GOE 506 AIRFOIL (goe506-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 506 AIRFOIL (goe506-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.91 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe506-il-1000000-n5.txt Download as CSV file: xf-goe506-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 506 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -0.5932 0.11402 0.11168 -0.0808 0.9939 0.0072
-18.250 -0.6200 0.10478 0.10232 -0.0861 0.9926 0.0072
-18.000 -0.6438 0.09632 0.09375 -0.0913 0.9909 0.0073
-17.750 -0.6598 0.08935 0.08667 -0.0958 0.9887 0.0073
-17.500 -0.6735 0.08280 0.08003 -0.1004 0.9864 0.0074
-17.250 -0.6904 0.07632 0.07345 -0.1047 0.9821 0.0072
-17.000 -0.7064 0.07010 0.06713 -0.1089 0.9766 0.0074
-16.750 -0.7227 0.06365 0.06058 -0.1140 0.9722 0.0075
-16.500 -0.7350 0.05753 0.05435 -0.1192 0.9665 0.0075
-16.250 -0.7454 0.05099 0.04767 -0.1257 0.9620 0.0075
-16.000 -0.7502 0.04497 0.04152 -0.1323 0.9554 0.0076
-15.750 -0.7468 0.03924 0.03562 -0.1398 0.9493 0.0076
-15.500 -0.7355 0.03446 0.03068 -0.1471 0.9425 0.0077
-15.250 -0.7178 0.03010 0.02614 -0.1552 0.9365 0.0079
-15.000 -0.6930 0.02745 0.02336 -0.1611 0.9315 0.0082
-14.750 -0.6747 0.02511 0.02087 -0.1654 0.9242 0.0083
-14.500 -0.6585 0.02318 0.01877 -0.1682 0.9170 0.0085
-14.250 -0.6483 0.02190 0.01738 -0.1683 0.9098 0.0085
-14.000 -0.6355 0.02093 0.01630 -0.1680 0.9038 0.0087
-13.750 -0.6283 0.02000 0.01527 -0.1664 0.8984 0.0088
-13.500 -0.6209 0.01924 0.01442 -0.1642 0.8930 0.0089
-13.250 -0.6138 0.01849 0.01359 -0.1619 0.8880 0.0092
-13.000 -0.6060 0.01786 0.01289 -0.1592 0.8837 0.0094
-12.750 -0.5969 0.01735 0.01234 -0.1565 0.8794 0.0097
-12.500 -0.5873 0.01687 0.01179 -0.1537 0.8750 0.0099
-12.250 -0.5771 0.01642 0.01127 -0.1509 0.8710 0.0100
-12.000 -0.5663 0.01608 0.01089 -0.1481 0.8673 0.0104
-11.750 -0.5530 0.01568 0.01044 -0.1457 0.8632 0.0107
-11.500 -0.5367 0.01533 0.01002 -0.1439 0.8594 0.0111
-11.250 -0.5197 0.01497 0.00959 -0.1421 0.8556 0.0114
-11.000 -0.5027 0.01459 0.00916 -0.1404 0.8520 0.0117
-10.750 -0.4850 0.01424 0.00879 -0.1387 0.8473 0.0123
-10.500 -0.4661 0.01393 0.00843 -0.1372 0.8421 0.0127
-10.250 -0.4456 0.01366 0.00812 -0.1359 0.8381 0.0133
-10.000 -0.4259 0.01337 0.00779 -0.1345 0.8329 0.0138
-9.750 -0.4053 0.01310 0.00746 -0.1332 0.8278 0.0142
-9.500 -0.3845 0.01282 0.00712 -0.1320 0.8235 0.0147
-9.250 -0.3633 0.01255 0.00684 -0.1308 0.8183 0.0154
-9.000 -0.3409 0.01235 0.00662 -0.1298 0.8132 0.0161
-8.750 -0.3184 0.01216 0.00639 -0.1289 0.8081 0.0168
-8.500 -0.2958 0.01196 0.00615 -0.1279 0.8017 0.0175
-8.250 -0.2742 0.01179 0.00590 -0.1267 0.7937 0.0181
