GOE 769 AIRFOIL (goe769-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 769 AIRFOIL (goe769-il) Reynolds number: 500,000 Max Cl/Cd: 85.24 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe769-il-500000-n5.txt Download as CSV file: xf-goe769-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 769 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.7105 0.03771 0.03423 -0.0721 1.0000 0.0256
-11.000 -0.7210 0.03328 0.02947 -0.0725 0.9994 0.0256
-10.750 -0.6993 0.02987 0.02579 -0.0761 0.9774 0.0257
-10.500 -0.6594 0.02736 0.02306 -0.0813 0.9424 0.0259
-10.250 -0.6212 0.02559 0.02101 -0.0850 0.8832 0.0261
-10.000 -0.6032 0.02461 0.01972 -0.0839 0.8290 0.0263
-9.750 -0.5854 0.02375 0.01862 -0.0826 0.7923 0.0264
-9.500 -0.5663 0.02289 0.01753 -0.0814 0.7639 0.0265
-9.250 -0.5459 0.02208 0.01653 -0.0804 0.7412 0.0267
-9.000 -0.5246 0.02129 0.01555 -0.0795 0.7221 0.0269
-8.750 -0.5024 0.02056 0.01465 -0.0786 0.7060 0.0271
-8.500 -0.4795 0.01988 0.01381 -0.0778 0.6915 0.0273
-8.250 -0.4558 0.01924 0.01303 -0.0770 0.6784 0.0276
-8.000 -0.4318 0.01863 0.01226 -0.0763 0.6671 0.0279
-7.750 -0.4073 0.01803 0.01152 -0.0756 0.6564 0.0281
-7.500 -0.3825 0.01746 0.01080 -0.0749 0.6472 0.0284
-7.250 -0.3573 0.01692 0.01013 -0.0742 0.6373 0.0286
-7.000 -0.3318 0.01643 0.00951 -0.0735 0.6283 0.0288
-6.750 -0.3058 0.01598 0.00895 -0.0729 0.6193 0.0290
-6.500 -0.2803 0.01550 0.00837 -0.0723 0.6110 0.0292
-6.250 -0.2542 0.01502 0.00786 -0.0717 0.6033 0.0295
-6.000 -0.2279 0.01464 0.00742 -0.0711 0.5944 0.0298
-5.750 -0.2014 0.01431 0.00703 -0.0706 0.5856 0.0301
-5.500 -0.1746 0.01400 0.00666 -0.0700 0.5758 0.0305
-5.250 -0.1478 0.01371 0.00631 -0.0695 0.5671 0.0309
-5.000 -0.1207 0.01342 0.00597 -0.0690 0.5577 0.0313
-4.750 -0.0938 0.01318 0.00564 -0.0684 0.5484 0.0317
-4.500 -0.0665 0.01292 0.00533 -0.0679 0.5379 0.0322
-4.250 -0.0394 0.01272 0.00505 -0.0674 0.5266 0.0326
-4.000 -0.0124 0.01248 0.00476 -0.0669 0.5140 0.0332
-3.750 0.0147 0.01229 0.00452 -0.0664 0.5002 0.0339
-3.500 0.0417 0.01216 0.00431 -0.0659 0.4836 0.0347
-3.250 0.0687 0.01205 0.00411 -0.0653 0.4668 0.0356
-3.000 0.0958 0.01195 0.00392 -0.0648 0.4532 0.0365
-2.750 0.1231 0.01182 0.00374 -0.0643 0.4412 0.0374
-2.500 0.1504 0.01171 0.00359 -0.0638 0.4309 0.0386
-2.250 0.1778 0.01163 0.00346 -0.0634 0.4211 0.0401
-2.000 0.2052 0.01155 0.00334 -0.0629 0.4122 0.0418
-1.750 0.2326 0.01147 0.00324 -0.0625 0.4024 0.0443
-1.500 0.2600 0.01141 0.00315 -0.0620 0.3945 0.0477
-1.250 0.2876 0.01134 0.00308 -0.0616 0.3867 0.0527
-0.750 0.3425 0.01127 0.00300 -0.0608 0.3715 0.0670
-0.500 0.3699 0.01127 0.00299 -0.0603 0.3634 0.0745
-0.250 0.3974 0.01127 0.00299 -0.0599 0.3573 0.0816
0.000 0.4251 0.01126 0.00299 -0.0596 0.3506 0.0887
0.250 0.4524 0.01130 0.00300 -0.0591 0.3432 0.0958
0.500 0.4799 0.01131 0.00301 -0.0587 0.3366 0.1031
0.750 0.5073 0.01133 0.00303 -0.0584 0.3295 0.1105
1.000 0.5343 0.01138 0.00307 -0.0579 0.3230 0.1206
1.250 0.5618 0.01138 0.00311 -0.0575 0.3171 0.1330
1.500 0.5888 0.01142 0.00315 -0.0571 0.3098 0.1462
1.750 0.6157 0.01145 0.00320 -0.0567 0.3031 0.1634
2.250 0.6686 0.01142 0.00337 -0.0558 0.2888 0.2547
2.500 0.6949 0.01133 0.00346 -0.0553 0.2826 0.3258
2.750 0.7190 0.01109 0.00358 -0.0546 0.2749 0.4803
3.500 0.8307 0.01053 0.00406 -0.0599 0.2504 1.0000
