GOE 505 AIRFOIL (goe505-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 505 AIRFOIL (goe505-il) Reynolds number: 1,000,000 Max Cl/Cd: 90.96 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe505-il-1000000.txt Download as CSV file: xf-goe505-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 0.0311 0.10191 0.10014 -0.1134 0.9662 0.0231
-12.500 0.0392 0.09857 0.09680 -0.1153 0.9632 0.0240
-12.000 -0.3726 0.03158 0.02894 -0.1694 0.9522 0.0228
-11.750 -0.3526 0.03081 0.02815 -0.1698 0.9448 0.0231
-11.500 -0.3542 0.02873 0.02588 -0.1680 0.9321 0.0232
-11.250 -0.3515 0.02731 0.02429 -0.1657 0.9205 0.0235
-11.000 -0.3480 0.02577 0.02254 -0.1632 0.9090 0.0237
-10.750 -0.3440 0.02453 0.02113 -0.1602 0.8976 0.0240
-10.500 -0.3361 0.02344 0.01985 -0.1576 0.8883 0.0243
-10.250 -0.3240 0.02252 0.01875 -0.1556 0.8807 0.0247
-10.000 -0.3123 0.02166 0.01772 -0.1532 0.8742 0.0250
-9.750 -0.2975 0.02094 0.01684 -0.1513 0.8686 0.0253
-9.500 -0.2801 0.02030 0.01603 -0.1498 0.8638 0.0255
-9.250 -0.2627 0.01993 0.01554 -0.1480 0.8595 0.0257
-9.000 -0.2541 0.01823 0.01359 -0.1452 0.8548 0.0260
-8.750 -0.2390 0.01689 0.01210 -0.1433 0.8508 0.0263
-8.500 -0.2199 0.01609 0.01121 -0.1420 0.8469 0.0266
-8.250 -0.2002 0.01557 0.01066 -0.1406 0.8429 0.0271
-8.000 -0.1792 0.01508 0.01010 -0.1394 0.8385 0.0275
-7.750 -0.1568 0.01457 0.00948 -0.1384 0.8343 0.0278
-7.500 -0.1347 0.01410 0.00894 -0.1374 0.8305 0.0281
-7.250 -0.1132 0.01364 0.00843 -0.1361 0.8267 0.0284
-7.000 -0.0910 0.01319 0.00790 -0.1350 0.8227 0.0287
-6.750 -0.0672 0.01278 0.00741 -0.1342 0.8188 0.0290
-6.500 -0.0431 0.01241 0.00697 -0.1335 0.8152 0.0294
-6.250 -0.0206 0.01208 0.00660 -0.1323 0.8115 0.0298
-6.000 0.0025 0.01176 0.00623 -0.1313 0.8070 0.0301
-5.750 0.0277 0.01156 0.00594 -0.1306 0.8017 0.0305
-5.500 0.0510 0.01131 0.00566 -0.1296 0.7968 0.0307
-5.250 0.0731 0.01086 0.00516 -0.1284 0.7927 0.0310
-5.000 0.0958 0.01040 0.00465 -0.1273 0.7895 0.0315
-4.750 0.1202 0.01007 0.00427 -0.1266 0.7862 0.0320
-4.500 0.1452 0.00982 0.00398 -0.1259 0.7825 0.0325
-4.250 0.1688 0.00958 0.00373 -0.1250 0.7790 0.0331
-4.000 0.1930 0.00937 0.00351 -0.1241 0.7748 0.0337
-3.750 0.2181 0.00919 0.00329 -0.1234 0.7707 0.0344
-3.500 0.2438 0.00905 0.00310 -0.1229 0.7667 0.0352
-3.250 0.2677 0.00889 0.00295 -0.1220 0.7624 0.0361
-3.000 0.2921 0.00875 0.00279 -0.1211 0.7575 0.0367
-2.750 0.3166 0.00858 0.00257 -0.1203 0.7525 0.0386
-2.500 0.3403 0.00843 0.00244 -0.1193 0.7472 0.0404
-2.250 0.3637 0.00831 0.00231 -0.1182 0.7405 0.0428
-2.000 0.3855 0.00809 0.00217 -0.1169 0.7334 0.0655
-1.750 0.4064 0.00790 0.00209 -0.1154 0.7242 0.0944
-1.500 0.4273 0.00779 0.00201 -0.1138 0.7142 0.1129
-1.250 0.4465 0.00771 0.00196 -0.1119 0.7016 0.1336
-1.000 0.4645 0.00768 0.00193 -0.1097 0.6854 0.1517
-0.750 0.4800 0.00771 0.00192 -0.1069 0.6646 0.1671
-0.500 0.4917 0.00780 0.00194 -0.1033 0.6403 0.1791
-0.250 0.4998 0.00793 0.00196 -0.0990 0.6143 0.1874
0.000 0.5084 0.00807 0.00201 -0.0948 0.5887 0.1955
0.250 0.5171 0.00828 0.00209 -0.0907 0.5615 0.2008
0.500 0.5277 0.00849 0.00219 -0.0870 0.5337 0.2074
0.750 0.5381 0.00875 0.00233 -0.0834 0.5051 0.2135
1.000 0.5490 0.00904 0.00248 -0.0799 0.4770 0.2190
1.250 0.5601 0.00931 0.00265 -0.0765 0.4488 0.2272
1.500 0.5738 0.00956 0.00280 -0.0736 0.4267 0.2344
1.750 0.5879 0.00979 0.00295 -0.0709 0.4056 0.2439
