GOE 584 AIRFOIL (goe584-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 584 AIRFOIL (goe584-il) Reynolds number: 200,000 Max Cl/Cd: 77.92 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe584-il-200000-n5.txt Download as CSV file: xf-goe584-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 584 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3009 0.10994 0.10618 -0.0466 1.0000 0.0296
-11.250 -0.3111 0.10443 0.10071 -0.0488 1.0000 0.0312
-11.000 -0.3198 0.09945 0.09578 -0.0504 1.0000 0.0320
-10.750 -0.3155 0.09768 0.09405 -0.0502 1.0000 0.0324
-10.500 -0.3052 0.09513 0.09154 -0.0517 0.9916 0.0331
-10.250 -0.2916 0.09112 0.08751 -0.0560 0.9796 0.0345
-10.000 -0.3120 0.07814 0.07453 -0.0682 0.9627 0.0376
-9.750 -0.2867 0.07620 0.07256 -0.0721 0.9501 0.0383
-9.500 -0.2602 0.07398 0.07029 -0.0765 0.9367 0.0394
-9.000 -0.3723 0.03524 0.03036 -0.1104 0.8725 0.0453
-8.750 -0.3483 0.03522 0.03032 -0.1101 0.8618 0.0461
-8.500 -0.3284 0.03439 0.02937 -0.1098 0.8518 0.0471
-8.250 -0.3123 0.03284 0.02758 -0.1093 0.8420 0.0485
-8.000 -0.3010 0.03029 0.02462 -0.1086 0.8322 0.0505
-7.750 -0.2879 0.02785 0.02157 -0.1076 0.8237 0.0525
-7.500 -0.2707 0.02614 0.01954 -0.1067 0.8152 0.0538
-7.250 -0.2483 0.02529 0.01860 -0.1062 0.8077 0.0549
-7.000 -0.2255 0.02463 0.01784 -0.1056 0.8001 0.0560
-6.750 -0.2029 0.02380 0.01681 -0.1050 0.7925 0.0572
-6.500 -0.1798 0.02293 0.01574 -0.1043 0.7858 0.0585
-6.250 -0.1566 0.02209 0.01469 -0.1037 0.7782 0.0599
-6.000 -0.1326 0.02126 0.01360 -0.1031 0.7719 0.0611
-5.750 -0.1087 0.02046 0.01259 -0.1024 0.7645 0.0620
-5.500 -0.0838 0.01980 0.01171 -0.1019 0.7578 0.0629
-5.250 -0.0583 0.01931 0.01102 -0.1014 0.7516 0.0637
-5.000 -0.0340 0.01830 0.00992 -0.1009 0.7446 0.0650
-4.750 -0.0083 0.01770 0.00920 -0.1005 0.7386 0.0659
-4.500 0.0173 0.01719 0.00864 -0.1000 0.7317 0.0668
-4.250 0.0432 0.01674 0.00811 -0.0996 0.7254 0.0678
-4.000 0.0695 0.01633 0.00761 -0.0992 0.7198 0.0688
-3.750 0.0953 0.01596 0.00719 -0.0987 0.7128 0.0700
-3.500 0.1216 0.01564 0.00680 -0.0983 0.7067 0.0715
-3.250 0.1479 0.01534 0.00643 -0.0979 0.7011 0.0730
-3.000 0.1739 0.01504 0.00609 -0.0974 0.6946 0.0741
-2.750 0.2003 0.01478 0.00574 -0.0970 0.6890 0.0751
-2.500 0.2264 0.01455 0.00547 -0.0965 0.6830 0.0760
-2.250 0.2520 0.01423 0.00515 -0.0960 0.6769 0.0776
-2.000 0.2780 0.01399 0.00488 -0.0956 0.6717 0.0795
-1.750 0.3040 0.01382 0.00471 -0.0952 0.6657 0.0818
-1.500 0.3301 0.01368 0.00455 -0.0947 0.6596 0.0848
-1.250 0.3568 0.01358 0.00438 -0.0944 0.6546 0.0884
-1.000 0.3827 0.01344 0.00427 -0.0939 0.6485 0.0928
-0.750 0.4088 0.01332 0.00416 -0.0935 0.6425 0.0996
-0.500 0.4352 0.01320 0.00404 -0.0931 0.6374 0.1122
-0.250 0.4605 0.01303 0.00404 -0.0926 0.6309 0.1478
0.000 0.4860 0.01288 0.00402 -0.0921 0.6247 0.1972
0.250 0.5115 0.01274 0.00400 -0.0916 0.6189 0.2457
0.500 0.5356 0.01251 0.00405 -0.0910 0.6120 0.3265
0.750 0.5581 0.01212 0.00407 -0.0900 0.6063 0.4613
1.000 0.6305 0.01104 0.00426 -0.0987 0.5992 0.9769
1.250 0.6721 0.01115 0.00428 -0.1016 0.5925 1.0000
1.750 0.7199 0.01138 0.00437 -0.0999 0.5804 1.0000
2.000 0.7438 0.01150 0.00442 -0.0990 0.5741 1.0000
2.250 0.7678 0.01163 0.00448 -0.0982 0.5683 1.0000
