GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Reynolds number: 200,000 Max Cl/Cd: 72.01 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe275-il-200000.txt Download as CSV file: xf-goe275-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 275 (DAIMLER VI) 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3346 0.10189 0.09836 -0.0266 1.0000 0.0282
-8.250 -0.3434 0.10045 0.09700 -0.0268 1.0000 0.0282
-8.000 -0.3534 0.09887 0.09551 -0.0267 1.0000 0.0283
-7.750 -0.3527 0.09552 0.09221 -0.0255 1.0000 0.0284
-7.500 -0.3426 0.09140 0.08810 -0.0215 1.0000 0.0288
-7.250 -0.3452 0.08914 0.08589 -0.0195 1.0000 0.0291
-7.000 -0.3488 0.08699 0.08379 -0.0181 1.0000 0.0294
-6.750 -0.3527 0.08491 0.08176 -0.0170 1.0000 0.0297
-6.500 -0.3557 0.08274 0.07963 -0.0164 1.0000 0.0301
-6.250 -0.3569 0.08040 0.07733 -0.0162 1.0000 0.0306
-6.000 -0.3558 0.07787 0.07482 -0.0168 1.0000 0.0312
-5.750 -0.3519 0.07516 0.07212 -0.0179 1.0000 0.0318
-5.500 -0.3438 0.07219 0.06913 -0.0201 1.0000 0.0328
-5.250 -0.2878 0.06522 0.06192 -0.0365 0.9948 0.0344
-5.000 -0.2650 0.06152 0.05825 -0.0383 0.9900 0.0353
-4.750 -0.2278 0.05745 0.05410 -0.0444 0.9852 0.0367
-4.500 -0.1849 0.05311 0.04959 -0.0517 0.9789 0.0395
-4.250 -0.1319 0.04760 0.04370 -0.0610 0.9738 0.0419
-4.000 -0.1032 0.04455 0.04068 -0.0636 0.9673 0.0437
-3.500 -0.0163 0.03736 0.03291 -0.0733 0.9556 0.0517
-3.250 0.0163 0.03483 0.03035 -0.0758 0.9497 0.0545
-3.000 0.0644 0.03221 0.02721 -0.0801 0.9461 0.0625
-2.750 0.0913 0.02987 0.02496 -0.0813 0.9379 0.0663
-2.500 0.1348 0.02763 0.02236 -0.0846 0.9335 0.0766
-2.250 0.1728 0.02624 0.02068 -0.0866 0.9271 0.0895
-1.750 0.2506 0.02219 0.01659 -0.0924 0.9173 0.1235
-1.500 0.2810 0.02093 0.01533 -0.0934 0.9075 0.1554
-0.500 0.4299 0.01619 0.00954 -0.0967 0.8589 0.1497
-0.250 0.4660 0.01458 0.00759 -0.0960 0.8405 0.0970
0.000 0.4953 0.01406 0.00685 -0.0950 0.8159 0.0860
0.250 0.5240 0.01334 0.00594 -0.0941 0.7880 0.0767
0.500 0.5515 0.01310 0.00553 -0.0932 0.7529 0.0731
0.750 0.5773 0.01260 0.00488 -0.0921 0.7117 0.0708
1.000 0.6013 0.01241 0.00446 -0.0907 0.6673 0.0693
1.250 0.6239 0.01240 0.00421 -0.0892 0.6248 0.0687
1.500 0.6461 0.01247 0.00407 -0.0877 0.5855 0.0701
1.750 0.6685 0.01260 0.00400 -0.0864 0.5499 0.0722
2.000 0.6915 0.01274 0.00395 -0.0852 0.5199 0.0729
2.250 0.7151 0.01294 0.00394 -0.0842 0.4963 0.0739
2.500 0.7394 0.01309 0.00396 -0.0833 0.4765 0.0770
2.750 0.7639 0.01327 0.00403 -0.0825 0.4599 0.0850
3.000 0.7980 0.01178 0.00433 -0.0841 0.4450 1.0000
3.250 0.8224 0.01208 0.00445 -0.0832 0.4318 1.0000
3.750 0.8714 0.01266 0.00476 -0.0817 0.4075 1.0000
4.000 0.8961 0.01295 0.00498 -0.0811 0.3976 1.0000
