.0529
-0.500 0.4857 0.02034 0.01118 -0.1120 0.8360 0.0543
-0.250 0.5191 0.01955 0.01026 -0.1125 0.8187 0.0560
0.000 0.5529 0.01875 0.00934 -0.1131 0.7987 0.0559
0.250 0.5845 0.01808 0.00858 -0.1132 0.7736 0.0557
0.500 0.6163 0.01750 0.00789 -0.1134 0.7439 0.0557
0.750 0.6467 0.01706 0.00729 -0.1133 0.7082 0.0561
1.000 0.6754 0.01681 0.00684 -0.1130 0.6675 0.0566
1.250 0.7027 0.01674 0.00649 -0.1124 0.6254 0.0575
1.500 0.7289 0.01684 0.00627 -0.1118 0.5884 0.0595
1.750 0.7550 0.01692 0.00608 -0.1113 0.5575 0.0638
2.000 0.7810 0.01713 0.00603 -0.1108 0.5320 0.0670
2.250 0.8070 0.01736 0.00605 -0.1103 0.5108 0.0697
2.500 0.8333 0.01757 0.00612 -0.1099 0.4934 0.0745
2.750 0.8600 0.01773 0.00628 -0.1097 0.4790 0.0946
3.000 0.8774 0.01623 0.00647 -0.1075 0.4675 1.0000
3.250 0.9036 0.01658 0.00665 -0.1071 0.4554 1.0000
3.500 0.9296 0.01693 0.00686 -0.1068 0.4435 1.0000
3.750 0.9556 0.01725 0.00711 -0.1064 0.4313 1.0000
4.000 0.9813 0.01760 0.00738 -0.1061 0.4194 1.0000
4.250 1.0067 0.01796 0.00766 -0.1057 0.4078 1.0000
4.750 1.0570 0.01868 0.00832 -0.1048 0.3840 1.0000
5.000 1.0819 0.01905 0.00869 -0.1044 0.3723 1.0000
5.250 1.1066 0.01945 0.00906 -0.1039 0.3613 1.0000
5.500 1.1307 0.01987 0.00948 -0.1033 0.3502 1.0000
5.750 1.1549 0.02027 0.00991 -0.1027 0.3378 1.0000
6.000 1.1787 0.02071 0.01037 -0.1021 0.3257 1.0000
6.250 1.2020 0.02117 0.01086 -0.1014 0.3140 1.0000
6.500 1.2247 0.02167 0.01134 -0.1007 0.3029 1.0000
6.750 1.2475 0.02215 0.01189 -0.0999 0.2910 1.0000
7.000 1.2700 0.02267 0.01245 -0.0991 0.2798 1.0000
7.250 1.2919 0.02322 0.01305 -0.0983 0.2699 1.0000
7.500 1.3137 0.02379 0.01368 -0.0974 0.2612 1.0000
7.750 1.3353 0.02436 0.01435 -0.0965 0.2521 1.0000
8.000 1.3551 0.02494 0.01495 -0.0954 0.2402 1.0000
8.250 1.3737 0.02553 0.01560 -0.0941 0.2268 1.0000
8.750 1.4101 0.02685 0.01704 -0.0915 0.2046 1.0000
9.000 1.4267 0.02757 0.01782 -0.0900 0.1915 1.0000
9.250 1.4431 0.02832 0.01870 -0.0884 0.1805 1.0000
9.500 1.4574 0.02917 0.01960 -0.0866 0.1668 1.0000
9.750 1.4707 0.03006 0.02056 -0.0847 0.1499 1.0000
10.000 1.4845 0.03094 0.02155 -0.0828 0.1311 1.0000
10.250 1.4828 0.03273 0.02295 -0.0790 0.0850 1.0000
10.750 1.4696 0.03773 0.02763 -0.0712 0.0331 1.0000
11.000 1.4675 0.03998 0.03000 -0.0682 0.0297 1.0000
11.250 1.4644 0.04239 0.03258 -0.0655 0.0279 1.0000
11.500 1.4596 0.04507 0.03543 -0.0630 0.0267 1.0000
11.750 1.4564 0.04775 0.03835 -0.0611 0.0259 1.0000
12.000 1.4505 0.05086 0.04169 -0.0596 0.0252 1.0000
12.250 1.4425 0.05445 0.04551 -0.0586 0.0246 1.0000
12.500 1.4320 0.05862 0.04992 -0.0583 0.0241 1.0000
12.750 1.4192 0.06347 0.05499 -0.0587 0.0236 1.0000
13.000 1.4044 0.06906 0.06081 -0.0600 0.0233 1.0000
13.250 1.3878 0.07536 0.06734 -0.0620 0.0231 1.0000
13.500 1.3700 0.08228 0.07447 -0.0646 0.0230 1.0000
13.750 1.3514 0.08955 0.08194 -0.0675 0.0229 1.0000
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Polar data table (+)
Polar graphs
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