GOE 493 AIRFOIL (goe493-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 493 AIRFOIL (goe493-il) Reynolds number: 50,000 Max Cl/Cd: 24.39 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe493-il-50000-n5.txt Download as CSV file: xf-goe493-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 493 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4301 0.10851 0.10116 -0.0594 1.0000 0.0703
-11.750 -0.4511 0.10172 0.09449 -0.0614 1.0000 0.0709
-11.500 -0.4806 0.09338 0.08627 -0.0642 1.0000 0.0712
-11.250 -0.5178 0.08461 0.07761 -0.0674 1.0000 0.0710
-11.000 -0.5564 0.07712 0.07018 -0.0697 1.0000 0.0702
-10.750 -0.5964 0.07103 0.06409 -0.0709 1.0000 0.0691
-10.500 -0.6388 0.06631 0.05936 -0.0703 1.0000 0.0680
-10.250 -0.6824 0.06300 0.05601 -0.0672 1.0000 0.0667
-10.000 -0.7159 0.06002 0.05292 -0.0635 1.0000 0.0664
-9.750 -0.7386 0.05715 0.04988 -0.0604 1.0000 0.0669
-9.500 -0.7555 0.05426 0.04676 -0.0575 1.0000 0.0684
-9.250 -0.7679 0.05120 0.04335 -0.0548 1.0000 0.0702
-9.000 -0.7727 0.04857 0.04043 -0.0524 1.0000 0.0728
-8.750 -0.7597 0.04731 0.03917 -0.0518 0.9978 0.0767
-8.500 -0.7422 0.04430 0.03556 -0.0531 0.9920 0.0831
-8.250 -0.7182 0.04309 0.03437 -0.0542 0.9865 0.0897
-8.000 -0.6968 0.04114 0.03203 -0.0551 0.9809 0.0985
-7.750 -0.6725 0.03978 0.03043 -0.0561 0.9751 0.1084
-7.500 -0.6486 0.03870 0.02929 -0.0568 0.9695 0.1182
-7.250 -0.6238 0.03749 0.02789 -0.0575 0.9637 0.1296
-7.000 -0.5975 0.03641 0.02656 -0.0583 0.9582 0.1420
-6.750 -0.5738 0.03554 0.02544 -0.0585 0.9519 0.1545
-6.500 -0.5436 0.03480 0.02463 -0.0599 0.9469 0.1680
-6.250 -0.5217 0.03411 0.02389 -0.0595 0.9402 0.1797
-6.000 -0.4937 0.03342 0.02307 -0.0603 0.9345 0.1932
-5.750 -0.4644 0.03279 0.02233 -0.0612 0.9293 0.2077
-5.500 -0.4418 0.03221 0.02165 -0.0608 0.9222 0.2211
-5.250 -0.4111 0.03167 0.02106 -0.0618 0.9171 0.2376
-5.000 -0.3867 0.03119 0.02053 -0.0617 0.9106 0.2539
-4.750 -0.3609 0.03076 0.02010 -0.0618 0.9041 0.2730
-4.500 -0.3277 0.03034 0.01964 -0.0632 0.8995 0.2983
-4.250 -0.3083 0.03005 0.01943 -0.0621 0.8916 0.3203
-4.000 -0.2786 0.02978 0.01921 -0.0628 0.8860 0.3518
-3.750 -0.2525 0.02963 0.01909 -0.0627 0.8799 0.3839
-3.500 -0.2300 0.02955 0.01903 -0.0619 0.8726 0.4162
-3.250 -0.1982 0.02948 0.01898 -0.0626 0.8678 0.4528
-3.000 -0.1812 0.02955 0.01905 -0.0609 0.8595 0.4824
-2.750 -0.1527 0.02955 0.01903 -0.0609 0.8539 0.5159
-2.500 -0.1301 0.02962 0.01908 -0.0600 0.8471 0.5463
-2.250 -0.1074 0.02970 0.01916 -0.0590 0.8402 0.5749
-2.000 -0.0752 0.02966 0.01911 -0.0595 0.8359 0.6055
-1.750 -0.0612 0.02984 0.01930 -0.0571 0.8269 0.6303
-1.500 -0.0324 0.02984 0.01931 -0.0570 0.8218 0.6582
-1.250 -0.0133 0.02999 0.01948 -0.0554 0.8145 0.6836
-1.000 0.0103 0.03005 0.01955 -0.0544 0.8080 0.7115
-0.750 0.0422 0.02998 0.01951 -0.0546 0.8041 0.7413
-0.500 0.0537 0.03026 0.01983 -0.0519 0.7947 0.7687
-0.250 0.0847 0.03019 0.01979 -0.0521 0.7900 0.8016
0.000 0.1071 0.03038 0.02004 -0.0512 0.7827 0.8360
0.250 0.1451 0.03051 0.02021 -0.0532 0.7770 0.8768
0.500 0.2076 0.03057 0.02025 -0.0598 0.7738 0.9207
0.750 0.2600 0.03094 0.02059 -0.0658 0.7670 0.9811
1.000 0.2873 0.03114 0.02063 -0.0669 0.7604 1.0000
1.250 0.3216 0.03105 0.02039 -0.0683 0.7564 1.0000
1.500 0.3256 0.03173 0.02095 -0.0654 0.7452 1.0000
1.750 0.3612 0.03167 0.02078 -0.0668 0.7411 1.0000
