GOE 376 AIRFOIL (goe376-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 376 AIRFOIL (goe376-il) Reynolds number: 200,000 Max Cl/Cd: 76.5 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe376-il-200000-n5.txt Download as CSV file: xf-goe376-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 376 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2326 0.09285 0.08962 -0.0269 1.0000 0.0194
-8.500 -0.2329 0.09011 0.08691 -0.0271 1.0000 0.0195
-8.250 -0.2341 0.08747 0.08432 -0.0273 1.0000 0.0195
-8.000 -0.2397 0.08532 0.08223 -0.0275 1.0000 0.0195
-7.750 -0.2315 0.08072 0.07766 -0.0255 1.0000 0.0199
-7.500 -0.2315 0.07804 0.07503 -0.0243 1.0000 0.0203
-7.250 -0.2358 0.07585 0.07291 -0.0228 1.0000 0.0205
-7.000 -0.2271 0.07219 0.06926 -0.0252 0.9959 0.0209
-6.750 -0.2133 0.06802 0.06509 -0.0294 0.9878 0.0214
-6.500 -0.2950 0.08151 0.07843 -0.0242 0.9967 0.0203
-6.250 -0.2684 0.07728 0.07418 -0.0303 0.9901 0.0209
-6.000 -0.2398 0.07302 0.06988 -0.0370 0.9818 0.0218
-5.750 -0.2065 0.06868 0.06548 -0.0453 0.9711 0.0236
-5.500 -0.1571 0.06396 0.06056 -0.0586 0.9578 0.0244
-5.250 -0.1218 0.05939 0.05583 -0.0649 0.9471 0.0245
-5.000 -0.1006 0.05461 0.05105 -0.0673 0.9387 0.0249
-4.750 -0.0748 0.05119 0.04759 -0.0700 0.9290 0.0256
-4.500 -0.0397 0.04787 0.04416 -0.0748 0.9211 0.0279
-4.250 0.0176 0.04461 0.04043 -0.0828 0.9115 0.0309
-4.000 0.0510 0.04029 0.03591 -0.0864 0.9016 0.0313
-3.750 0.0765 0.03689 0.03249 -0.0888 0.8914 0.0324
-3.500 0.1059 0.03469 0.03018 -0.0908 0.8788 0.0348
-3.250 0.1466 0.03335 0.02834 -0.0926 0.8653 0.0397
-3.000 0.1729 0.03007 0.02480 -0.0935 0.8513 0.0407
-2.750 0.1958 0.02781 0.02248 -0.0939 0.8366 0.0420
-2.500 0.2205 0.02637 0.02091 -0.0940 0.8212 0.0451
-2.250 0.2494 0.02494 0.01905 -0.0938 0.8060 0.0528
-2.000 0.2729 0.02345 0.01747 -0.0936 0.7907 0.0551
-1.750 0.2987 0.02245 0.01625 -0.0932 0.7759 0.0602
-0.750 0.4049 0.01780 0.01025 -0.0898 0.7184 0.0524
-0.500 0.4302 0.01655 0.00888 -0.0891 0.7041 0.0452
-0.250 0.4575 0.01624 0.00818 -0.0880 0.6891 0.0403
0.000 0.4825 0.01536 0.00715 -0.0873 0.6718 0.0388
0.250 0.5073 0.01476 0.00636 -0.0864 0.6509 0.0382
0.500 0.5319 0.01430 0.00572 -0.0854 0.6276 0.0378
0.750 0.5565 0.01393 0.00519 -0.0845 0.6056 0.0377
1.000 0.5812 0.01362 0.00476 -0.0836 0.5860 0.0379
1.250 0.6058 0.01349 0.00451 -0.0828 0.5665 0.0392
1.500 0.6299 0.01333 0.00425 -0.0819 0.5473 0.0404
1.750 0.6540 0.01316 0.00401 -0.0810 0.5284 0.0403
2.000 0.6779 0.01305 0.00385 -0.0802 0.5115 0.0402
2.250 0.7018 0.01297 0.00372 -0.0793 0.4957 0.0402
2.500 0.7256 0.01294 0.00363 -0.0784 0.4811 0.0403
2.750 0.7496 0.01296 0.00358 -0.0776 0.4674 0.0406
3.000 0.7738 0.01302 0.00356 -0.0768 0.4553 0.0412
3.500 0.8227 0.01325 0.00366 -0.0754 0.4315 0.0436
3.750 0.8472 0.01340 0.00377 -0.0747 0.4194 0.0461
4.000 0.8714 0.01355 0.00391 -0.0740 0.4064 0.0554
4.500 0.9534 0.01263 0.00452 -0.0805 0.3738 1.0000
4.750 0.9772 0.01288 0.00473 -0.0797 0.3615 1.0000
5.000 1.0008 0.01314 0.00495 -0.0789 0.3491 1.0000
