GOE 92 AIRFOIL (goe92-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 92 AIRFOIL (goe92-il) Reynolds number: 200,000 Max Cl/Cd: 72.81 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe92-il-200000-n5.txt Download as CSV file: xf-goe92-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 92 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2496 0.10294 0.09980 -0.0259 1.0000 0.0150
-8.250 -0.2447 0.10025 0.09716 -0.0267 1.0000 0.0152
-8.000 -0.2418 0.09780 0.09476 -0.0271 1.0000 0.0155
-7.750 -0.2263 0.09416 0.09113 -0.0310 0.9839 0.0159
-7.500 -0.2100 0.09049 0.08746 -0.0352 0.9662 0.0163
-7.250 -0.1940 0.08689 0.08386 -0.0393 0.9498 0.0168
-7.000 -0.1779 0.08336 0.08030 -0.0436 0.9353 0.0173
-6.750 -0.1603 0.07980 0.07671 -0.0482 0.9226 0.0180
-6.250 -0.1198 0.07316 0.06997 -0.0592 0.8978 0.0194
-6.000 -0.0970 0.06980 0.06652 -0.0650 0.8855 0.0196
-5.750 -0.0736 0.06630 0.06292 -0.0699 0.8738 0.0197
-5.500 -0.0501 0.06272 0.05924 -0.0739 0.8628 0.0198
-5.250 -0.0252 0.05914 0.05554 -0.0776 0.8528 0.0199
-5.000 0.0021 0.05567 0.05192 -0.0812 0.8423 0.0200
-4.750 0.0279 0.05225 0.04835 -0.0837 0.8314 0.0201
-4.500 0.0524 0.04872 0.04468 -0.0857 0.8200 0.0201
-4.250 0.0766 0.04517 0.04097 -0.0872 0.8076 0.0200
-4.000 0.0933 0.04126 0.03701 -0.0881 0.7938 0.0194
-3.750 0.1150 0.03797 0.03357 -0.0892 0.7781 0.0180
-3.500 0.1434 0.03476 0.03011 -0.0906 0.7604 0.0173
-3.250 0.1724 0.03181 0.02684 -0.0915 0.7395 0.0175
-3.000 0.2046 0.02898 0.02355 -0.0917 0.7144 0.0194
-2.750 0.2328 0.02627 0.02036 -0.0916 0.6859 0.0195
-2.250 0.2846 0.02261 0.01588 -0.0912 0.6325 0.0220
-2.000 0.3111 0.02155 0.01446 -0.0909 0.6107 0.0251
-1.750 0.3393 0.01993 0.01235 -0.0904 0.5930 0.0261
-1.500 0.3675 0.01875 0.01066 -0.0899 0.5766 0.0299
-1.250 0.3938 0.01783 0.00953 -0.0897 0.5605 0.0320
-1.000 0.4210 0.01699 0.00839 -0.0894 0.5451 0.0334
-0.750 0.4481 0.01661 0.00774 -0.0890 0.5297 0.0371
-0.500 0.4752 0.01606 0.00694 -0.0886 0.5141 0.0378
-0.250 0.5019 0.01567 0.00632 -0.0882 0.4981 0.0384
0.000 0.5282 0.01505 0.00556 -0.0879 0.4820 0.0400
0.250 0.5543 0.01463 0.00506 -0.0877 0.4658 0.0423
0.500 0.5805 0.01439 0.00470 -0.0873 0.4504 0.0420
0.750 0.6066 0.01421 0.00443 -0.0870 0.4361 0.0418
1.000 0.6328 0.01409 0.00422 -0.0867 0.4230 0.0418
1.250 0.6590 0.01402 0.00406 -0.0865 0.4113 0.0421
1.500 0.6851 0.01402 0.00394 -0.0863 0.4011 0.0428
1.750 0.7116 0.01405 0.00388 -0.0861 0.3919 0.0440
2.000 0.7378 0.01413 0.00385 -0.0859 0.3835 0.0459
2.250 0.7641 0.01425 0.00387 -0.0856 0.3752 0.0484
2.500 0.7903 0.01439 0.00393 -0.0854 0.3677 0.0519
2.750 0.8164 0.01449 0.00404 -0.0852 0.3607 0.0720
