GOE 385 AIRFOIL (goe385-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 385 AIRFOIL (goe385-il) Reynolds number: 200,000 Max Cl/Cd: 72.2 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe385-il-200000-n5.txt Download as CSV file: xf-goe385-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 385 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3502 0.08833 0.08506 -0.0314 1.0000 0.0195
-8.000 -0.3483 0.08530 0.08206 -0.0318 1.0000 0.0193
-7.750 -0.3499 0.08224 0.07907 -0.0326 1.0000 0.0192
-7.500 -0.3467 0.07835 0.07522 -0.0358 0.9968 0.0191
-7.250 -0.3261 0.07457 0.07143 -0.0411 0.9869 0.0209
-7.000 -0.3030 0.07059 0.06741 -0.0472 0.9763 0.0228
-6.750 -0.2798 0.06490 0.06164 -0.0551 0.9640 0.0232
-6.500 -0.2575 0.05911 0.05572 -0.0617 0.9507 0.0226
-6.250 -0.2355 0.05366 0.05011 -0.0668 0.9360 0.0226
-6.000 -0.2136 0.04872 0.04496 -0.0704 0.9199 0.0231
-5.750 -0.1881 0.04285 0.03868 -0.0736 0.9035 0.0251
-5.250 -0.1434 0.03398 0.02902 -0.0758 0.8731 0.0269
-5.000 -0.1211 0.03313 0.02811 -0.0759 0.8585 0.0283
-4.750 -0.0972 0.03124 0.02596 -0.0759 0.8449 0.0303
-4.500 -0.0722 0.02837 0.02265 -0.0758 0.8322 0.0310
-4.250 -0.0464 0.02601 0.01986 -0.0755 0.8199 0.0322
-4.000 -0.0194 0.02443 0.01783 -0.0750 0.8076 0.0341
-3.750 0.0073 0.02292 0.01591 -0.0747 0.7953 0.0346
-3.500 0.0344 0.02187 0.01452 -0.0744 0.7829 0.0351
-3.250 0.0601 0.01959 0.01195 -0.0744 0.7711 0.0368
-3.000 0.0870 0.01859 0.01075 -0.0742 0.7587 0.0378
-2.750 0.1143 0.01764 0.00957 -0.0740 0.7464 0.0381
-2.500 0.1418 0.01683 0.00857 -0.0738 0.7329 0.0386
-2.250 0.1690 0.01614 0.00771 -0.0734 0.7173 0.0392
-2.000 0.1961 0.01555 0.00694 -0.0731 0.7000 0.0398
-1.750 0.2231 0.01512 0.00637 -0.0728 0.6839 0.0414
-1.500 0.2503 0.01470 0.00582 -0.0726 0.6714 0.0426
-1.250 0.2776 0.01426 0.00528 -0.0723 0.6607 0.0430
-1.000 0.3049 0.01388 0.00482 -0.0722 0.6509 0.0434
-0.750 0.3322 0.01357 0.00443 -0.0720 0.6418 0.0440
-0.500 0.3596 0.01331 0.00411 -0.0719 0.6326 0.0448
-0.250 0.3872 0.01311 0.00385 -0.0718 0.6240 0.0457
0.000 0.4148 0.01298 0.00364 -0.0717 0.6154 0.0467
0.250 0.4426 0.01287 0.00347 -0.0717 0.6070 0.0478
0.500 0.4703 0.01276 0.00329 -0.0717 0.5988 0.0522
0.750 0.4982 0.01270 0.00321 -0.0717 0.5900 0.0564
1.000 0.5260 0.01270 0.00313 -0.0717 0.5818 0.0608
1.250 0.5528 0.01202 0.00316 -0.0719 0.5730 0.3156
1.750 0.6073 0.01054 0.00321 -0.0712 0.5546 1.0000
2.250 0.6619 0.01077 0.00330 -0.0711 0.5327 1.0000
2.500 0.6890 0.01090 0.00335 -0.0709 0.5199 1.0000
2.750 0.7160 0.01104 0.00341 -0.0708 0.5056 1.0000