2.500 0.7914 0.01176 0.00459 -0.0973 0.5614 1.0000
2.750 0.8154 0.01190 0.00466 -0.0965 0.5553 1.0000
3.000 0.8390 0.01203 0.00478 -0.0956 0.5485 1.0000
3.250 0.8626 0.01218 0.00489 -0.0947 0.5415 1.0000
3.500 0.8864 0.01233 0.00500 -0.0939 0.5349 1.0000
3.750 0.9098 0.01248 0.00516 -0.0930 0.5274 1.0000
4.000 0.9335 0.01265 0.00526 -0.0921 0.5207 1.0000
4.250 0.9566 0.01281 0.00545 -0.0912 0.5126 1.0000
4.500 0.9799 0.01299 0.00559 -0.0903 0.5051 1.0000
4.750 1.0027 0.01316 0.00579 -0.0893 0.4966 1.0000
5.000 1.0255 0.01336 0.00594 -0.0884 0.4886 1.0000
5.250 1.0479 0.01355 0.00617 -0.0873 0.4793 1.0000
5.500 1.0696 0.01376 0.00635 -0.0862 0.4691 1.0000
5.750 1.0900 0.01399 0.00653 -0.0848 0.4560 1.0000
6.000 1.1096 0.01424 0.00676 -0.0833 0.4410 1.0000
6.250 1.1288 0.01451 0.00700 -0.0818 0.4261 1.0000
6.500 1.1482 0.01481 0.00727 -0.0803 0.4128 1.0000
6.750 1.1672 0.01512 0.00758 -0.0788 0.4006 1.0000
7.000 1.1851 0.01547 0.00790 -0.0771 0.3880 1.0000
7.500 1.2190 0.01623 0.00862 -0.0735 0.3636 1.0000
7.750 1.2347 0.01664 0.00903 -0.0715 0.3519 1.0000
8.000 1.2477 0.01709 0.00945 -0.0690 0.3405 1.0000
8.250 1.2593 0.01758 0.00992 -0.0664 0.3288 1.0000
8.500 1.2720 0.01807 0.01043 -0.0640 0.3178 1.0000
8.750 1.2833 0.01864 0.01098 -0.0615 0.3076 1.0000
9.000 1.2948 0.01924 0.01158 -0.0592 0.2972 1.0000
9.250 1.3068 0.01985 0.01222 -0.0570 0.2872 1.0000
9.500 1.3166 0.02058 0.01296 -0.0547 0.2772 1.0000
9.750 1.3258 0.02139 0.01377 -0.0524 0.2654 1.0000
10.000 1.3336 0.02230 0.01467 -0.0502 0.2520 1.0000
10.250 1.3397 0.02336 0.01571 -0.0479 0.2375 1.0000
10.500 1.3450 0.02455 0.01687 -0.0457 0.2230 1.0000
10.750 1.3505 0.02580 0.01811 -0.0437 0.2097 1.0000
11.000 1.3559 0.02714 0.01944 -0.0418 0.1974 1.0000
11.250 1.3598 0.02864 0.02092 -0.0400 0.1851 1.0000
11.500 1.3634 0.03024 0.02250 -0.0384 0.1742 1.0000
11.750 1.3688 0.03176 0.02404 -0.0370 0.1636 1.0000
12.000 1.3722 0.03350 0.02578 -0.0356 0.1555 1.0000
12.250 1.3780 0.03512 0.02745 -0.0344 0.1474 1.0000
12.500 1.3795 0.03711 0.02945 -0.0331 0.1403 1.0000
12.750 1.3857 0.03878 0.03118 -0.0322 0.1335 1.0000
13.000 1.3878 0.04085 0.03328 -0.0312 0.1268 1.0000
13.250 1.3907 0.04291 0.03539 -0.0303 0.1200 1.0000
13.500 1.3923 0.04516 0.03767 -0.0296 0.1125 1.0000
13.750 1.3937 0.04751 0.04005 -0.0289 0.1060 1.0000
14.000 1.3962 0.04982 0.04243 -0.0284 0.0992 1.0000
14.250 1.3966 0.05240 0.04506 -0.0280 0.0917 1.0000
14.500 1.3949 0.05530 0.04797 -0.0277 0.0806 1.0000
14.750 1.3909 0.05855 0.05120 -0.0276 0.0667 1.0000
15.000 1.3800 0.06269 0.05523 -0.0276 0.0485 1.0000
15.250 1.3696 0.06692 0.05941 -0.0278 0.0399 1.0000
15.500 1.3604 0.07114 0.06364 -0.0282 0.0351 1.0000
15.750 1.3554 0.07493 0.06752 -0.0286 0.0328 1.0000
16.000 1.3486 0.07908 0.07175 -0.0293 0.0306 1.0000
16.250 1.3410 0.08345 0.07622 -0.0301 0.0291 1.0000
16.500 1.3342 0.08781 0.08071 -0.0311 0.0281 1.0000
16.750 1.3289 0.09205 0.08508 -0.0321 0.0268 1.0000
17.000 1.3226 0.09652 0.08968 -0.0334 0.0259 1.0000
17.250 1.3153 0.10124 0.09453 -0.0348 0.0252 1.0000
17.500 1.3063 0.10634 0.09975 -0.0365 0.0245 1.0000
17.750 1.2961 0.11169 0.10522 -0.0385 0.0239 1.0000
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