GOE 274 (DAIMLER V) AIRFOIL (goe274-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 274 (DAIMLER V) AIRFOIL (goe274-il) Reynolds number: 200,000 Max Cl/Cd: 73.18 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe274-il-200000-n5.txt Download as CSV file: xf-goe274-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3381 0.10593 0.10253 -0.0259 1.0000 0.0244
-8.250 -0.3486 0.10437 0.10103 -0.0241 1.0000 0.0244
-8.000 -0.3607 0.10290 0.09962 -0.0220 1.0000 0.0244
-7.750 -0.3477 0.09868 0.09541 -0.0277 0.9969 0.0245
-7.500 -0.3265 0.09369 0.09040 -0.0356 0.9933 0.0245
-7.250 -0.3164 0.08937 0.08609 -0.0337 0.9914 0.0248
-7.000 -0.2996 0.08584 0.08256 -0.0344 0.9887 0.0256
-6.750 -0.2747 0.08184 0.07854 -0.0400 0.9853 0.0268
-6.500 -0.2502 0.07760 0.07427 -0.0465 0.9793 0.0283
-6.250 -0.2034 0.07195 0.06848 -0.0621 0.9747 0.0304
-6.000 -0.1646 0.06687 0.06322 -0.0728 0.9678 0.0307
-5.750 -0.1326 0.06118 0.05741 -0.0796 0.9644 0.0311
-5.500 -0.1116 0.05727 0.05351 -0.0815 0.9619 0.0317
-5.250 -0.0902 0.05420 0.05041 -0.0833 0.9554 0.0323
-5.000 -0.0572 0.05070 0.04682 -0.0880 0.9519 0.0334
-4.750 -0.0183 0.04700 0.04298 -0.0937 0.9494 0.0351
-4.500 0.0323 0.04420 0.03958 -0.1001 0.9423 0.0392
-4.250 0.0692 0.04118 0.03626 -0.1035 0.9375 0.0394
-4.000 0.0984 0.03624 0.03138 -0.1070 0.9340 0.0403
-3.750 0.1225 0.03398 0.02907 -0.1079 0.9250 0.0412
-3.500 0.1557 0.03177 0.02672 -0.1102 0.9200 0.0429
-3.250 0.1942 0.03140 0.02575 -0.1113 0.9121 0.0491
-3.000 0.2257 0.02798 0.02221 -0.1134 0.9056 0.0500
-2.750 0.2538 0.02585 0.02006 -0.1145 0.8967 0.0512
-2.500 0.2866 0.02422 0.01829 -0.1160 0.8889 0.0532
-2.250 0.3172 0.02291 0.01679 -0.1166 0.8777 0.0558
-2.000 0.3495 0.02154 0.01513 -0.1175 0.8662 0.0622
-1.500 0.4150 0.01861 0.01165 -0.1181 0.8379 0.0454
-1.250 0.4481 0.01778 0.01031 -0.1179 0.8199 0.0398
-1.000 0.4779 0.01695 0.00931 -0.1180 0.7960 0.0388
-0.750 0.5069 0.01611 0.00823 -0.1179 0.7632 0.0385
-0.500 0.5345 0.01557 0.00739 -0.1174 0.7220 0.0383
-0.250 0.5606 0.01524 0.00672 -0.1167 0.6706 0.0384
0.000 0.5854 0.01510 0.00622 -0.1158 0.6156 0.0386
0.250 0.6102 0.01505 0.00585 -0.1150 0.5719 0.0399
0.500 0.6354 0.01477 0.00541 -0.1145 0.5414 0.0412
0.750 0.6612 0.01468 0.00516 -0.1141 0.5181 0.0413
1.000 0.6876 0.01458 0.00497 -0.1138 0.4993 0.0414
1.250 0.7141 0.01451 0.00483 -0.1136 0.4825 0.0417
1.500 0.7408 0.01447 0.00472 -0.1134 0.4663 0.0421
1.750 0.7677 0.01445 0.00466 -0.1133 0.4522 0.0428
2.000 0.7946 0.01448 0.00463 -0.1132 0.4398 0.0438
2.250 0.8215 0.01455 0.00462 -0.1131 0.4280 0.0452
