GOE 632 AIRFOIL (goe632-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 632 AIRFOIL (goe632-il) Reynolds number: 500,000 Max Cl/Cd: 98.84 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe632-il-500000.txt Download as CSV file: xf-goe632-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 632 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3201 0.09625 0.09399 -0.0449 1.0000 0.0372
-10.000 -0.3263 0.09303 0.09081 -0.0452 1.0000 0.0379
-9.750 -0.3467 0.07885 0.07664 -0.0618 0.9922 0.0401
-9.500 -0.3306 0.07560 0.07340 -0.0652 0.9849 0.0404
-9.250 -0.3170 0.07202 0.06981 -0.0696 0.9733 0.0408
-9.000 -0.3033 0.06766 0.06542 -0.0758 0.9601 0.0414
-8.750 -0.2886 0.06162 0.05928 -0.0847 0.9456 0.0422
-8.500 -0.3303 0.04556 0.04231 -0.0942 0.9076 0.0465
-8.250 -0.3066 0.04326 0.03996 -0.0956 0.8892 0.0469
-8.000 -0.2930 0.04156 0.03814 -0.0946 0.8697 0.0473
-7.750 -0.2818 0.04014 0.03658 -0.0930 0.8533 0.0477
-7.500 -0.3484 0.02864 0.02365 -0.0786 0.8350 0.0399
-7.250 -0.3322 0.02683 0.02173 -0.0769 0.8237 0.0391
-7.000 -0.3233 0.02453 0.01914 -0.0738 0.8124 0.0386
-6.750 -0.3109 0.02247 0.01676 -0.0711 0.8020 0.0383
-6.500 -0.2957 0.02075 0.01472 -0.0687 0.7913 0.0384
-6.250 -0.2770 0.01948 0.01319 -0.0668 0.7810 0.0387
-6.000 -0.2561 0.01857 0.01203 -0.0653 0.7710 0.0391
-5.750 -0.2343 0.01777 0.01105 -0.0640 0.7604 0.0394
-5.500 -0.2111 0.01701 0.01010 -0.0630 0.7512 0.0397
-5.250 -0.1854 0.01564 0.00860 -0.0627 0.7415 0.0401
-5.000 -0.1599 0.01487 0.00775 -0.0622 0.7328 0.0407
-4.750 -0.1349 0.01435 0.00718 -0.0616 0.7235 0.0413
-4.500 -0.1099 0.01394 0.00672 -0.0609 0.7152 0.0420
-4.250 -0.0851 0.01356 0.00628 -0.0602 0.7067 0.0427
-4.000 -0.0602 0.01324 0.00590 -0.0595 0.6990 0.0438
-3.750 -0.0353 0.01292 0.00552 -0.0588 0.6913 0.0449
-3.500 -0.0106 0.01265 0.00517 -0.0581 0.6844 0.0457
-3.250 0.0132 0.01218 0.00467 -0.0572 0.6773 0.0468
-3.000 0.0367 0.01189 0.00435 -0.0562 0.6705 0.0482
-2.750 0.0610 0.01169 0.00415 -0.0554 0.6641 0.0499
-2.500 0.0853 0.01153 0.00395 -0.0545 0.6576 0.0518
-2.250 0.1094 0.01136 0.00371 -0.0537 0.6519 0.0540
-2.000 0.1334 0.01115 0.00356 -0.0528 0.6459 0.0579
-1.750 0.1581 0.01107 0.00343 -0.0520 0.6399 0.0625
-1.500 0.1819 0.01089 0.00326 -0.0511 0.6343 0.0703
-1.250 0.2055 0.01068 0.00309 -0.0502 0.6286 0.0806
-1.000 0.2293 0.01054 0.00295 -0.0493 0.6230 0.0914
-0.750 0.2534 0.01044 0.00285 -0.0484 0.6176 0.1045
-0.500 0.2754 0.01018 0.00278 -0.0472 0.6117 0.1468
-0.250 0.2892 0.00950 0.00275 -0.0446 0.6061 0.3463
0.000 0.3053 0.00915 0.00272 -0.0422 0.6010 0.4586
0.250 0.3722 0.00813 0.00318 -0.0503 0.5944 0.9070
0.500 0.4190 0.00879 0.00376 -0.0535 0.5877 0.9303
0.750 0.4567 0.00924 0.00416 -0.0551 0.5809 0.9424
1.000 0.5304 0.00990 0.00470 -0.0643 0.5701 0.9497
1.250 0.5615 0.01012 0.00489 -0.0648 0.5629 0.9572
1.500 0.6040 0.01024 0.00492 -0.0678 0.5525 0.9593
1.750 0.6428 0.01032 0.00497 -0.0701 0.5435 0.9621
2.000 0.6775 0.01051 0.00508 -0.0715 0.5356 0.9679
2.250 0.7141 0.01056 0.00512 -0.0734 0.5263 0.9716
2.500 0.7539 0.01058 0.00507 -0.0761 0.5150 0.9742
2.750 0.7917 0.01067 0.00509 -0.0783 0.5030 0.9788
3.000 0.8185 0.01080 0.00520 -0.0781 0.4927 0.9828
3.250 0.8520 0.01077 0.00511 -0.0795 0.4829 0.9842
