GOE 505 AIRFOIL (goe505-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 505 AIRFOIL (goe505-il) Reynolds number: 500,000 Max Cl/Cd: 69.21 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe505-il-500000-n5.txt Download as CSV file: xf-goe505-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 505 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3659 0.03222 0.02868 -0.1608 0.9146 0.0236
-11.250 -0.3719 0.03022 0.02645 -0.1580 0.9017 0.0240
-11.000 -0.3711 0.02834 0.02432 -0.1558 0.8916 0.0242
-10.500 -0.3556 0.02552 0.02104 -0.1518 0.8762 0.0248
-10.250 -0.3432 0.02433 0.01961 -0.1501 0.8701 0.0250
-10.000 -0.3303 0.02339 0.01850 -0.1481 0.8642 0.0252
-9.750 -0.3148 0.02257 0.01749 -0.1465 0.8592 0.0253
-9.500 -0.2988 0.02157 0.01630 -0.1450 0.8551 0.0255
-9.250 -0.2868 0.02027 0.01485 -0.1428 0.8509 0.0260
-9.000 -0.2698 0.01946 0.01394 -0.1412 0.8468 0.0263
-8.750 -0.2505 0.01878 0.01316 -0.1400 0.8432 0.0266
-8.500 -0.2296 0.01815 0.01241 -0.1390 0.8403 0.0269
-8.250 -0.2087 0.01754 0.01170 -0.1379 0.8374 0.0271
-8.000 -0.1889 0.01699 0.01106 -0.1365 0.8341 0.0273
-7.750 -0.1679 0.01646 0.01045 -0.1353 0.8309 0.0276
-7.500 -0.1456 0.01597 0.00986 -0.1344 0.8273 0.0279
-7.250 -0.1216 0.01550 0.00927 -0.1337 0.8236 0.0283
-7.000 -0.1002 0.01507 0.00877 -0.1325 0.8194 0.0285
-6.750 -0.0787 0.01467 0.00829 -0.1312 0.8145 0.0289
-6.500 -0.0550 0.01430 0.00783 -0.1304 0.8102 0.0293
-6.250 -0.0294 0.01395 0.00738 -0.1300 0.8064 0.0297
-6.000 -0.0082 0.01363 0.00702 -0.1286 0.8018 0.0301
-5.750 0.0144 0.01331 0.00664 -0.1275 0.7971 0.0304
-5.500 0.0389 0.01301 0.00626 -0.1268 0.7925 0.0306
-5.250 0.0626 0.01275 0.00594 -0.1259 0.7875 0.0308
-5.000 0.0844 0.01249 0.00565 -0.1245 0.7807 0.0311
-4.750 0.1079 0.01215 0.00522 -0.1236 0.7740 0.0314
-4.500 0.1295 0.01184 0.00489 -0.1223 0.7681 0.0320
-4.250 0.1530 0.01159 0.00461 -0.1213 0.7633 0.0325
-4.000 0.1776 0.01137 0.00435 -0.1206 0.7589 0.0331
-3.750 0.2016 0.01118 0.00413 -0.1197 0.7542 0.0337
-3.500 0.2246 0.01100 0.00393 -0.1186 0.7479 0.0344
-3.250 0.2487 0.01085 0.00373 -0.1177 0.7418 0.0352
-3.000 0.2717 0.01071 0.00357 -0.1166 0.7351 0.0361
-2.750 0.2948 0.01059 0.00340 -0.1155 0.7275 0.0373
-2.500 0.3175 0.01046 0.00325 -0.1143 0.7192 0.0388
-2.250 0.3392 0.01034 0.00310 -0.1129 0.7090 0.0412
-2.000 0.3600 0.01022 0.00297 -0.1113 0.6962 0.0452
-1.750 0.3783 0.01005 0.00285 -0.1093 0.6801 0.0700
-1.500 0.3947 0.01001 0.00277 -0.1068 0.6591 0.0846
-1.250 0.4078 0.01006 0.00271 -0.1035 0.6336 0.0957
-1.000 0.4193 0.01013 0.00269 -0.1000 0.6079 0.1069
-0.750 0.4274 0.01024 0.00270 -0.0957 0.5832 0.1165
-0.500 0.4372 0.01034 0.00273 -0.0919 0.5587 0.1291
-0.250 0.4462 0.01048 0.00281 -0.0880 0.5345 0.1474
0.000 0.4573 0.01066 0.00293 -0.0845 0.5100 0.1645
0.250 0.4686 0.01089 0.00306 -0.0811 0.4868 0.1761
0.500 0.4816 0.01111 0.00320 -0.0781 0.4649 0.1856
0.750 0.4954 0.01135 0.00334 -0.0753 0.4448 0.1933
1.000 0.5099 0.01156 0.00349 -0.0727 0.4267 0.2011
1.250 0.5252 0.01179 0.00363 -0.0703 0.4103 0.2097
1.500 0.5412 0.01198 0.00378 -0.0680 0.3968 0.2176
1.750 0.5580 0.01218 0.00392 -0.0659 0.3851 0.2242