5.250 1.0242 0.01341 0.00521 -0.0781 0.3359 1.0000
5.500 1.0473 0.01369 0.00547 -0.0772 0.3218 1.0000
5.750 1.0701 0.01400 0.00576 -0.0763 0.3068 1.0000
6.000 1.0925 0.01434 0.00607 -0.0754 0.2923 1.0000
6.250 1.1144 0.01472 0.00642 -0.0744 0.2755 1.0000
6.500 1.1353 0.01516 0.00680 -0.0732 0.2561 1.0000
6.750 1.1554 0.01566 0.00721 -0.0720 0.2365 1.0000
7.000 1.1754 0.01619 0.00765 -0.0708 0.2166 1.0000
7.250 1.1957 0.01669 0.00813 -0.0696 0.1984 1.0000
7.500 1.2158 0.01720 0.00861 -0.0685 0.1800 1.0000
7.750 1.2341 0.01785 0.00913 -0.0671 0.1521 1.0000
8.000 1.2515 0.01859 0.00975 -0.0656 0.1256 1.0000
8.250 1.2656 0.01963 0.01059 -0.0637 0.0865 1.0000
8.500 1.2662 0.02188 0.01229 -0.0600 0.0220 1.0000
8.750 1.2800 0.02287 0.01334 -0.0579 0.0184 1.0000
9.000 1.2939 0.02380 0.01441 -0.0558 0.0165 1.0000
9.250 1.3062 0.02481 0.01561 -0.0535 0.0152 1.0000
9.500 1.3171 0.02578 0.01674 -0.0510 0.0145 1.0000
9.750 1.3260 0.02676 0.01791 -0.0483 0.0136 1.0000
10.000 1.3330 0.02786 0.01917 -0.0455 0.0128 1.0000
10.250 1.3381 0.02910 0.02057 -0.0427 0.0123 1.0000
10.500 1.3404 0.03058 0.02220 -0.0398 0.0118 1.0000
10.750 1.3405 0.03229 0.02406 -0.0371 0.0114 1.0000
11.000 1.3390 0.03423 0.02615 -0.0347 0.0111 1.0000
11.250 1.3355 0.03651 0.02857 -0.0327 0.0109 1.0000
11.500 1.3309 0.03909 0.03128 -0.0311 0.0107 1.0000
11.750 1.3238 0.04216 0.03448 -0.0299 0.0105 1.0000
12.000 1.3180 0.04532 0.03777 -0.0292 0.0104 1.0000
12.250 1.3101 0.04892 0.04149 -0.0287 0.0102 1.0000
12.500 1.3025 0.05262 0.04529 -0.0283 0.0100 1.0000
12.750 1.2994 0.05590 0.04866 -0.0281 0.0099 1.0000
13.000 1.2988 0.05899 0.05188 -0.0281 0.0098 1.0000
13.250 1.2982 0.06217 0.05519 -0.0284 0.0096 1.0000
13.500 1.2968 0.06557 0.05876 -0.0289 0.0093 1.0000
13.750 1.2950 0.06910 0.06244 -0.0296 0.0090 1.0000
14.000 1.2924 0.07277 0.06624 -0.0301 0.0087 1.0000
14.250 1.2897 0.07652 0.07012 -0.0308 0.0085 1.0000
14.500 1.2868 0.08040 0.07413 -0.0317 0.0084 1.0000
14.750 1.2838 0.08438 0.07825 -0.0325 0.0083 1.0000
15.000 1.2803 0.08851 0.08252 -0.0336 0.0081 1.0000
15.250 1.2761 0.09286 0.08703 -0.0349 0.0080 1.0000
15.500 1.2714 0.09741 0.09173 -0.0364 0.0079 1.0000
15.750 1.2658 0.10223 0.09670 -0.0382 0.0078 1.0000
16.000 1.2596 0.10726 0.10188 -0.0402 0.0078 1.0000
16.250 1.2526 0.11257 0.10734 -0.0425 0.0077 1.0000
16.500 1.2450 0.11816 0.11310 -0.0452 0.0077 1.0000
16.750 1.2367 0.12404 0.11914 -0.0482 0.0077 1.0000
17.000 1.2277 0.13023 0.12550 -0.0515 0.0076 1.0000
17.250 1.2182 0.13673 0.13215 -0.0551 0.0076 1.0000
17.500 1.2079 0.14369 0.13928 -0.0592 0.0077 1.0000
17.750 1.1975 0.15090 0.14665 -0.0635 0.0077 1.0000
18.000 1.1863 0.15865 0.15455 -0.0683 0.0077 1.0000
18.250 1.1741 0.16696 0.16302 -0.0736 0.0078 1.0000
18.500 1.1612 0.17589 0.17210 -0.0792 0.0079 1.0000
18.750 1.1468 0.18584 0.18218 -0.0854 0.0080 1.0000
19.000 1.1309 0.19714 0.19358 -0.0922 0.0082 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 376 AIRFOIL (goe376-il)