3.500 0.8848 0.01077 0.00507 -0.0808 0.4730 0.9860
3.750 0.9160 0.01081 0.00508 -0.0817 0.4634 0.9882
4.000 0.9452 0.01090 0.00511 -0.0823 0.4546 0.9908
4.250 0.9731 0.01101 0.00522 -0.0825 0.4456 0.9933
4.500 1.0088 0.01099 0.00515 -0.0844 0.4353 0.9956
4.750 1.0417 0.01101 0.00514 -0.0858 0.4245 0.9979
5.000 1.0740 0.01104 0.00516 -0.0871 0.4155 0.9999
5.250 1.0943 0.01120 0.00529 -0.0858 0.4078 1.0000
5.500 1.1140 0.01134 0.00543 -0.0843 0.4006 1.0000
5.750 1.1332 0.01150 0.00559 -0.0828 0.3932 1.0000
6.000 1.1519 0.01166 0.00576 -0.0812 0.3852 1.0000
6.250 1.1699 0.01185 0.00593 -0.0794 0.3761 1.0000
6.500 1.1880 0.01202 0.00610 -0.0777 0.3670 1.0000
6.750 1.2042 0.01226 0.00631 -0.0756 0.3577 1.0000
7.000 1.2216 0.01244 0.00651 -0.0737 0.3473 1.0000
7.250 1.2372 0.01267 0.00673 -0.0715 0.3372 1.0000
7.500 1.2513 0.01294 0.00697 -0.0691 0.3261 1.0000
7.750 1.2645 0.01322 0.00723 -0.0665 0.3119 1.0000
8.000 1.2739 0.01359 0.00753 -0.0631 0.2923 1.0000
8.250 1.2801 0.01404 0.00789 -0.0593 0.2677 1.0000
8.500 1.2760 0.01474 0.00838 -0.0535 0.2302 1.0000
8.750 1.2598 0.01544 0.00890 -0.0454 0.1991 1.0000
9.000 1.2493 0.01608 0.00945 -0.0385 0.1816 1.0000
9.250 1.2433 0.01676 0.01007 -0.0327 0.1687 1.0000
9.500 1.2407 0.01745 0.01074 -0.0278 0.1588 1.0000
9.750 1.2413 0.01814 0.01142 -0.0235 0.1500 1.0000
10.000 1.2434 0.01886 0.01214 -0.0197 0.1414 1.0000
10.250 1.2446 0.01972 0.01297 -0.0160 0.1327 1.0000
10.500 1.2496 0.02050 0.01376 -0.0130 0.1244 1.0000
10.750 1.2521 0.02149 0.01472 -0.0099 0.1167 1.0000
11.000 1.2580 0.02239 0.01564 -0.0074 0.1120 1.0000
11.250 1.2619 0.02348 0.01673 -0.0049 0.1077 1.0000
11.500 1.2670 0.02458 0.01786 -0.0027 0.1040 1.0000
11.750 1.2725 0.02572 0.01902 -0.0006 0.1008 1.0000
12.000 1.2777 0.02694 0.02028 0.0013 0.0987 1.0000
12.250 1.2808 0.02838 0.02174 0.0032 0.0960 1.0000
12.500 1.2828 0.02997 0.02336 0.0051 0.0934 1.0000
12.750 1.2896 0.03127 0.02473 0.0065 0.0921 1.0000
13.000 1.2959 0.03265 0.02619 0.0078 0.0904 1.0000
13.250 1.3000 0.03425 0.02784 0.0090 0.0885 1.0000
13.500 1.3027 0.03604 0.02967 0.0103 0.0865 1.0000
13.750 1.3029 0.03810 0.03177 0.0115 0.0841 1.0000
14.000 1.3038 0.04017 0.03388 0.0125 0.0817 1.0000
14.250 1.3124 0.04158 0.03538 0.0132 0.0800 1.0000
14.500 1.3192 0.04319 0.03707 0.0139 0.0777 1.0000
14.750 1.3204 0.04539 0.03928 0.0146 0.0739 1.0000
15.000 1.3239 0.04740 0.04136 0.0152 0.0702 1.0000
15.250 1.3334 0.04885 0.04286 0.0156 0.0650 1.0000
15.500 1.3360 0.05103 0.04499 0.0160 0.0532 1.0000
15.750 1.3176 0.05545 0.04919 0.0166 0.0317 1.0000
16.000 1.3100 0.05884 0.05260 0.0169 0.0278 1.0000
16.250 1.2993 0.06271 0.05651 0.0171 0.0243 1.0000
16.500 1.2952 0.06593 0.05980 0.0171 0.0230 1.0000
16.750 1.2897 0.06937 0.06332 0.0170 0.0220 1.0000
17.000 1.2821 0.07316 0.06718 0.0167 0.0210 1.0000
17.250 1.2784 0.07655 0.07067 0.0164 0.0204 1.0000
17.500 1.2744 0.08003 0.07424 0.0160 0.0199 1.0000
17.750 1.2691 0.08373 0.07803 0.0154 0.0194 1.0000
18.000 1.2624 0.08767 0.08206 0.0147 0.0190 1.0000
18.250 1.2540 0.09192 0.08639 0.0138 0.0185 1.0000
18.500 1.2459 0.09623 0.09079 0.0128 0.0183 1.0000
18.750 1.2352 0.10093 0.09557 0.0116 0.0180 1.0000
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