GOE 633 AIRFOIL (goe633-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 633 AIRFOIL (goe633-il) Reynolds number: 50,000 Max Cl/Cd: 26.5 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe633-il-50000-n5.txt Download as CSV file: xf-goe633-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 633 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3152 0.10412 0.09698 -0.0340 1.0000 0.0813
-9.750 -0.3156 0.10028 0.09322 -0.0359 1.0000 0.0809
-9.500 -0.3174 0.09636 0.08939 -0.0378 1.0000 0.0806
-9.250 -0.3219 0.09220 0.08533 -0.0400 1.0000 0.0801
-9.000 -0.3500 0.08488 0.07816 -0.0454 1.0000 0.0780
-8.750 -0.3585 0.08158 0.07500 -0.0464 1.0000 0.0777
-8.500 -0.3721 0.07838 0.07196 -0.0475 0.9884 0.0773
-8.250 -0.3687 0.07193 0.06543 -0.0547 0.9577 0.0768
-8.000 -0.3688 0.06415 0.05746 -0.0622 0.9373 0.0763
-7.750 -0.3732 0.05695 0.04992 -0.0671 0.9197 0.0760
-7.500 -0.3741 0.05110 0.04362 -0.0696 0.9050 0.0760
-7.250 -0.3725 0.04647 0.03847 -0.0700 0.8910 0.0765
-7.000 -0.3666 0.04258 0.03395 -0.0696 0.8791 0.0777
-6.750 -0.3459 0.04083 0.03202 -0.0695 0.8698 0.0794
-6.500 -0.3288 0.03935 0.03034 -0.0687 0.8591 0.0812
-6.250 -0.3089 0.03749 0.02813 -0.0681 0.8509 0.0833
-6.000 -0.2927 0.03577 0.02606 -0.0668 0.8407 0.0850
-5.750 -0.2704 0.03398 0.02381 -0.0661 0.8336 0.0872
-5.500 -0.2513 0.03288 0.02254 -0.0649 0.8240 0.0893
-5.250 -0.2270 0.03198 0.02153 -0.0643 0.8170 0.0925
-5.000 -0.2065 0.03115 0.02049 -0.0632 0.8081 0.0973
-4.750 -0.1821 0.03034 0.01958 -0.0625 0.8011 0.1034
-4.500 -0.1593 0.02965 0.01875 -0.0617 0.7932 0.1113
-4.250 -0.1352 0.02902 0.01813 -0.0609 0.7857 0.1208
-4.000 -0.1102 0.02852 0.01765 -0.0603 0.7789 0.1366
-3.750 -0.0874 0.02840 0.01757 -0.0594 0.7707 0.1592
-3.500 -0.0618 0.02840 0.01744 -0.0587 0.7646 0.1851
-3.250 -0.0422 0.02863 0.01759 -0.0574 0.7558 0.2071
-3.000 -0.0216 0.02892 0.01788 -0.0559 0.7490 0.2323
-2.750 -0.0034 0.02922 0.01813 -0.0543 0.7409 0.2573
-2.500 0.0200 0.02920 0.01802 -0.0534 0.7333 0.2778
-2.250 0.0494 0.02892 0.01766 -0.0534 0.7265 0.2924
-2.000 0.0774 0.02873 0.01737 -0.0534 0.7172 0.3041
-1.750 0.1120 0.02832 0.01679 -0.0540 0.7109 0.3181
-1.500 0.1365 0.02830 0.01671 -0.0536 0.7000 0.3315
-1.250 0.1687 0.02790 0.01625 -0.0537 0.6932 0.3469
-1.000 0.1919 0.02789 0.01629 -0.0530 0.6826 0.3619
-0.750 0.2221 0.02753 0.01591 -0.0528 0.6758 0.3818
-0.500 0.2441 0.02755 0.01603 -0.0520 0.6657 0.4029
-0.250 0.2719 0.02717 0.01576 -0.0514 0.6587 0.4292
0.000 0.2928 0.02708 0.01589 -0.0503 0.6493 0.4628
0.250 0.3164 0.02646 0.01569 -0.0491 0.6420 0.5342
0.750 0.4963 0.02557 0.01524 -0.0707 0.6230 1.0000