3.750 0.8555 0.01074 0.00419 -0.0591 0.2437 1.0000
4.000 0.8802 0.01095 0.00433 -0.0583 0.2377 1.0000
4.250 0.9052 0.01115 0.00448 -0.0575 0.2320 1.0000
4.500 0.9297 0.01139 0.00465 -0.0567 0.2267 1.0000
4.750 0.9545 0.01160 0.00482 -0.0560 0.2226 1.0000
5.000 0.9795 0.01181 0.00499 -0.0553 0.2183 1.0000
5.250 1.0040 0.01205 0.00519 -0.0545 0.2139 1.0000
5.500 1.0279 0.01233 0.00541 -0.0537 0.2097 1.0000
5.750 1.0529 0.01253 0.00560 -0.0530 0.2070 1.0000
6.000 1.0776 0.01275 0.00581 -0.0523 0.2039 1.0000
6.250 1.1018 0.01300 0.00603 -0.0516 0.2005 1.0000
6.500 1.1254 0.01329 0.00628 -0.0508 0.1971 1.0000
6.750 1.1491 0.01357 0.00654 -0.0500 0.1942 1.0000
7.000 1.1734 0.01380 0.00677 -0.0492 0.1918 1.0000
7.250 1.1973 0.01405 0.00702 -0.0485 0.1892 1.0000
7.500 1.2206 0.01432 0.00729 -0.0477 0.1865 1.0000
7.750 1.2431 0.01464 0.00759 -0.0468 0.1838 1.0000
8.000 1.2648 0.01500 0.00792 -0.0458 0.1809 1.0000
8.250 1.2881 0.01525 0.00819 -0.0450 0.1789 1.0000
8.500 1.3106 0.01553 0.00849 -0.0441 0.1766 1.0000
8.750 1.3325 0.01584 0.00880 -0.0431 0.1743 1.0000
9.000 1.3534 0.01618 0.00915 -0.0420 0.1720 1.0000
9.250 1.3733 0.01656 0.00952 -0.0408 0.1698 1.0000
9.500 1.3918 0.01699 0.00994 -0.0394 0.1675 1.0000
9.750 1.4121 0.01730 0.01029 -0.0383 0.1658 1.0000
10.000 1.4303 0.01764 0.01067 -0.0368 0.1638 1.0000
10.250 1.4465 0.01802 0.01107 -0.0350 0.1617 1.0000
10.500 1.4613 0.01846 0.01152 -0.0331 0.1598 1.0000
10.750 1.4751 0.01895 0.01203 -0.0311 0.1579 1.0000
11.000 1.4876 0.01954 0.01263 -0.0291 0.1561 1.0000
11.250 1.5006 0.02013 0.01325 -0.0274 0.1545 1.0000
11.500 1.5153 0.02069 0.01386 -0.0259 0.1531 1.0000
11.750 1.5291 0.02132 0.01454 -0.0244 0.1515 1.0000
12.000 1.5420 0.02204 0.01531 -0.0230 0.1498 1.0000
12.250 1.5536 0.02288 0.01619 -0.0217 0.1479 1.0000
12.500 1.5638 0.02387 0.01721 -0.0204 0.1462 1.0000
12.750 1.5726 0.02503 0.01840 -0.0193 0.1445 1.0000
13.000 1.5805 0.02634 0.01974 -0.0182 0.1430 1.0000
13.250 1.5921 0.02744 0.02092 -0.0175 0.1419 1.0000
13.500 1.6026 0.02868 0.02223 -0.0169 0.1405 1.0000
13.750 1.6120 0.03007 0.02368 -0.0163 0.1391 1.0000
14.000 1.6203 0.03158 0.02526 -0.0158 0.1377 1.0000
14.250 1.6269 0.03331 0.02703 -0.0154 0.1362 1.0000
14.500 1.6318 0.03523 0.02901 -0.0151 0.1347 1.0000
14.750 1.6348 0.03738 0.03120 -0.0149 0.1333 1.0000
15.000 1.6363 0.03969 0.03356 -0.0147 0.1319 1.0000
15.250 1.6421 0.04162 0.03558 -0.0146 0.1309 1.0000
15.500 1.6466 0.04369 0.03774 -0.0146 0.1298 1.0000
15.750 1.6496 0.04595 0.04007 -0.0146 0.1283 1.0000
16.000 1.6510 0.04842 0.04262 -0.0147 0.1270 1.0000
16.250 1.6504 0.05118 0.04544 -0.0150 0.1255 1.0000
16.500 1.6485 0.05415 0.04847 -0.0154 0.1242 1.0000
16.750 1.6443 0.05745 0.05183 -0.0160 0.1227 1.0000
17.000 1.6398 0.06087 0.05529 -0.0166 0.1212 1.0000
17.250 1.6408 0.06367 0.05820 -0.0172 0.1201 1.0000
17.500 1.6395 0.06685 0.06147 -0.0180 0.1185 1.0000
17.750 1.6369 0.07021 0.06492 -0.0188 0.1173 1.0000
18.000 1.6321 0.07393 0.06870 -0.0199 0.1155 1.0000
18.250 1.6274 0.07763 0.07248 -0.0210 0.1145 1.0000
18.500 1.6197 0.08183 0.07673 -0.0223 0.1131 1.0000
18.750 1.6121 0.08603 0.08098 -0.0237 0.1118 1.0000
19.000 1.6094 0.08958 0.08463 -0.0249 0.1109 1.0000
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