GOE 633 AIRFOIL (goe633-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 633 AIRFOIL (goe633-il) Reynolds number: 200,000 Max Cl/Cd: 67.38 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe633-il-200000.txt Download as CSV file: xf-goe633-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3109 0.11205 0.10851 -0.0264 1.0000 0.0797
-10.500 -0.3051 0.10915 0.10565 -0.0276 1.0000 0.0821
-10.250 -0.3466 0.10359 0.10021 -0.0374 1.0000 0.0862
-10.000 -0.3238 0.10062 0.09727 -0.0351 1.0000 0.0870
-9.750 -0.3051 0.09847 0.09516 -0.0339 1.0000 0.0881
-9.250 -0.2973 0.08597 0.08257 -0.0580 0.9036 0.0975
-9.000 -0.2595 0.08296 0.07943 -0.0571 0.8851 0.0985
-8.750 -0.2350 0.08039 0.07674 -0.0579 0.8667 0.0997
-8.500 -0.4269 0.04731 0.04300 -0.0742 0.8452 0.0681
-8.250 -0.4866 0.03620 0.03043 -0.0686 0.8337 0.0592
-8.000 -0.4750 0.03359 0.02756 -0.0670 0.8248 0.0587
-7.750 -0.4630 0.03124 0.02490 -0.0651 0.8161 0.0584
-7.500 -0.4487 0.02924 0.02256 -0.0632 0.8083 0.0582
-7.250 -0.4322 0.02768 0.02066 -0.0615 0.8003 0.0585
-7.000 -0.4135 0.02642 0.01904 -0.0599 0.7940 0.0588
-6.750 -0.3930 0.02524 0.01760 -0.0586 0.7863 0.0591
-6.500 -0.3711 0.02388 0.01601 -0.0575 0.7797 0.0593
-6.250 -0.3478 0.02258 0.01457 -0.0567 0.7732 0.0597
-6.000 -0.3235 0.02154 0.01344 -0.0559 0.7664 0.0602
-5.750 -0.2987 0.02069 0.01251 -0.0552 0.7609 0.0609
-5.500 -0.2738 0.01998 0.01177 -0.0545 0.7546 0.0618
-5.250 -0.2488 0.01935 0.01108 -0.0538 0.7480 0.0629
-5.000 -0.2236 0.01883 0.01047 -0.0530 0.7428 0.0645
-4.750 -0.1983 0.01836 0.00996 -0.0523 0.7368 0.0662
-4.500 -0.1736 0.01780 0.00937 -0.0515 0.7305 0.0679
-4.250 -0.1490 0.01730 0.00887 -0.0506 0.7254 0.0700
-4.000 -0.1241 0.01695 0.00852 -0.0498 0.7193 0.0728
-3.750 -0.0991 0.01658 0.00812 -0.0489 0.7121 0.0765
-3.500 -0.0738 0.01620 0.00770 -0.0480 0.7059 0.0828
-3.250 -0.0489 0.01580 0.00739 -0.0472 0.6974 0.0970
-3.000 -0.0242 0.01520 0.00707 -0.0464 0.6910 0.1466
-2.750 0.0026 0.01529 0.00718 -0.0458 0.6857 0.1863
-2.500 0.0288 0.01538 0.00726 -0.0453 0.6788 0.2047
-2.250 0.0555 0.01543 0.00722 -0.0447 0.6732 0.2196
-2.000 0.0820 0.01548 0.00720 -0.0441 0.6681 0.2330
-1.750 0.1076 0.01543 0.00721 -0.0436 0.6610 0.2454
-1.500 0.1343 0.01535 0.00708 -0.0430 0.6554 0.2578
-1.250 0.1612 0.01535 0.00698 -0.0425 0.6505 0.2708
-1.000 0.1866 0.01522 0.00696 -0.0420 0.6431 0.2837
-0.750 0.2132 0.01507 0.00681 -0.0414 0.6372 0.2979
-0.500 0.2400 0.01496 0.00667 -0.0410 0.6317 0.3113
-0.250 0.2659 0.01484 0.00660 -0.0404 0.6243 0.3232
0.000 0.2929 0.01461 0.00639 -0.0400 0.6185 0.3342
0.250 0.3191 0.01449 0.00628 -0.0394 0.6121 0.3465
0.500 0.3447 0.01430 0.00617 -0.0388 0.6045 0.3613
0.750 0.3709 0.01406 0.00597 -0.0381 0.5987 0.3819
1.000 0.3936 0.01379 0.00596 -0.0370 0.5904 0.4188
1.250 0.5988 0.01273 0.00622 -0.0715 0.5751 1.0000
1.500 0.6235 0.01274 0.00612 -0.0707 0.5667 1.0000
1.750 0.6478 0.01278 0.00609 -0.0698 0.5578 1.0000
2.000 0.6723 0.01280 0.00601 -0.0689 0.5487 1.0000
2.250 0.6962 0.01287 0.00603 -0.0681 0.5388 1.0000
2.500 0.7207 0.01292 0.00596 -0.0672 0.5299 1.0000
2.750 0.7442 0.01301 0.00603 -0.0662 0.5189 1.0000
3.000 0.7682 0.01311 0.00602 -0.0653 0.5092 1.0000
3.250 0.7915 0.01319 0.00605 -0.0643 0.4975 1.0000
3.500 0.8146 0.01331 0.00613 -0.0633 0.4856 1.0000
