GOE 286 AIRFOIL (goe286-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 286 AIRFOIL (goe286-il) Reynolds number: 500,000 Max Cl/Cd: 78.82 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe286-il-500000-n5.txt Download as CSV file: xf-goe286-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 286 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4055 0.08747 0.08532 -0.0171 1.0000 0.0141
-8.250 -0.4042 0.08326 0.08114 -0.0200 1.0000 0.0147
-8.000 -0.4072 0.07371 0.07159 -0.0315 0.9849 0.0159
-7.500 -0.3716 0.06726 0.06508 -0.0400 0.9594 0.0164
-7.250 -0.3574 0.06352 0.06129 -0.0437 0.9439 0.0167
-7.000 -0.3425 0.05907 0.05675 -0.0480 0.9266 0.0172
-6.750 -0.3277 0.04219 0.03940 -0.0618 0.9137 0.0197
-6.500 -0.3094 0.03948 0.03652 -0.0624 0.8895 0.0200
-6.250 -0.2905 0.03765 0.03448 -0.0622 0.8595 0.0203
-6.000 -0.2696 0.03573 0.03230 -0.0623 0.8303 0.0207
-5.750 -0.2470 0.03312 0.02941 -0.0628 0.8056 0.0215
-5.500 -0.2257 0.02456 0.02006 -0.0643 0.7891 0.0230
-5.250 -0.2013 0.02094 0.01570 -0.0643 0.7641 0.0241
-5.000 -0.1757 0.01933 0.01362 -0.0642 0.7271 0.0245
-4.500 -0.1236 0.01679 0.01038 -0.0641 0.6596 0.0252
-4.250 -0.0963 0.01605 0.00941 -0.0641 0.6419 0.0255
-4.000 -0.0686 0.01538 0.00855 -0.0641 0.6294 0.0258
-3.750 -0.0407 0.01481 0.00783 -0.0642 0.6186 0.0262
-3.500 -0.0127 0.01437 0.00724 -0.0642 0.6082 0.0268
-3.250 0.0154 0.01385 0.00659 -0.0642 0.5963 0.0272
-3.000 0.0436 0.01334 0.00594 -0.0642 0.5852 0.0275
-2.750 0.0719 0.01290 0.00539 -0.0642 0.5746 0.0279
-2.500 0.1002 0.01251 0.00489 -0.0642 0.5628 0.0283
-2.250 0.1285 0.01216 0.00446 -0.0642 0.5507 0.0287
-2.000 0.1568 0.01186 0.00408 -0.0642 0.5354 0.0290
-1.750 0.1850 0.01163 0.00373 -0.0642 0.5132 0.0293
-1.500 0.2130 0.01149 0.00343 -0.0642 0.4782 0.0296
-1.250 0.2408 0.01143 0.00319 -0.0642 0.4439 0.0299
-1.000 0.2687 0.01141 0.00303 -0.0643 0.4179 0.0303
-0.750 0.2967 0.01132 0.00282 -0.0643 0.3966 0.0309
-0.500 0.3247 0.01119 0.00260 -0.0644 0.3783 0.0315
-0.250 0.3529 0.01112 0.00246 -0.0644 0.3632 0.0321
0.000 0.3812 0.01107 0.00235 -0.0645 0.3509 0.0329
0.250 0.4095 0.01107 0.00228 -0.0645 0.3383 0.0338
0.500 0.4377 0.01109 0.00223 -0.0646 0.3255 0.0348
1.000 0.4939 0.01123 0.00220 -0.0647 0.2935 0.0372
1.500 0.5492 0.01147 0.00229 -0.0648 0.2477 0.0558
1.750 0.5765 0.01162 0.00241 -0.0648 0.2171 0.1066
2.000 0.6014 0.01206 0.00277 -0.0649 0.1335 0.2244
2.500 0.6533 0.01061 0.00311 -0.0644 0.1197 1.0000
2.750 0.6809 0.01079 0.00324 -0.0644 0.1175 1.0000
3.000 0.7084 0.01098 0.00338 -0.0644 0.1150 1.0000
3.250 0.7358 0.01118 0.00353 -0.0643 0.1125 1.0000
3.500 0.7632 0.01138 0.00370 -0.0643 0.1104 1.0000
3.750 0.7906 0.01157 0.00387 -0.0642 0.1088 1.0000
4.000 0.8179 0.01175 0.00403 -0.0642 0.1081 1.0000
