GOE 585 AIRFOIL (goe585-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 585 AIRFOIL (goe585-il) Reynolds number: 100,000 Max Cl/Cd: 51 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe585-il-100000-n5.txt Download as CSV file: xf-goe585-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 585 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4026 0.09436 0.08925 -0.0305 1.0000 0.0427
-8.500 -0.3996 0.09120 0.08614 -0.0299 1.0000 0.0420
-8.250 -0.4025 0.08804 0.08304 -0.0303 1.0000 0.0419
-8.000 -0.4092 0.08501 0.08010 -0.0305 1.0000 0.0419
-7.750 -0.4157 0.08162 0.07679 -0.0314 1.0000 0.0421
-7.500 -0.4198 0.07771 0.07294 -0.0333 1.0000 0.0422
-7.250 -0.4215 0.07393 0.06920 -0.0346 1.0000 0.0421
-7.000 -0.4223 0.07004 0.06532 -0.0357 1.0000 0.0419
-6.750 -0.4219 0.06602 0.06129 -0.0368 1.0000 0.0416
-6.500 -0.4202 0.06153 0.05675 -0.0381 1.0000 0.0415
-6.250 -0.4165 0.05640 0.05150 -0.0399 1.0000 0.0417
-6.000 -0.4105 0.04940 0.04416 -0.0426 1.0000 0.0427
-5.750 -0.4021 0.04308 0.03732 -0.0440 1.0000 0.0433
-5.500 -0.3912 0.03898 0.03292 -0.0438 1.0000 0.0437
-5.250 -0.3654 0.03567 0.02931 -0.0458 0.9965 0.0448
-5.000 -0.3339 0.03429 0.02782 -0.0479 0.9917 0.0472
-4.750 -0.3018 0.03109 0.02410 -0.0502 0.9868 0.0491
-4.500 -0.2706 0.02802 0.02044 -0.0518 0.9818 0.0500
-4.250 -0.2377 0.02571 0.01759 -0.0533 0.9770 0.0513
-4.000 -0.2052 0.02410 0.01545 -0.0544 0.9718 0.0539
-3.750 -0.1726 0.02260 0.01364 -0.0556 0.9666 0.0551
-3.500 -0.1390 0.02142 0.01231 -0.0569 0.9619 0.0563
-3.250 -0.1079 0.02052 0.01131 -0.0576 0.9555 0.0579
-3.000 -0.0722 0.01971 0.01039 -0.0592 0.9510 0.0599
-2.750 -0.0422 0.01906 0.00963 -0.0595 0.9439 0.0629
-2.500 -0.0077 0.01846 0.00894 -0.0608 0.9385 0.0672
-2.250 0.0253 0.01790 0.00841 -0.0619 0.9326 0.0717
-2.000 0.0574 0.01740 0.00787 -0.0626 0.9255 0.0772
-1.750 0.0980 0.01676 0.00726 -0.0649 0.9201 0.0891
-1.500 0.1331 0.01616 0.00673 -0.0659 0.9083 0.1137
-1.250 0.1689 0.01562 0.00627 -0.0670 0.8958 0.1505
-1.000 0.2034 0.01503 0.00599 -0.0681 0.8845 0.2170
-0.750 0.2381 0.01431 0.00580 -0.0694 0.8756 0.3618
-0.500 0.3059 0.01254 0.00564 -0.0767 0.8701 1.0000
-0.250 0.3374 0.01248 0.00540 -0.0770 0.8574 1.0000
0.000 0.3672 0.01244 0.00520 -0.0770 0.8433 1.0000
0.250 0.3957 0.01242 0.00504 -0.0767 0.8277 1.0000
0.500 0.4235 0.01241 0.00491 -0.0762 0.8108 1.0000
0.750 0.4515 0.01240 0.00477 -0.0758 0.7929 1.0000
1.000 0.4800 0.01239 0.00465 -0.0754 0.7742 1.0000
1.250 0.5079 0.01241 0.00454 -0.0749 0.7539 1.0000
1.500 0.5347 0.01247 0.00447 -0.0742 0.7315 1.0000
1.750 0.5614 0.01256 0.00443 -0.0735 0.7079 1.0000
2.000 0.5868 0.01268 0.00443 -0.0725 0.6820 1.0000
2.250 0.6112 0.01284 0.00447 -0.0714 0.6532 1.0000
2.500 0.6351 0.01303 0.00453 -0.0703 0.6212 1.0000
2.750 0.6584 0.01326 0.00460 -0.0690 0.5857 1.0000
3.000 0.6811 0.01353 0.00469 -0.0677 0.5459 1.0000