3.750 0.8377 0.01344 0.00616 -0.0623 0.4747 1.0000
4.000 0.8605 0.01358 0.00625 -0.0613 0.4637 1.0000
4.250 0.8833 0.01377 0.00641 -0.0602 0.4534 1.0000
4.500 0.9062 0.01398 0.00650 -0.0592 0.4445 1.0000
4.750 0.9283 0.01418 0.00673 -0.0581 0.4344 1.0000
5.000 0.9509 0.01443 0.00686 -0.0571 0.4264 1.0000
5.250 0.9728 0.01466 0.00714 -0.0560 0.4179 1.0000
5.750 1.0163 0.01518 0.00759 -0.0537 0.4021 1.0000
6.000 1.0379 0.01546 0.00778 -0.0526 0.3949 1.0000
6.250 1.0585 0.01573 0.00810 -0.0513 0.3870 1.0000
6.500 1.0795 0.01602 0.00835 -0.0500 0.3801 1.0000
6.750 1.1003 0.01636 0.00868 -0.0488 0.3739 1.0000
7.000 1.1204 0.01666 0.00902 -0.0474 0.3674 1.0000
7.250 1.1414 0.01702 0.00930 -0.0462 0.3617 1.0000
7.500 1.1607 0.01736 0.00971 -0.0448 0.3558 1.0000
7.750 1.1799 0.01768 0.01008 -0.0433 0.3497 1.0000
8.250 1.2176 0.01843 0.01086 -0.0403 0.3380 1.0000
8.500 1.2354 0.01878 0.01124 -0.0386 0.3319 1.0000
8.750 1.2543 0.01922 0.01163 -0.0372 0.3260 1.0000
9.000 1.2690 0.01956 0.01210 -0.0350 0.3194 1.0000
9.250 1.2856 0.01995 0.01246 -0.0332 0.3130 1.0000
9.500 1.2996 0.02037 0.01296 -0.0310 0.3062 1.0000
9.750 1.3122 0.02075 0.01340 -0.0285 0.2990 1.0000
10.000 1.3253 0.02121 0.01385 -0.0262 0.2919 1.0000
10.250 1.3330 0.02161 0.01435 -0.0230 0.2836 1.0000
10.500 1.3413 0.02212 0.01484 -0.0201 0.2756 1.0000
10.750 1.3414 0.02258 0.01539 -0.0157 0.2669 1.0000
11.000 1.3419 0.02317 0.01597 -0.0117 0.2586 1.0000
11.250 1.3415 0.02389 0.01672 -0.0080 0.2494 1.0000
11.500 1.3424 0.02481 0.01768 -0.0049 0.2398 1.0000
11.750 1.3447 0.02586 0.01865 -0.0024 0.2316 1.0000
12.000 1.3473 0.02706 0.01994 -0.0002 0.2226 1.0000
12.250 1.3517 0.02829 0.02107 0.0016 0.2156 1.0000
12.500 1.3562 0.02962 0.02251 0.0032 0.2085 1.0000
12.750 1.3618 0.03091 0.02373 0.0047 0.2027 1.0000
13.000 1.3673 0.03231 0.02520 0.0060 0.1970 1.0000
13.250 1.3720 0.03377 0.02669 0.0072 0.1915 1.0000
13.500 1.3781 0.03516 0.02801 0.0084 0.1862 1.0000
13.750 1.3816 0.03683 0.02980 0.0093 0.1814 1.0000
14.000 1.3852 0.03849 0.03148 0.0102 0.1766 1.0000
14.250 1.3937 0.03981 0.03273 0.0112 0.1723 1.0000
14.500 1.3969 0.04163 0.03470 0.0119 0.1688 1.0000
14.750 1.4010 0.04339 0.03654 0.0126 0.1652 1.0000
15.000 1.4073 0.04495 0.03810 0.0133 0.1617 1.0000
15.250 1.4165 0.04630 0.03942 0.0141 0.1582 1.0000
15.500 1.4163 0.04856 0.04185 0.0145 0.1552 1.0000
15.750 1.4172 0.05075 0.04414 0.0148 0.1517 1.0000
16.000 1.4210 0.05268 0.04610 0.0151 0.1484 1.0000
16.250 1.4295 0.05415 0.04753 0.0157 0.1447 1.0000
16.500 1.4233 0.05730 0.05087 0.0154 0.1416 1.0000
16.750 1.4215 0.06005 0.05374 0.0152 0.1383 1.0000
17.000 1.4227 0.06246 0.05617 0.0151 0.1349 1.0000
17.250 1.4295 0.06417 0.05786 0.0154 0.1314 1.0000
17.500 1.4213 0.06793 0.06184 0.0146 0.1288 1.0000
17.750 1.4166 0.07134 0.06538 0.0138 0.1258 1.0000
18.000 1.4144 0.07440 0.06852 0.0132 0.1227 1.0000
18.250 1.4178 0.07662 0.07069 0.0130 0.1187 1.0000
18.500 1.4048 0.08143 0.07572 0.0114 0.1160 1.0000
18.750 1.3948 0.08591 0.08035 0.0098 0.1126 1.0000
19.000 1.3897 0.08963 0.08410 0.0085 0.1088 1.0000
19.250 1.3813 0.09394 0.08851 0.0070 0.1052 1.0000
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Polar data table (+)
Polar graphs
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