GOE 274 (DAIMLER V) AIRFOIL (goe274-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 274 (DAIMLER V) AIRFOIL (goe274-il) Reynolds number: 200,000 Max Cl/Cd: 73.2 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe274-il-200000.txt Download as CSV file: xf-goe274-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3392 0.10409 0.10068 -0.0244 1.0000 0.0305
-8.000 -0.3546 0.10327 0.09994 -0.0223 1.0000 0.0305
-7.750 -0.3655 0.10189 0.09863 -0.0224 1.0000 0.0306
-7.500 -0.3695 0.09979 0.09657 -0.0246 1.0000 0.0307
-7.000 -0.3694 0.09301 0.08987 -0.0236 1.0000 0.0310
-6.750 -0.3687 0.08991 0.08681 -0.0200 1.0000 0.0313
-6.500 -0.3674 0.08723 0.08415 -0.0184 1.0000 0.0317
-6.250 -0.3653 0.08463 0.08156 -0.0180 1.0000 0.0321
-6.000 -0.3614 0.08200 0.07896 -0.0183 1.0000 0.0328
-5.750 -0.3525 0.07905 0.07601 -0.0201 0.9997 0.0338
-5.500 -0.3115 0.07389 0.07076 -0.0303 0.9953 0.0357
-5.250 -0.2306 0.06715 0.06355 -0.0533 0.9890 0.0377
-5.000 -0.2123 0.06198 0.05850 -0.0544 0.9856 0.0383
-4.750 -0.1831 0.05831 0.05481 -0.0578 0.9819 0.0394
-4.500 -0.1491 0.05480 0.05121 -0.0626 0.9767 0.0416
-4.250 -0.0749 0.05156 0.04726 -0.0752 0.9728 0.0460
-4.000 -0.0440 0.04571 0.04151 -0.0796 0.9707 0.0470
-3.750 -0.0174 0.04283 0.03863 -0.0816 0.9642 0.0484
-3.500 0.0233 0.03997 0.03564 -0.0861 0.9604 0.0513
-3.250 0.0781 0.03680 0.03195 -0.0924 0.9579 0.0575
-3.000 0.1093 0.03419 0.02936 -0.0948 0.9521 0.0597
-2.750 0.1583 0.03437 0.02897 -0.0980 0.9469 0.0682
-2.500 0.1969 0.02950 0.02421 -0.1027 0.9444 0.0718
-2.250 0.2461 0.02779 0.02214 -0.1073 0.9423 0.0839
-2.000 0.2763 0.02594 0.02036 -0.1086 0.9339 0.0907
-1.750 0.3227 0.02432 0.01850 -0.1128 0.9306 0.1146
-1.500 0.3666 0.02241 0.01658 -0.1167 0.9277 0.1351
-0.750 0.4675 0.01791 0.01208 -0.1211 0.9001 0.2538
-0.500 0.5005 0.01687 0.01095 -0.1214 0.8857 0.2811
-0.250 0.5449 0.01634 0.00950 -0.1196 0.8701 0.1251
0.000 0.5775 0.01529 0.00818 -0.1187 0.8492 0.0946
0.250 0.6087 0.01459 0.00725 -0.1180 0.8234 0.0812
0.500 0.6373 0.01366 0.00621 -0.1173 0.7889 0.0757
0.750 0.6650 0.01328 0.00557 -0.1164 0.7441 0.0712
1.000 0.6907 0.01323 0.00522 -0.1153 0.6895 0.0694
1.250 0.7152 0.01328 0.00497 -0.1142 0.6346 0.0688
1.500 0.7399 0.01327 0.00471 -0.1134 0.5926 0.0700
1.750 0.7655 0.01335 0.00460 -0.1130 0.5632 0.0738
2.000 0.7918 0.01352 0.00459 -0.1126 0.5402 0.0752
2.250 0.8181 0.01373 0.00462 -0.1122 0.5215 0.0775
2.500 0.8446 0.01394 0.00469 -0.1119 0.5052 0.0816
2.750 0.8715 0.01408 0.00486 -0.1117 0.4906 0.1103
3.000 0.8879 0.01261 0.00504 -0.1092 0.4789 1.0000
3.250 0.9144 0.01293 0.00520 -0.1089 0.4663 1.0000
3.500 0.9407 0.01326 0.00537 -0.1085 0.4543 1.0000
3.750 0.9670 0.01353 0.00558 -0.1083 0.4416 1.0000
4.000 0.9930 0.01380 0.00579 -0.1080 0.4287 1.0000
4.250 1.0189 0.01409 0.00601 -0.1076 0.4157 1.0000
4.500 1.0445 0.01438 0.00626 -0.1072 0.4029 1.0000
4.750 1.0698 0.01469 0.00650 -0.1068 0.3900 1.0000
5.000 1.0949 0.01502 0.00676 -0.1064 0.3773 1.0000
5.250 1.1200 0.01531 0.00705 -0.1059 0.3638 1.0000
