GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Reynolds number: 200,000 Max Cl/Cd: 73.78 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe277-il-200000-n5.txt Download as CSV file: xf-goe277-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 277 (DAIMLER VIII) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3434 0.09329 0.08997 -0.0290 1.0000 0.0240
-7.750 -0.3451 0.09041 0.08715 -0.0297 1.0000 0.0241
-7.500 -0.3451 0.08729 0.08406 -0.0301 1.0000 0.0240
-7.250 -0.3440 0.08423 0.08104 -0.0271 1.0000 0.0234
-7.000 -0.3453 0.08156 0.07841 -0.0258 1.0000 0.0226
-6.750 -0.3345 0.07750 0.07436 -0.0296 0.9972 0.0220
-6.500 -0.3080 0.07186 0.06868 -0.0381 0.9911 0.0216
-6.250 -0.2747 0.06560 0.06232 -0.0486 0.9854 0.0228
-6.000 -0.2340 0.05763 0.05415 -0.0612 0.9780 0.0239
-5.750 -0.2005 0.05063 0.04693 -0.0691 0.9721 0.0245
-5.500 -0.1749 0.04829 0.04456 -0.0718 0.9668 0.0256
-5.250 -0.1456 0.04632 0.04252 -0.0745 0.9601 0.0281
-5.000 -0.1094 0.04157 0.03751 -0.0797 0.9524 0.0297
-4.750 -0.0760 0.03676 0.03238 -0.0835 0.9425 0.0301
-4.500 -0.0379 0.03236 0.02747 -0.0866 0.9336 0.0326
-4.000 0.0222 0.02533 0.01957 -0.0896 0.9089 0.0345
-3.750 0.0497 0.02407 0.01821 -0.0902 0.8938 0.0363
-3.500 0.0782 0.02235 0.01621 -0.0905 0.8785 0.0372
-3.250 0.1069 0.02055 0.01404 -0.0905 0.8631 0.0375
-3.000 0.1350 0.01912 0.01229 -0.0904 0.8457 0.0379
-2.750 0.1629 0.01805 0.01094 -0.0902 0.8258 0.0389
-2.500 0.1906 0.01721 0.00984 -0.0899 0.8041 0.0405
-2.250 0.2182 0.01630 0.00862 -0.0895 0.7816 0.0407
-2.000 0.2455 0.01552 0.00755 -0.0890 0.7609 0.0409
-1.750 0.2727 0.01489 0.00668 -0.0886 0.7416 0.0413
-1.500 0.2998 0.01437 0.00597 -0.0881 0.7228 0.0418
-1.250 0.3267 0.01394 0.00536 -0.0877 0.7045 0.0425
-1.000 0.3535 0.01359 0.00487 -0.0873 0.6862 0.0432
-0.750 0.3804 0.01329 0.00447 -0.0870 0.6675 0.0441
-0.500 0.4073 0.01315 0.00423 -0.0867 0.6483 0.0456
-0.250 0.4340 0.01286 0.00386 -0.0864 0.6286 0.0468
0.000 0.4607 0.01261 0.00353 -0.0861 0.6074 0.0476
0.250 0.4873 0.01248 0.00328 -0.0858 0.5851 0.0487
0.500 0.5139 0.01243 0.00311 -0.0855 0.5632 0.0503
0.750 0.5405 0.01244 0.00298 -0.0852 0.5423 0.0527
1.000 0.5671 0.01248 0.00290 -0.0849 0.5236 0.0563
1.250 0.5938 0.01252 0.00286 -0.0846 0.5064 0.0647
1.750 0.6432 0.01066 0.00301 -0.0834 0.4744 1.0000
2.000 0.6697 0.01087 0.00308 -0.0832 0.4583 1.0000
2.250 0.6963 0.01109 0.00316 -0.0829 0.4429 1.0000
2.500 0.7227 0.01132 0.00328 -0.0827 0.4288 1.0000
2.750 0.7492 0.01156 0.00341 -0.0824 0.4166 1.0000
3.000 0.7757 0.01178 0.00355 -0.0822 0.4056 1.0000
3.250 0.8022 0.01202 0.00373 -0.0820 0.3960 1.0000
3.500 0.8285 0.01228 0.00391 -0.0817 0.3876 1.0000
3.750 0.8550 0.01251 0.00412 -0.0815 0.3794 1.0000
4.000 0.8811 0.01279 0.00435 -0.0813 0.3723 1.0000
4.250 0.9075 0.01303 0.00458 -0.0811 0.3648 1.0000
4.500 0.9334 0.01333 0.00483 -0.0808 0.3580 1.0000
4.750 0.9597 0.01357 0.00510 -0.0806 0.3510 1.0000
5.000 0.9855 0.01388 0.00539 -0.0803 0.3449 1.0000