2.000 0.3691 0.03237 0.02140 -0.0644 0.7300 1.0000
2.250 0.4054 0.03224 0.02120 -0.0656 0.7256 1.0000
2.500 0.4158 0.03291 0.02181 -0.0634 0.7143 1.0000
2.750 0.4536 0.03264 0.02149 -0.0647 0.7098 1.0000
3.000 0.4645 0.03333 0.02214 -0.0625 0.6981 1.0000
3.250 0.5028 0.03298 0.02177 -0.0637 0.6938 1.0000
3.500 0.5122 0.03381 0.02258 -0.0614 0.6821 1.0000
3.750 0.5504 0.03344 0.02221 -0.0625 0.6780 1.0000
4.000 0.5586 0.03439 0.02318 -0.0602 0.6661 1.0000
4.250 0.5964 0.03405 0.02286 -0.0612 0.6621 1.0000
4.500 0.6040 0.03508 0.02390 -0.0588 0.6501 1.0000
4.750 0.6426 0.03466 0.02354 -0.0598 0.6461 1.0000
5.000 0.6489 0.03581 0.02473 -0.0574 0.6339 1.0000
5.250 0.6881 0.03536 0.02435 -0.0584 0.6301 1.0000
5.500 0.6939 0.03656 0.02560 -0.0560 0.6175 1.0000
5.750 0.7337 0.03604 0.02516 -0.0569 0.6137 1.0000
6.000 0.7386 0.03734 0.02653 -0.0545 0.6010 1.0000
6.500 0.7829 0.03818 0.02756 -0.0529 0.5843 1.0000
6.750 0.7908 0.03948 0.02894 -0.0510 0.5726 1.0000
7.000 0.8271 0.03904 0.02866 -0.0514 0.5675 1.0000
7.250 0.8309 0.04063 0.03034 -0.0492 0.5551 1.0000
7.500 0.8701 0.04003 0.02989 -0.0497 0.5508 1.0000
7.750 0.8702 0.04191 0.03187 -0.0473 0.5378 1.0000
8.000 0.9131 0.04100 0.03116 -0.0480 0.5338 1.0000
8.250 0.9132 0.04280 0.03306 -0.0455 0.5204 1.0000
8.500 0.9192 0.04417 0.03455 -0.0435 0.5075 1.0000
8.750 0.9413 0.04413 0.03466 -0.0422 0.4962 1.0000
9.000 0.9910 0.04172 0.03246 -0.0422 0.4864 1.0000
9.250 1.0097 0.04140 0.03224 -0.0402 0.4701 1.0000
9.500 1.0084 0.04255 0.03349 -0.0371 0.4508 1.0000
9.750 1.0207 0.04213 0.03309 -0.0342 0.4260 1.0000
10.000 1.0227 0.04293 0.03394 -0.0314 0.4003 1.0000
10.250 1.0300 0.04341 0.03438 -0.0289 0.3717 1.0000
10.500 1.0385 0.04410 0.03502 -0.0267 0.3441 1.0000
10.750 1.0410 0.04558 0.03649 -0.0247 0.3167 1.0000
11.000 1.0404 0.04747 0.03836 -0.0228 0.2861 1.0000
11.250 1.0367 0.04981 0.04066 -0.0211 0.2489 1.0000
11.500 1.0311 0.05243 0.04304 -0.0195 0.2043 1.0000
11.750 1.0217 0.05559 0.04582 -0.0180 0.1726 1.0000
12.000 1.0119 0.05912 0.04908 -0.0170 0.1516 1.0000
12.250 1.0053 0.06256 0.05234 -0.0162 0.1354 1.0000
12.500 1.0016 0.06581 0.05555 -0.0156 0.1225 1.0000
12.750 1.0016 0.06875 0.05848 -0.0151 0.1122 1.0000
13.000 1.0029 0.07154 0.06124 -0.0146 0.1048 1.0000
13.250 1.0076 0.07399 0.06372 -0.0140 0.0986 1.0000
13.500 1.0140 0.07623 0.06594 -0.0134 0.0938 1.0000
13.750 1.0224 0.07837 0.06821 -0.0129 0.0884 1.0000
14.000 1.0312 0.08035 0.07018 -0.0123 0.0841 1.0000
14.250 1.0443 0.08205 0.07201 -0.0115 0.0803 1.0000
14.500 1.0575 0.08388 0.07405 -0.0108 0.0769 1.0000
14.750 1.0699 0.08574 0.07600 -0.0103 0.0736 1.0000
15.000 1.0878 0.08702 0.07726 -0.0094 0.0701 1.0000
15.250 1.0913 0.09035 0.08093 -0.0096 0.0680 1.0000
15.500 1.0934 0.09387 0.08474 -0.0099 0.0661 1.0000
15.750 1.0926 0.09771 0.08884 -0.0105 0.0643 1.0000
16.000 1.0917 0.10152 0.09282 -0.0113 0.0626 1.0000
16.250 1.0962 0.10453 0.09590 -0.0117 0.0607 1.0000
16.500 1.0940 0.10873 0.10022 -0.0128 0.0595 1.0000
16.750 1.0751 0.11553 0.10732 -0.0157 0.0591 1.0000
17.000 1.0546 0.12301 0.11507 -0.0194 0.0589 1.0000
17.250 1.0296 0.13188 0.12417 -0.0242 0.0589 1.0000
17.500 1.0006 0.14244 0.13493 -0.0305 0.0591 1.0000
17.750 0.9702 0.15462 0.14721 -0.0378 0.0594 1.0000
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