5.500 1.1448 0.01564 0.00737 -0.1054 0.3496 1.0000
5.750 1.1690 0.01599 0.00769 -0.1049 0.3347 1.0000
6.000 1.1929 0.01637 0.00804 -0.1042 0.3195 1.0000
6.250 1.2167 0.01678 0.00842 -0.1036 0.3054 1.0000
6.500 1.2404 0.01721 0.00885 -0.1030 0.2922 1.0000
6.750 1.2636 0.01763 0.00925 -0.1023 0.2790 1.0000
7.000 1.2865 0.01804 0.00965 -0.1016 0.2664 1.0000
7.250 1.3090 0.01849 0.01008 -0.1008 0.2552 1.0000
7.500 1.3317 0.01892 0.01053 -0.1000 0.2448 1.0000
7.750 1.3544 0.01933 0.01100 -0.0993 0.2348 1.0000
8.000 1.3761 0.01980 0.01147 -0.0984 0.2245 1.0000
8.250 1.3966 0.02030 0.01197 -0.0974 0.2137 1.0000
8.500 1.4178 0.02073 0.01247 -0.0965 0.2016 1.0000
8.750 1.4376 0.02124 0.01299 -0.0953 0.1875 1.0000
9.000 1.4564 0.02182 0.01358 -0.0941 0.1724 1.0000
9.250 1.4756 0.02239 0.01417 -0.0928 0.1541 1.0000
9.500 1.4937 0.02309 0.01480 -0.0914 0.1180 1.0000
9.750 1.4956 0.02513 0.01634 -0.0878 0.0615 1.0000
10.000 1.4957 0.02712 0.01810 -0.0838 0.0365 1.0000
10.250 1.5016 0.02846 0.01952 -0.0805 0.0329 1.0000
10.500 1.5089 0.02973 0.02097 -0.0776 0.0312 1.0000
10.750 1.5140 0.03118 0.02260 -0.0745 0.0300 1.0000
11.000 1.5161 0.03287 0.02448 -0.0714 0.0289 1.0000
11.250 1.5144 0.03489 0.02667 -0.0681 0.0280 1.0000
11.500 1.5086 0.03733 0.02927 -0.0650 0.0272 1.0000
11.750 1.4990 0.04027 0.03237 -0.0620 0.0265 1.0000
12.000 1.4969 0.04277 0.03502 -0.0601 0.0260 1.0000
12.250 1.4928 0.04565 0.03806 -0.0584 0.0256 1.0000
12.500 1.4872 0.04889 0.04145 -0.0572 0.0252 1.0000
12.750 1.4809 0.05243 0.04513 -0.0564 0.0250 1.0000
13.000 1.4743 0.05620 0.04904 -0.0560 0.0247 1.0000
13.250 1.4679 0.06011 0.05309 -0.0558 0.0245 1.0000
13.500 1.4623 0.06404 0.05714 -0.0558 0.0242 1.0000
13.750 1.4574 0.06791 0.06113 -0.0559 0.0240 1.0000
14.000 1.4540 0.07162 0.06494 -0.0558 0.0238 1.0000
14.250 1.4519 0.07514 0.06856 -0.0557 0.0236 1.0000
14.500 1.4512 0.07844 0.07195 -0.0555 0.0234 1.0000
14.750 1.4517 0.08155 0.07515 -0.0551 0.0232 1.0000
15.000 1.4530 0.08458 0.07828 -0.0547 0.0229 1.0000
15.250 1.4541 0.08769 0.08148 -0.0544 0.0226 1.0000
15.500 1.4553 0.09078 0.08466 -0.0541 0.0222 1.0000
15.750 1.4576 0.09367 0.08762 -0.0536 0.0217 1.0000
16.000 1.4614 0.09641 0.09044 -0.0526 0.0214 1.0000
16.250 1.4602 0.10020 0.09439 -0.0530 0.0213 1.0000
16.500 1.4559 0.10464 0.09902 -0.0543 0.0214 1.0000
16.750 1.4492 0.10954 0.10412 -0.0561 0.0214 1.0000
17.000 1.4404 0.11496 0.10975 -0.0587 0.0215 1.0000
17.250 1.4298 0.12091 0.11593 -0.0618 0.0217 1.0000
17.500 1.4175 0.12743 0.12268 -0.0656 0.0219 1.0000
17.750 1.4037 0.13453 0.13003 -0.0700 0.0221 1.0000
18.000 1.3852 0.14306 0.13884 -0.0758 0.0225 1.0000
18.250 1.3648 0.15247 0.14850 -0.0825 0.0228 1.0000
18.500 1.3432 0.16275 0.15903 -0.0900 0.0232 1.0000
18.750 1.3197 0.17427 0.17078 -0.0985 0.0237 1.0000
19.000 1.2924 0.18790 0.18462 -0.1085 0.0243 1.0000
19.250 1.2571 0.20580 0.20268 -0.1212 0.0253 1.0000
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Polar data table (+)
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