-8.000 -0.2522 0.01156 0.00564 -0.1255 0.7860 0.0188
-7.500 -0.2069 0.01123 0.00523 -0.1235 0.7723 0.0202
-7.000 -0.1614 0.01096 0.00487 -0.1215 0.7564 0.0218
-6.750 -0.1382 0.01084 0.00469 -0.1205 0.7501 0.0224
-6.500 -0.1145 0.01070 0.00451 -0.1197 0.7452 0.0227
-6.250 -0.0926 0.01045 0.00422 -0.1186 0.7389 0.0238
-5.750 -0.0464 0.01017 0.00387 -0.1166 0.7259 0.0254
-5.500 -0.0238 0.01005 0.00370 -0.1155 0.7183 0.0262
-5.250 -0.0010 0.00994 0.00354 -0.1145 0.7098 0.0269
-5.000 0.0218 0.00985 0.00340 -0.1134 0.7020 0.0276
-4.750 0.0454 0.00975 0.00326 -0.1125 0.6949 0.0280
-4.500 0.0675 0.00962 0.00307 -0.1113 0.6865 0.0290
-4.250 0.0884 0.00951 0.00291 -0.1099 0.6729 0.0301
-4.000 0.1094 0.00944 0.00278 -0.1084 0.6586 0.0311
-3.750 0.1275 0.00943 0.00267 -0.1063 0.6364 0.0319
-3.500 0.1144 0.01010 0.00281 -0.0977 0.5159 0.0323
-3.250 0.1285 0.01022 0.00280 -0.0949 0.4881 0.0332
-3.000 0.1419 0.01029 0.00276 -0.0919 0.4642 0.0341
-2.750 0.1572 0.01034 0.00272 -0.0892 0.4450 0.0349
-2.500 0.1732 0.01037 0.00267 -0.0868 0.4253 0.0378
-2.250 0.1881 0.01043 0.00264 -0.0841 0.4020 0.0418
-2.000 0.1996 0.01025 0.00254 -0.0809 0.3814 0.0961
-1.750 0.2113 0.01001 0.00252 -0.0778 0.3639 0.1791
-1.500 0.2295 0.01009 0.00257 -0.0759 0.3512 0.1903
-1.250 0.2478 0.01021 0.00264 -0.0740 0.3381 0.2003
-1.000 0.2670 0.01028 0.00270 -0.0723 0.3295 0.2106
-0.750 0.2877 0.01037 0.00275 -0.0708 0.3231 0.2157
-0.250 0.3284 0.01052 0.00288 -0.0679 0.3126 0.2291
0.000 0.3497 0.01059 0.00294 -0.0667 0.3089 0.2362
0.250 0.3708 0.01065 0.00300 -0.0654 0.3058 0.2440
0.750 0.4117 0.01080 0.00317 -0.0626 0.2992 0.2649
1.000 0.4329 0.01085 0.00325 -0.0613 0.2967 0.2782
1.250 0.4539 0.01088 0.00334 -0.0601 0.2945 0.2992
1.500 0.4750 0.01095 0.00343 -0.0589 0.2925 0.3100
1.750 0.4945 0.01098 0.00355 -0.0574 0.2896 0.3465
2.000 0.5152 0.01105 0.00367 -0.0561 0.2874 0.3657
2.250 0.5353 0.01114 0.00379 -0.0547 0.2847 0.3856
2.500 0.5549 0.01123 0.00393 -0.0533 0.2818 0.4088
2.750 0.5758 0.01129 0.00406 -0.0521 0.2805 0.4341
3.000 0.5960 0.01133 0.00420 -0.0508 0.2786 0.4681
3.250 0.6152 0.01135 0.00435 -0.0493 0.2761 0.5161
3.500 0.6325 0.01137 0.00454 -0.0474 0.2719 0.5795
3.750 0.6482 0.01133 0.00474 -0.0452 0.2692 0.6669
4.000 0.6582 0.01111 0.00497 -0.0417 0.2664 0.8107
4.250 0.8450 0.01125 0.00539 -0.0770 0.2564 0.9807
4.500 0.8716 0.01152 0.00562 -0.0772 0.2520 0.9926
4.750 0.8988 0.01184 0.00591 -0.0774 0.2468 0.9997
5.000 0.9185 0.01212 0.00614 -0.0763 0.2386 1.0000
5.250 0.9336 0.01247 0.00641 -0.0742 0.2235 1.0000
5.500 0.9365 0.01337 0.00703 -0.0702 0.1751 1.0000
5.750 0.9513 0.01381 0.00742 -0.0682 0.1659 1.0000