4.250 0.9208 0.01330 0.00520 -0.0804 0.3890 1.0000
4.500 0.9458 0.01354 0.00546 -0.0798 0.3803 1.0000
4.750 0.9707 0.01392 0.00574 -0.0793 0.3728 1.0000
5.000 0.9954 0.01416 0.00603 -0.0786 0.3642 1.0000
5.250 1.0199 0.01453 0.00632 -0.0780 0.3560 1.0000
5.500 1.0440 0.01478 0.00662 -0.0773 0.3465 1.0000
5.750 1.0678 0.01510 0.00694 -0.0765 0.3369 1.0000
6.000 1.0914 0.01544 0.00724 -0.0758 0.3273 1.0000
6.250 1.1149 0.01569 0.00758 -0.0750 0.3176 1.0000
6.500 1.1382 0.01604 0.00792 -0.0742 0.3083 1.0000
6.750 1.1609 0.01630 0.00825 -0.0732 0.2975 1.0000
7.000 1.1833 0.01654 0.00857 -0.0722 0.2855 1.0000
7.250 1.2054 0.01680 0.00888 -0.0712 0.2732 1.0000
7.500 1.2272 0.01706 0.00920 -0.0701 0.2601 1.0000
7.750 1.2486 0.01734 0.00953 -0.0690 0.2464 1.0000
8.000 1.2697 0.01766 0.00988 -0.0679 0.2308 1.0000
8.250 1.2897 0.01806 0.01028 -0.0666 0.2135 1.0000
8.500 1.3073 0.01865 0.01081 -0.0650 0.1954 1.0000
8.750 1.3229 0.01949 0.01156 -0.0632 0.1776 1.0000
9.000 1.3375 0.02046 0.01248 -0.0612 0.1609 1.0000
9.250 1.3520 0.02142 0.01340 -0.0593 0.1474 1.0000
9.500 1.3670 0.02226 0.01422 -0.0575 0.1370 1.0000
9.750 1.3847 0.02285 0.01494 -0.0560 0.1279 1.0000
10.000 1.3992 0.02361 0.01570 -0.0541 0.1209 1.0000
10.250 1.4143 0.02423 0.01642 -0.0522 0.1147 1.0000
10.500 1.4251 0.02511 0.01727 -0.0498 0.1100 1.0000
10.750 1.4391 0.02578 0.01810 -0.0479 0.1045 1.0000
11.000 1.4478 0.02674 0.01905 -0.0454 0.0995 1.0000
11.250 1.4580 0.02770 0.02012 -0.0432 0.0949 1.0000
11.500 1.4662 0.02875 0.02126 -0.0409 0.0904 1.0000
11.750 1.4692 0.03031 0.02277 -0.0383 0.0861 1.0000
12.000 1.4778 0.03136 0.02408 -0.0363 0.0819 1.0000
12.250 1.4812 0.03283 0.02565 -0.0341 0.0772 1.0000
12.500 1.4814 0.03469 0.02759 -0.0319 0.0722 1.0000
12.750 1.4845 0.03619 0.02930 -0.0302 0.0650 1.0000
13.000 1.4844 0.03818 0.03144 -0.0287 0.0568 1.0000
13.250 1.4829 0.04046 0.03379 -0.0275 0.0487 1.0000
13.500 1.4784 0.04326 0.03662 -0.0266 0.0429 1.0000
13.750 1.4733 0.04640 0.03989 -0.0260 0.0391 1.0000
14.000 1.4668 0.04990 0.04349 -0.0260 0.0366 1.0000
14.250 1.4554 0.05424 0.04789 -0.0265 0.0350 1.0000
14.500 1.4470 0.05848 0.05227 -0.0273 0.0337 1.0000
14.750 1.4394 0.06281 0.05677 -0.0283 0.0323 1.0000
15.000 1.4308 0.06742 0.06151 -0.0297 0.0312 1.0000
15.250 1.4215 0.07232 0.06653 -0.0314 0.0301 1.0000
15.500 1.4110 0.07752 0.07183 -0.0333 0.0293 1.0000
15.750 1.4002 0.08277 0.07714 -0.0352 0.0286 1.0000
16.000 1.3912 0.08779 0.08225 -0.0369 0.0278 1.0000
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Polar data table (+)
Polar graphs
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