3.250 0.7032 0.01387 0.00483 -0.0663 0.5056 1.0000
3.500 0.7249 0.01428 0.00501 -0.0650 0.4698 1.0000
3.750 0.7468 0.01471 0.00525 -0.0637 0.4402 1.0000
4.000 0.7691 0.01514 0.00556 -0.0626 0.4163 1.0000
4.250 0.7916 0.01558 0.00589 -0.0615 0.3963 1.0000
4.500 0.8143 0.01603 0.00625 -0.0605 0.3787 1.0000
4.750 0.8371 0.01647 0.00665 -0.0595 0.3629 1.0000
5.000 0.8602 0.01690 0.00705 -0.0586 0.3487 1.0000
5.250 0.8835 0.01734 0.00748 -0.0578 0.3361 1.0000
5.500 0.9068 0.01778 0.00794 -0.0569 0.3243 1.0000
5.750 0.9299 0.01826 0.00843 -0.0561 0.3134 1.0000
6.000 0.9529 0.01874 0.00892 -0.0552 0.3032 1.0000
6.250 0.9764 0.01921 0.00947 -0.0544 0.2934 1.0000
6.500 0.9992 0.01972 0.01000 -0.0535 0.2838 1.0000
6.750 1.0209 0.02020 0.01051 -0.0525 0.2718 1.0000
7.000 1.0422 0.02063 0.01101 -0.0514 0.2582 1.0000
7.250 1.0635 0.02108 0.01155 -0.0504 0.2454 1.0000
7.500 1.0851 0.02157 0.01214 -0.0494 0.2347 1.0000
7.750 1.1059 0.02209 0.01276 -0.0483 0.2248 1.0000
8.000 1.1265 0.02261 0.01339 -0.0471 0.2141 1.0000
8.250 1.1468 0.02314 0.01407 -0.0459 0.2024 1.0000
8.500 1.1661 0.02369 0.01475 -0.0446 0.1898 1.0000
8.750 1.1836 0.02426 0.01540 -0.0431 0.1732 1.0000
9.000 1.1998 0.02488 0.01609 -0.0415 0.1512 1.0000
9.250 1.2149 0.02567 0.01685 -0.0399 0.1242 1.0000
9.500 1.2279 0.02672 0.01782 -0.0381 0.1006 1.0000
9.750 1.2387 0.02801 0.01904 -0.0360 0.0817 1.0000
10.000 1.2469 0.02949 0.02050 -0.0337 0.0678 1.0000
10.250 1.2524 0.03101 0.02208 -0.0309 0.0571 1.0000
10.500 1.2545 0.03267 0.02378 -0.0279 0.0490 1.0000
10.750 1.2556 0.03438 0.02563 -0.0249 0.0436 1.0000
11.000 1.2548 0.03626 0.02762 -0.0220 0.0395 1.0000
11.250 1.2548 0.03815 0.02965 -0.0196 0.0360 1.0000
11.500 1.2513 0.04038 0.03196 -0.0175 0.0339 1.0000
11.750 1.2488 0.04271 0.03445 -0.0156 0.0319 1.0000
12.000 1.2457 0.04523 0.03715 -0.0143 0.0300 1.0000
12.250 1.2412 0.04806 0.04013 -0.0133 0.0288 1.0000
12.500 1.2359 0.05119 0.04339 -0.0128 0.0279 1.0000
12.750 1.2294 0.05465 0.04699 -0.0128 0.0273 1.0000
13.000 1.2209 0.05857 0.05100 -0.0132 0.0265 1.0000
13.250 1.2154 0.06239 0.05499 -0.0137 0.0258 1.0000
13.500 1.2097 0.06645 0.05925 -0.0146 0.0251 1.0000
13.750 1.2031 0.07080 0.06379 -0.0158 0.0245 1.0000
14.000 1.1955 0.07553 0.06870 -0.0174 0.0238 1.0000
14.250 1.1876 0.08043 0.07378 -0.0193 0.0233 1.0000
14.500 1.1782 0.08584 0.07935 -0.0217 0.0227 1.0000
14.750 1.1692 0.09137 0.08503 -0.0243 0.0223 1.0000
15.000 1.1600 0.09705 0.09090 -0.0269 0.0220 1.0000
15.250 1.1499 0.10311 0.09710 -0.0299 0.0216 1.0000
15.500 1.1398 0.10936 0.10351 -0.0331 0.0215 1.0000
15.750 1.1285 0.11602 0.11032 -0.0366 0.0214 1.0000
16.000 1.1157 0.12332 0.11778 -0.0406 0.0213 1.0000
16.250 1.0997 0.13172 0.12632 -0.0455 0.0213 1.0000
16.500 1.0767 0.14250 0.13730 -0.0519 0.0215 1.0000
16.750 1.0279 0.16253 0.15757 -0.0636 0.0227 1.0000
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