6.000 0.9687 0.01417 0.00775 -0.0666 0.1606 1.0000
6.250 0.9870 0.01451 0.00806 -0.0653 0.1574 1.0000
6.500 1.0053 0.01485 0.00840 -0.0639 0.1551 1.0000
6.750 1.0236 0.01521 0.00874 -0.0626 0.1529 1.0000
7.000 1.0429 0.01553 0.00907 -0.0615 0.1516 1.0000
7.250 1.0622 0.01587 0.00941 -0.0604 0.1504 1.0000
7.500 1.0802 0.01627 0.00981 -0.0592 0.1470 1.0000
7.750 1.0997 0.01662 0.01017 -0.0582 0.1456 1.0000
8.000 1.1195 0.01695 0.01052 -0.0573 0.1446 1.0000
8.250 1.1388 0.01731 0.01089 -0.0563 0.1431 1.0000
8.500 1.1577 0.01770 0.01129 -0.0553 0.1418 1.0000
8.750 1.1763 0.01812 0.01172 -0.0543 0.1400 1.0000
9.000 1.1947 0.01855 0.01216 -0.0533 0.1383 1.0000
9.250 1.2116 0.01907 0.01268 -0.0521 0.1351 1.0000
9.500 1.2289 0.01958 0.01319 -0.0510 0.1320 1.0000
9.750 1.2481 0.01999 0.01363 -0.0502 0.1305 1.0000
10.000 1.2660 0.02047 0.01412 -0.0492 0.1270 1.0000
10.250 1.2811 0.02113 0.01473 -0.0479 0.1208 1.0000
10.500 1.2821 0.02265 0.01599 -0.0451 0.0812 1.0000
10.750 1.2899 0.02379 0.01711 -0.0430 0.0696 1.0000
11.000 1.2837 0.02586 0.01903 -0.0396 0.0357 1.0000
11.250 1.2854 0.02751 0.02063 -0.0371 0.0176 1.0000
11.500 1.2964 0.02856 0.02170 -0.0358 0.0146 1.0000
11.750 1.3069 0.02966 0.02283 -0.0345 0.0129 1.0000
12.000 1.3184 0.03073 0.02394 -0.0333 0.0119 1.0000
12.250 1.3293 0.03186 0.02511 -0.0322 0.0112 1.0000
12.500 1.3398 0.03305 0.02634 -0.0311 0.0106 1.0000
12.750 1.3485 0.03441 0.02773 -0.0299 0.0098 1.0000
13.000 1.3567 0.03583 0.02920 -0.0287 0.0093 1.0000
13.250 1.3661 0.03719 0.03062 -0.0278 0.0091 1.0000
13.500 1.3740 0.03871 0.03218 -0.0268 0.0086 1.0000
13.750 1.3815 0.04030 0.03383 -0.0258 0.0083 1.0000
14.000 1.3877 0.04204 0.03562 -0.0249 0.0080 1.0000
14.250 1.3921 0.04399 0.03762 -0.0239 0.0075 1.0000
14.500 1.3954 0.04607 0.03976 -0.0231 0.0071 1.0000
14.750 1.3980 0.04830 0.04205 -0.0223 0.0070 1.0000
15.000 1.4021 0.05044 0.04426 -0.0217 0.0068 1.0000
15.250 1.4043 0.05284 0.04673 -0.0211 0.0065 1.0000
15.500 1.4045 0.05552 0.04950 -0.0207 0.0064 1.0000
15.750 1.4042 0.05833 0.05238 -0.0204 0.0062 1.0000
16.000 1.4023 0.06142 0.05555 -0.0202 0.0061 1.0000
16.250 1.3988 0.06481 0.05903 -0.0203 0.0060 1.0000
16.500 1.3936 0.06852 0.06283 -0.0205 0.0058 1.0000
16.750 1.3890 0.07224 0.06663 -0.0208 0.0057 1.0000
17.000 1.3810 0.07642 0.07091 -0.0213 0.0057 1.0000
17.250 1.3694 0.08116 0.07574 -0.0220 0.0053 1.0000
17.500 1.3612 0.08552 0.08021 -0.0228 0.0053 1.0000
17.750 1.3496 0.09038 0.08517 -0.0237 0.0054 1.0000
18.000 1.3358 0.09559 0.09049 -0.0248 0.0053 1.0000
18.250 1.3250 0.10043 0.09543 -0.0260 0.0051 1.0000
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