4.250 0.8453 0.01192 0.00420 -0.0641 0.1073 1.0000
4.500 0.8725 0.01210 0.00438 -0.0641 0.1063 1.0000
4.750 0.8996 0.01229 0.00457 -0.0640 0.1051 1.0000
5.000 0.9266 0.01250 0.00478 -0.0639 0.1037 1.0000
5.250 0.9534 0.01272 0.00500 -0.0639 0.1022 1.0000
5.500 0.9801 0.01295 0.00523 -0.0638 0.1004 1.0000
5.750 1.0065 0.01321 0.00549 -0.0636 0.0986 1.0000
6.000 1.0328 0.01348 0.00577 -0.0635 0.0966 1.0000
6.250 1.0591 0.01373 0.00603 -0.0634 0.0952 1.0000
6.500 1.0858 0.01391 0.00624 -0.0633 0.0936 1.0000
6.750 1.1122 0.01411 0.00647 -0.0631 0.0886 1.0000
7.000 1.1359 0.01468 0.00682 -0.0628 0.0592 1.0000
7.250 1.1603 0.01513 0.00727 -0.0624 0.0560 1.0000
7.500 1.1846 0.01556 0.00773 -0.0620 0.0535 1.0000
7.750 1.2089 0.01598 0.00818 -0.0616 0.0513 1.0000
8.000 1.2334 0.01634 0.00859 -0.0613 0.0500 1.0000
8.250 1.2577 0.01671 0.00901 -0.0609 0.0485 1.0000
8.500 1.2813 0.01713 0.00949 -0.0605 0.0462 1.0000
8.750 1.3041 0.01762 0.01002 -0.0599 0.0441 1.0000
9.000 1.3263 0.01814 0.01058 -0.0593 0.0418 1.0000
9.250 1.3500 0.01846 0.01096 -0.0589 0.0390 1.0000
9.500 1.3722 0.01893 0.01145 -0.0583 0.0337 1.0000
9.750 1.3889 0.01989 0.01225 -0.0570 0.0164 1.0000
10.000 1.4074 0.02063 0.01304 -0.0559 0.0141 1.0000
10.250 1.4249 0.02141 0.01388 -0.0547 0.0128 1.0000
10.500 1.4402 0.02229 0.01484 -0.0532 0.0117 1.0000
10.750 1.4552 0.02312 0.01577 -0.0517 0.0109 1.0000
11.000 1.4690 0.02392 0.01665 -0.0500 0.0104 1.0000
11.250 1.4789 0.02481 0.01763 -0.0477 0.0099 1.0000
11.500 1.4876 0.02585 0.01876 -0.0456 0.0095 1.0000
11.750 1.4952 0.02706 0.02006 -0.0436 0.0091 1.0000
12.000 1.5011 0.02848 0.02158 -0.0417 0.0088 1.0000
12.250 1.5044 0.03023 0.02345 -0.0399 0.0085 1.0000
12.500 1.5049 0.03240 0.02573 -0.0385 0.0082 1.0000
12.750 1.5096 0.03434 0.02778 -0.0376 0.0080 1.0000
13.000 1.5129 0.03656 0.03012 -0.0369 0.0078 1.0000
13.250 1.5146 0.03909 0.03276 -0.0366 0.0076 1.0000
13.500 1.5150 0.04193 0.03573 -0.0366 0.0074 1.0000
13.750 1.5138 0.04516 0.03907 -0.0369 0.0072 1.0000
14.000 1.5111 0.04872 0.04275 -0.0375 0.0070 1.0000
14.250 1.5065 0.05259 0.04675 -0.0383 0.0069 1.0000
14.500 1.5000 0.05674 0.05103 -0.0391 0.0068 1.0000
14.750 1.4917 0.06119 0.05560 -0.0401 0.0067 1.0000
15.000 1.4818 0.06595 0.06048 -0.0413 0.0066 1.0000
15.250 1.4711 0.07095 0.06561 -0.0427 0.0065 1.0000
15.500 1.4596 0.07625 0.07103 -0.0443 0.0064 1.0000
15.750 1.4476 0.08172 0.07661 -0.0460 0.0064 1.0000
16.000 1.4352 0.08732 0.08233 -0.0478 0.0063 1.0000
16.250 1.4228 0.09305 0.08817 -0.0497 0.0063 1.0000
16.500 1.4103 0.09884 0.09406 -0.0518 0.0062 1.0000
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Polar data table (+)
Polar graphs
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