3.000 0.7428 0.01119 0.00350 -0.0706 0.4897 1.0000
3.250 0.7694 0.01137 0.00359 -0.0705 0.4726 1.0000
3.500 0.7957 0.01157 0.00371 -0.0703 0.4552 1.0000
3.750 0.8219 0.01179 0.00386 -0.0701 0.4380 1.0000
4.000 0.8479 0.01204 0.00403 -0.0698 0.4217 1.0000
4.250 0.8738 0.01231 0.00423 -0.0696 0.4065 1.0000
4.500 0.8995 0.01259 0.00446 -0.0694 0.3917 1.0000
4.750 0.9250 0.01290 0.00471 -0.0691 0.3777 1.0000
5.000 0.9506 0.01320 0.00498 -0.0689 0.3654 1.0000
5.250 0.9759 0.01352 0.00527 -0.0686 0.3536 1.0000
5.500 1.0010 0.01387 0.00559 -0.0683 0.3417 1.0000
5.750 1.0257 0.01423 0.00592 -0.0680 0.3304 1.0000
6.000 1.0508 0.01456 0.00626 -0.0677 0.3202 1.0000
6.250 1.0758 0.01490 0.00663 -0.0674 0.3115 1.0000
6.500 1.1003 0.01527 0.00701 -0.0670 0.3034 1.0000
6.750 1.1253 0.01559 0.00739 -0.0667 0.2956 1.0000
7.000 1.1492 0.01599 0.00780 -0.0663 0.2861 1.0000
7.250 1.1728 0.01638 0.00822 -0.0658 0.2729 1.0000
7.500 1.1960 0.01679 0.00865 -0.0653 0.2581 1.0000
7.750 1.2190 0.01720 0.00909 -0.0648 0.2440 1.0000
8.000 1.2410 0.01768 0.00957 -0.0642 0.2273 1.0000
8.250 1.2617 0.01827 0.01012 -0.0634 0.2006 1.0000
8.500 1.2799 0.01905 0.01077 -0.0623 0.1645 1.0000
8.750 1.2923 0.02033 0.01176 -0.0606 0.1244 1.0000
9.000 1.3058 0.02150 0.01281 -0.0590 0.1021 1.0000
9.250 1.3163 0.02284 0.01397 -0.0570 0.0618 1.0000
9.500 1.3242 0.02427 0.01534 -0.0546 0.0423 1.0000
10.000 1.3336 0.02709 0.01810 -0.0491 0.0193 1.0000
10.250 1.3390 0.02852 0.01962 -0.0467 0.0173 1.0000
10.500 1.3435 0.03010 0.02134 -0.0445 0.0160 1.0000
10.750 1.3497 0.03164 0.02305 -0.0428 0.0154 1.0000
11.000 1.3542 0.03342 0.02500 -0.0413 0.0148 1.0000
11.250 1.3570 0.03546 0.02720 -0.0400 0.0142 1.0000
11.500 1.3582 0.03779 0.02972 -0.0389 0.0135 1.0000
11.750 1.3574 0.04043 0.03251 -0.0381 0.0130 1.0000
12.000 1.3546 0.04344 0.03567 -0.0376 0.0125 1.0000
12.250 1.3493 0.04689 0.03927 -0.0374 0.0120 1.0000
12.500 1.3418 0.05078 0.04331 -0.0375 0.0117 1.0000
12.750 1.3325 0.05501 0.04768 -0.0378 0.0115 1.0000
13.000 1.3224 0.05943 0.05223 -0.0383 0.0113 1.0000
13.250 1.3159 0.06343 0.05636 -0.0388 0.0112 1.0000
13.500 1.3109 0.06731 0.06037 -0.0393 0.0110 1.0000
13.750 1.3058 0.07130 0.06449 -0.0399 0.0109 1.0000
14.000 1.3008 0.07533 0.06865 -0.0406 0.0107 1.0000
14.250 1.2962 0.07939 0.07283 -0.0413 0.0106 1.0000
14.500 1.2922 0.08342 0.07698 -0.0421 0.0104 1.0000
14.750 1.2885 0.08741 0.08108 -0.0428 0.0103 1.0000
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Polar data table (+)
Polar graphs
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