2.500 0.8485 0.01463 0.00465 -0.1130 0.4166 0.0482
2.750 0.8753 0.01472 0.00468 -0.1128 0.4062 0.0515
3.250 0.9286 0.01499 0.00486 -0.1124 0.3855 0.0581
3.500 0.9536 0.01395 0.00521 -0.1124 0.3748 0.7305
3.750 0.9713 0.01370 0.00523 -0.1098 0.3642 1.0000
4.000 0.9973 0.01395 0.00540 -0.1095 0.3518 1.0000
4.250 1.0232 0.01421 0.00560 -0.1092 0.3395 1.0000
4.500 1.0489 0.01449 0.00583 -0.1089 0.3277 1.0000
4.750 1.0742 0.01479 0.00607 -0.1085 0.3166 1.0000
5.000 1.0996 0.01509 0.00633 -0.1082 0.3052 1.0000
5.250 1.1249 0.01539 0.00662 -0.1078 0.2939 1.0000
5.500 1.1497 0.01571 0.00693 -0.1074 0.2826 1.0000
5.750 1.1742 0.01607 0.00725 -0.1069 0.2702 1.0000
6.000 1.1982 0.01646 0.00760 -0.1064 0.2573 1.0000
6.250 1.2220 0.01686 0.00799 -0.1058 0.2453 1.0000
6.500 1.2459 0.01725 0.00838 -0.1052 0.2347 1.0000
6.750 1.2689 0.01769 0.00880 -0.1046 0.2227 1.0000
7.000 1.2913 0.01819 0.00926 -0.1038 0.2092 1.0000
7.250 1.3133 0.01870 0.00974 -0.1030 0.1971 1.0000
7.500 1.3348 0.01925 0.01026 -0.1021 0.1875 1.0000
7.750 1.3571 0.01971 0.01077 -0.1014 0.1791 1.0000
8.000 1.3780 0.02026 0.01135 -0.1004 0.1697 1.0000
8.250 1.3979 0.02089 0.01195 -0.0993 0.1566 1.0000
8.500 1.4183 0.02146 0.01254 -0.0983 0.1437 1.0000
8.750 1.4377 0.02210 0.01314 -0.0971 0.1150 1.0000
9.000 1.4436 0.02394 0.01454 -0.0942 0.0685 1.0000
9.250 1.4461 0.02595 0.01629 -0.0906 0.0252 1.0000
9.500 1.4569 0.02708 0.01751 -0.0881 0.0217 1.0000
9.750 1.4664 0.02812 0.01869 -0.0853 0.0200 1.0000
10.000 1.4764 0.02917 0.01989 -0.0827 0.0188 1.0000
10.250 1.4848 0.03036 0.02124 -0.0801 0.0176 1.0000
10.500 1.4909 0.03175 0.02281 -0.0774 0.0165 1.0000
10.750 1.4937 0.03341 0.02464 -0.0745 0.0157 1.0000
11.000 1.4928 0.03543 0.02686 -0.0714 0.0151 1.0000
11.250 1.4954 0.03723 0.02882 -0.0690 0.0147 1.0000
11.500 1.4963 0.03926 0.03102 -0.0667 0.0144 1.0000
11.750 1.4951 0.04159 0.03353 -0.0647 0.0141 1.0000
12.000 1.4920 0.04427 0.03639 -0.0629 0.0138 1.0000
12.250 1.4871 0.04732 0.03960 -0.0616 0.0135 1.0000
12.500 1.4811 0.05074 0.04320 -0.0608 0.0132 1.0000
12.750 1.4736 0.05461 0.04724 -0.0604 0.0129 1.0000
13.000 1.4649 0.05892 0.05172 -0.0607 0.0127 1.0000
13.250 1.4554 0.06367 0.05663 -0.0615 0.0124 1.0000
13.500 1.4450 0.06880 0.06191 -0.0627 0.0122 1.0000
13.750 1.4341 0.07423 0.06748 -0.0642 0.0120 1.0000
14.000 1.4227 0.07983 0.07322 -0.0659 0.0119 1.0000
14.250 1.4113 0.08544 0.07895 -0.0677 0.0117 1.0000
14.500 1.4000 0.09101 0.08463 -0.0693 0.0115 1.0000
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Polar data table (+)
Polar graphs
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