5.250 1.0117 0.01414 0.00569 -0.0801 0.3387 1.0000
5.500 1.0374 0.01443 0.00599 -0.0798 0.3321 1.0000
5.750 1.0630 0.01473 0.00633 -0.0795 0.3261 1.0000
6.000 1.0890 0.01500 0.00667 -0.0793 0.3206 1.0000
6.250 1.1142 0.01533 0.00702 -0.0789 0.3149 1.0000
6.500 1.1398 0.01559 0.00738 -0.0786 0.3076 1.0000
6.750 1.1641 0.01590 0.00772 -0.0782 0.2969 1.0000
7.000 1.1883 0.01617 0.00804 -0.0777 0.2820 1.0000
7.250 1.2126 0.01645 0.00837 -0.0772 0.2661 1.0000
7.500 1.2366 0.01676 0.00874 -0.0767 0.2490 1.0000
7.750 1.2595 0.01717 0.00916 -0.0761 0.2244 1.0000
8.000 1.2769 0.01811 0.00977 -0.0749 0.1636 1.0000
8.250 1.2891 0.01973 0.01098 -0.0731 0.1059 1.0000
8.500 1.3044 0.02096 0.01207 -0.0716 0.0788 1.0000
8.750 1.3119 0.02285 0.01359 -0.0692 0.0267 1.0000
9.000 1.3253 0.02405 0.01486 -0.0673 0.0209 1.0000
9.250 1.3402 0.02505 0.01600 -0.0656 0.0190 1.0000
9.500 1.3526 0.02618 0.01728 -0.0636 0.0173 1.0000
9.750 1.3608 0.02752 0.01875 -0.0611 0.0158 1.0000
10.000 1.3640 0.02899 0.02038 -0.0580 0.0147 1.0000
10.250 1.3704 0.03030 0.02186 -0.0555 0.0141 1.0000
10.500 1.3744 0.03186 0.02357 -0.0530 0.0137 1.0000
10.750 1.3764 0.03366 0.02553 -0.0508 0.0132 1.0000
11.000 1.3767 0.03573 0.02779 -0.0488 0.0128 1.0000
11.250 1.3757 0.03808 0.03029 -0.0471 0.0125 1.0000
11.500 1.3738 0.04072 0.03307 -0.0459 0.0121 1.0000
11.750 1.3712 0.04365 0.03614 -0.0452 0.0118 1.0000
12.000 1.3678 0.04687 0.03949 -0.0449 0.0114 1.0000
12.250 1.3633 0.05039 0.04313 -0.0449 0.0111 1.0000
12.500 1.3570 0.05425 0.04710 -0.0451 0.0108 1.0000
12.750 1.3492 0.05838 0.05134 -0.0454 0.0105 1.0000
13.000 1.3403 0.06261 0.05566 -0.0456 0.0103 1.0000
13.250 1.3375 0.06623 0.05940 -0.0459 0.0101 1.0000
13.500 1.3351 0.06983 0.06312 -0.0463 0.0099 1.0000
13.750 1.3326 0.07344 0.06686 -0.0466 0.0098 1.0000
14.000 1.3302 0.07710 0.07065 -0.0470 0.0096 1.0000
14.250 1.3279 0.08080 0.07449 -0.0474 0.0095 1.0000
14.500 1.3254 0.08456 0.07839 -0.0479 0.0093 1.0000
14.750 1.3228 0.08840 0.08239 -0.0485 0.0092 1.0000
15.000 1.3200 0.09237 0.08650 -0.0493 0.0091 1.0000
15.250 1.3164 0.09654 0.09082 -0.0502 0.0089 1.0000
15.500 1.3122 0.10089 0.09533 -0.0514 0.0088 1.0000
15.750 1.3071 0.10554 0.10013 -0.0529 0.0087 1.0000
16.000 1.3012 0.11044 0.10520 -0.0547 0.0086 1.0000
16.250 1.2947 0.11561 0.11053 -0.0568 0.0085 1.0000
16.500 1.2875 0.12104 0.11612 -0.0593 0.0085 1.0000
16.750 1.2797 0.12672 0.12196 -0.0621 0.0083 1.0000
17.000 1.2716 0.13262 0.12802 -0.0652 0.0083 1.0000
17.250 1.2634 0.13873 0.13428 -0.0686 0.0082 1.0000
17.500 1.2542 0.14526 0.14097 -0.0723 0.0081 1.0000
17.750 1.2454 0.15191 0.14777 -0.0763 0.0080 1.0000
18.000 1.2350 0.15922 0.15525 -0.0809 0.0080 1.0000
18.250 1.2248 0.16677 0.16294 -0.0857 0.0080 1.0000
18.500 1.2101 0.17618 0.17254 -0.0919 0.0081 1.0000
18.750 1.1917 0.18765 0.18420 -0.0994 0.0083 1.0000
19.000 1.1650 0.20382 0.20056 -0.1096 0.0087 1.0000
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