2.000 0.5751 0.01235 0.00408 -0.0639 0.3746 0.2367
2.500 0.6111 0.01267 0.00439 -0.0602 0.3593 0.2615
2.750 0.6288 0.01283 0.00457 -0.0584 0.3525 0.2812
3.000 0.6468 0.01297 0.00475 -0.0566 0.3451 0.3054
3.250 0.6642 0.01316 0.00495 -0.0547 0.3396 0.3278
3.500 0.6832 0.01329 0.00513 -0.0532 0.3349 0.3503
3.750 0.7021 0.01343 0.00531 -0.0516 0.3302 0.3768
4.000 0.7195 0.01356 0.00551 -0.0498 0.3255 0.4129
4.250 0.7187 0.01296 0.00574 -0.0443 0.3222 0.7463
4.750 0.9473 0.01379 0.00696 -0.0830 0.3051 1.0000
5.000 0.9645 0.01398 0.00715 -0.0811 0.3025 1.0000
5.250 0.9815 0.01420 0.00736 -0.0792 0.2998 1.0000
5.500 0.9987 0.01443 0.00758 -0.0774 0.2971 1.0000
5.750 1.0154 0.01469 0.00784 -0.0755 0.2943 1.0000
6.000 1.0315 0.01499 0.00812 -0.0736 0.2915 1.0000
6.250 1.0480 0.01530 0.00841 -0.0718 0.2890 1.0000
6.500 1.0669 0.01554 0.00867 -0.0704 0.2870 1.0000
6.750 1.0852 0.01580 0.00894 -0.0690 0.2830 1.0000
7.000 1.1014 0.01616 0.00927 -0.0672 0.2767 1.0000
7.250 1.1181 0.01653 0.00961 -0.0656 0.2724 1.0000
7.500 1.1368 0.01682 0.00992 -0.0643 0.2681 1.0000
7.750 1.1538 0.01720 0.01029 -0.0628 0.2621 1.0000
8.000 1.1702 0.01762 0.01069 -0.0612 0.2571 1.0000
8.250 1.1880 0.01800 0.01107 -0.0599 0.2496 1.0000
8.500 1.2034 0.01849 0.01152 -0.0583 0.2415 1.0000
8.750 1.2179 0.01906 0.01202 -0.0567 0.2281 1.0000
9.000 1.2326 0.01964 0.01256 -0.0551 0.2165 1.0000
9.250 1.2445 0.02038 0.01322 -0.0532 0.2001 1.0000
9.500 1.2523 0.02140 0.01409 -0.0508 0.1776 1.0000
9.750 1.2616 0.02237 0.01496 -0.0487 0.1628 1.0000
10.000 1.2679 0.02354 0.01602 -0.0464 0.1449 1.0000
10.250 1.2742 0.02476 0.01712 -0.0441 0.1234 1.0000
10.500 1.2425 0.02859 0.02046 -0.0380 0.0370 1.0000
10.750 1.2452 0.03022 0.02206 -0.0357 0.0180 1.0000
11.000 1.2552 0.03134 0.02323 -0.0342 0.0160 1.0000
11.250 1.2658 0.03244 0.02438 -0.0328 0.0149 1.0000
11.500 1.2763 0.03358 0.02558 -0.0315 0.0142 1.0000
11.750 1.2850 0.03489 0.02696 -0.0302 0.0133 1.0000
12.000 1.2927 0.03632 0.02846 -0.0288 0.0127 1.0000
12.250 1.2991 0.03788 0.03010 -0.0274 0.0121 1.0000
12.500 1.3067 0.03937 0.03167 -0.0263 0.0119 1.0000
12.750 1.3134 0.04100 0.03337 -0.0251 0.0114 1.0000
13.000 1.3191 0.04277 0.03522 -0.0240 0.0111 1.0000
13.250 1.3234 0.04472 0.03726 -0.0230 0.0108 1.0000
13.500 1.3269 0.04682 0.03943 -0.0221 0.0104 1.0000
13.750 1.3288 0.04913 0.04183 -0.0212 0.0102 1.0000
14.000 1.3284 0.05177 0.04456 -0.0204 0.0099 1.0000
14.250 1.3260 0.05474 0.04762 -0.0198 0.0096 1.0000
14.500 1.3201 0.05822 0.05122 -0.0193 0.0095 1.0000
14.750 1.3168 0.06150 0.05460 -0.0190 0.0093 1.0000
15.000 1.3148 0.06473 0.05793 -0.0189 0.0091 1.0000
15.250 1.3092 0.06849 0.06182 -0.0190 0.0089 1.0000
15.500 1.3006 0.07279 0.06623 -0.0193 0.0089 1.0000
15.750 1.2920 0.07715 0.07072 -0.0198 0.0087 1.0000
16.000 1.2814 0.08191 0.07559 -0.0205 0.0087 1.0000
16.250 1.2699 0.08690 0.08071 -0.0214 0.0086 1.0000
16.500 1.2595 0.09180 0.08572 -0.0224 0.0086 1.0000
16.750 1.2477 0.09695 0.09099 -0.0235 0.0084 1.0000
17.000 1.2359 0.10217 0.09632 -0.0247 0.0082 1.0000
17.250 1.2240 0.10745 0.10170 -0.0260 0.0082 1.0000
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