1.000 0.5156 0.02599 0.01555 -0.0694 0.6129 1.0000
1.250 0.5393 0.02606 0.01544 -0.0681 0.6055 1.0000
1.500 0.5577 0.02653 0.01583 -0.0667 0.5953 1.0000
1.750 0.5815 0.02659 0.01573 -0.0654 0.5880 1.0000
2.000 0.5992 0.02710 0.01619 -0.0639 0.5777 1.0000
2.250 0.6231 0.02714 0.01609 -0.0626 0.5706 1.0000
2.500 0.6399 0.02771 0.01664 -0.0610 0.5602 1.0000
2.750 0.6640 0.02775 0.01656 -0.0598 0.5532 1.0000
3.000 0.6798 0.02839 0.01719 -0.0581 0.5428 1.0000
3.250 0.7040 0.02843 0.01712 -0.0568 0.5360 1.0000
3.500 0.7187 0.02916 0.01787 -0.0551 0.5258 1.0000
3.750 0.7424 0.02927 0.01788 -0.0538 0.5192 1.0000
4.000 0.7564 0.03005 0.01868 -0.0520 0.5096 1.0000
4.250 0.7788 0.03024 0.01881 -0.0507 0.5028 1.0000
4.500 0.7933 0.03100 0.01958 -0.0489 0.4941 1.0000
4.750 0.8127 0.03143 0.01997 -0.0474 0.4870 1.0000
5.000 0.8324 0.03188 0.02039 -0.0459 0.4806 1.0000
5.250 0.8436 0.03284 0.02141 -0.0439 0.4721 1.0000
5.500 0.8701 0.03283 0.02133 -0.0430 0.4671 1.0000
5.750 0.8729 0.03434 0.02293 -0.0402 0.4580 1.0000
6.000 0.8946 0.03465 0.02322 -0.0390 0.4523 1.0000
6.250 0.9063 0.03562 0.02422 -0.0370 0.4457 1.0000
6.500 0.9142 0.03677 0.02543 -0.0347 0.4384 1.0000
6.750 0.9435 0.03662 0.02523 -0.0340 0.4339 1.0000
7.000 0.9327 0.03890 0.02763 -0.0303 0.4250 1.0000
7.250 0.9551 0.03907 0.02781 -0.0291 0.4193 1.0000
7.500 0.9575 0.04039 0.02917 -0.0263 0.4115 1.0000
7.750 0.9722 0.04077 0.02955 -0.0243 0.4036 1.0000
8.000 0.9796 0.04160 0.03039 -0.0218 0.3954 1.0000
8.250 0.9917 0.04196 0.03075 -0.0195 0.3870 1.0000
8.500 0.9923 0.04307 0.03188 -0.0165 0.3788 1.0000
8.750 1.0005 0.04379 0.03261 -0.0142 0.3706 1.0000
9.000 1.0086 0.04473 0.03355 -0.0122 0.3633 1.0000
9.250 0.9967 0.04734 0.03623 -0.0099 0.3549 1.0000
9.500 1.0503 0.04499 0.03385 -0.0095 0.3502 1.0000
9.750 0.9894 0.05197 0.04099 -0.0068 0.3390 1.0000
10.000 1.0371 0.04956 0.03856 -0.0056 0.3345 1.0000
10.250 0.9818 0.05719 0.04632 -0.0047 0.3223 1.0000
10.500 1.0250 0.05485 0.04399 -0.0031 0.3181 1.0000
10.750 0.9718 0.06320 0.05245 -0.0034 0.3050 1.0000
11.000 1.0096 0.06123 0.05052 -0.0016 0.3013 1.0000
11.250 0.9581 0.07024 0.05961 -0.0029 0.2873 1.0000
11.500 0.9957 0.06800 0.05742 -0.0009 0.2841 1.0000
12.000 0.9128 0.08555 0.07507 -0.0049 0.2568 1.0000
12.250 0.9344 0.08522 0.07479 -0.0035 0.2527 1.0000
12.500 0.9674 0.08318 0.07280 -0.0015 0.2505 1.0000
13.000 0.8751 0.10541 0.09509 -0.0090 0.2259 1.0000
13.250 0.8836 0.10763 0.09736 -0.0089 0.2222 1.0000
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Polar data table (+)
Polar graphs
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