2.000 0.6043 0.00997 0.00309 -0.0687 0.3914 0.2565
2.250 0.6203 0.01016 0.00324 -0.0664 0.3782 0.2686
2.500 0.6361 0.01035 0.00341 -0.0640 0.3658 0.2829
2.750 0.6551 0.01046 0.00355 -0.0623 0.3581 0.3055
3.000 0.6720 0.01061 0.00372 -0.0603 0.3505 0.3364
3.250 0.6904 0.01069 0.00388 -0.0585 0.3450 0.3727
3.500 0.7067 0.01076 0.00405 -0.0564 0.3385 0.4233
3.750 0.8640 0.01015 0.00476 -0.0856 0.3263 0.9842
4.000 0.9014 0.01045 0.00501 -0.0880 0.3216 0.9919
4.250 0.9398 0.01077 0.00527 -0.0907 0.3163 0.9966
4.500 0.9855 0.01096 0.00544 -0.0948 0.3132 0.9992
4.750 1.0142 0.01115 0.00561 -0.0954 0.3098 1.0000
5.000 1.0281 0.01133 0.00577 -0.0928 0.3071 1.0000
5.250 1.0420 0.01155 0.00597 -0.0902 0.3039 1.0000
5.500 1.0553 0.01180 0.00620 -0.0875 0.3006 1.0000
5.750 1.0737 0.01194 0.00635 -0.0858 0.2984 1.0000
6.000 1.0916 0.01211 0.00653 -0.0841 0.2950 1.0000
6.250 1.1082 0.01233 0.00674 -0.0821 0.2911 1.0000
6.500 1.1235 0.01262 0.00700 -0.0800 0.2871 1.0000
6.750 1.1413 0.01285 0.00722 -0.0783 0.2829 1.0000
7.000 1.1603 0.01305 0.00743 -0.0769 0.2803 1.0000
7.250 1.1778 0.01331 0.00768 -0.0753 0.2752 1.0000
7.500 1.1939 0.01364 0.00798 -0.0734 0.2709 1.0000
7.750 1.2127 0.01388 0.00823 -0.0720 0.2666 1.0000
8.000 1.2311 0.01415 0.00850 -0.0707 0.2610 1.0000
8.250 1.2466 0.01456 0.00886 -0.0688 0.2541 1.0000
8.500 1.2651 0.01485 0.00915 -0.0675 0.2470 1.0000
8.750 1.2806 0.01529 0.00954 -0.0658 0.2371 1.0000
9.000 1.2949 0.01581 0.00999 -0.0640 0.2246 1.0000
9.250 1.3066 0.01649 0.01055 -0.0618 0.2041 1.0000
9.500 1.3106 0.01758 0.01144 -0.0586 0.1752 1.0000
9.750 1.3152 0.01870 0.01239 -0.0556 0.1519 1.0000
10.000 1.3128 0.02027 0.01369 -0.0519 0.1153 1.0000
10.250 1.2888 0.02325 0.01628 -0.0457 0.0455 1.0000
10.500 1.2884 0.02491 0.01786 -0.0426 0.0182 1.0000
10.750 1.3004 0.02581 0.01878 -0.0410 0.0165 1.0000
11.000 1.3120 0.02674 0.01976 -0.0395 0.0154 1.0000
11.250 1.3240 0.02767 0.02074 -0.0381 0.0147 1.0000
11.500 1.3342 0.02875 0.02186 -0.0366 0.0142 1.0000
11.750 1.3429 0.02996 0.02313 -0.0350 0.0135 1.0000
12.000 1.3497 0.03135 0.02458 -0.0332 0.0129 1.0000
12.250 1.3598 0.03250 0.02578 -0.0319 0.0125 1.0000
12.500 1.3683 0.03382 0.02715 -0.0306 0.0122 1.0000
12.750 1.3751 0.03532 0.02870 -0.0292 0.0119 1.0000
13.000 1.3821 0.03683 0.03028 -0.0279 0.0117 1.0000
13.250 1.3873 0.03853 0.03204 -0.0266 0.0114 1.0000
13.500 1.3914 0.04039 0.03397 -0.0253 0.0112 1.0000
13.750 1.3937 0.04248 0.03612 -0.0241 0.0108 1.0000
14.000 1.3915 0.04510 0.03883 -0.0228 0.0105 1.0000
14.250 1.3819 0.04857 0.04243 -0.0215 0.0102 1.0000
14.500 1.3768 0.05173 0.04570 -0.0206 0.0102 1.0000
14.750 1.3804 0.05407 0.04810 -0.0201 0.0100 1.0000
15.000 1.3816 0.05672 0.05083 -0.0198 0.0099 1.0000
15.250 1.3735 0.06058 0.05479 -0.0195 0.0099 1.0000
15.500 1.3698 0.06399 0.05830 -0.0194 0.0097 1.0000
15.750 1.3653 0.06760 0.06200 -0.0195 0.0096 1.0000
16.000 1.3554 0.07203 0.06653 -0.0198 0.0095 1.0000
16.250 1.3500 0.07595 0.07054 -0.0202 0.0093 1.0000
16.500 1.3368 0.08100 0.07570 -0.0209 0.0092 1.0000
16.750 1.3242 0.08610 0.08091 -0.0218 0.0090 1.0000
17.000 1.3137 0.09096 0.08587 -0.0227 0.0089 1.0000
17.250 1.3004 0.09630 0.09132 -0.0239 0.0088 1.0000
17.500 1.2851 0.10196 0.09709 -0.0252 0.0089 1.0000
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