3.250 0.8685 0.01319 0.00441 -0.0849 0.3504 1.0000
3.500 0.8945 0.01344 0.00459 -0.0847 0.3462 1.0000
3.750 0.9201 0.01373 0.00478 -0.0844 0.3424 1.0000
4.000 0.9464 0.01394 0.00498 -0.0842 0.3380 1.0000
4.250 0.9723 0.01419 0.00522 -0.0840 0.3338 1.0000
4.500 0.9979 0.01447 0.00546 -0.0838 0.3302 1.0000
4.750 1.0235 0.01476 0.00572 -0.0835 0.3270 1.0000
5.000 1.0495 0.01499 0.00600 -0.0834 0.3233 1.0000
5.250 1.0751 0.01525 0.00631 -0.0832 0.3192 1.0000
5.500 1.1003 0.01554 0.00660 -0.0829 0.3153 1.0000
5.750 1.1255 0.01585 0.00693 -0.0826 0.3119 1.0000
6.000 1.1509 0.01607 0.00726 -0.0824 0.3059 1.0000
6.250 1.1746 0.01629 0.00749 -0.0819 0.2927 1.0000
6.500 1.1983 0.01651 0.00772 -0.0815 0.2768 1.0000
6.750 1.2217 0.01678 0.00797 -0.0810 0.2571 1.0000
7.000 1.2438 0.01719 0.00830 -0.0804 0.2224 1.0000
7.250 1.2516 0.01916 0.00952 -0.0783 0.1263 1.0000
7.500 1.2676 0.02032 0.01053 -0.0769 0.0967 1.0000
7.750 1.2724 0.02245 0.01231 -0.0742 0.0196 1.0000
8.000 1.2893 0.02332 0.01332 -0.0728 0.0158 1.0000
8.250 1.3052 0.02423 0.01445 -0.0713 0.0140 1.0000
8.500 1.3199 0.02516 0.01559 -0.0696 0.0128 1.0000
8.750 1.3324 0.02615 0.01676 -0.0677 0.0115 1.0000
9.000 1.3412 0.02730 0.01810 -0.0653 0.0109 1.0000
9.250 1.3478 0.02864 0.01964 -0.0629 0.0104 1.0000
9.500 1.3517 0.03024 0.02143 -0.0606 0.0100 1.0000
9.750 1.3526 0.03217 0.02355 -0.0584 0.0096 1.0000
10.000 1.3495 0.03456 0.02613 -0.0564 0.0093 1.0000
10.250 1.3408 0.03766 0.02941 -0.0547 0.0089 1.0000
10.500 1.3273 0.04157 0.03349 -0.0536 0.0087 1.0000
10.750 1.3194 0.04525 0.03732 -0.0533 0.0084 1.0000
11.000 1.3195 0.04829 0.04050 -0.0533 0.0081 1.0000
11.250 1.3139 0.05223 0.04459 -0.0537 0.0078 1.0000
11.500 1.3063 0.05656 0.04909 -0.0544 0.0077 1.0000
11.750 1.2986 0.06096 0.05361 -0.0551 0.0076 1.0000
12.000 1.2914 0.06523 0.05799 -0.0557 0.0075 1.0000
12.250 1.2852 0.06934 0.06220 -0.0561 0.0074 1.0000
12.500 1.2803 0.07324 0.06618 -0.0564 0.0073 1.0000
12.750 1.2771 0.07684 0.06986 -0.0565 0.0072 1.0000
13.000 1.2761 0.08006 0.07315 -0.0563 0.0071 1.0000
13.250 1.2774 0.08287 0.07602 -0.0558 0.0069 1.0000
13.500 1.2810 0.08523 0.07843 -0.0550 0.0068 1.0000
13.750 1.2864 0.08733 0.08059 -0.0539 0.0067 1.0000
14.000 1.2918 0.08952 0.08285 -0.0530 0.0066 1.0000
14.250 1.2963 0.09197 0.08537 -0.0524 0.0064 1.0000
14.500 1.3016 0.09420 0.08762 -0.0518 0.0061 1.0000
14.750 1.3111 0.09547 0.08887 -0.0493 0.0057 1.0000
15.000 1.3065 0.10000 0.09364 -0.0511 0.0055 1.0000
15.250 1.3048 0.10401 0.09789 -0.0521 0.0054 1.0000
15.500 1.3045 0.10775 0.10180 -0.0528 0.0053 1.0000
15.750 1.3030 0.11171 0.10594 -0.0536 0.0053 1.0000
16.000 1.3000 0.11605 0.11046 -0.0549 0.0052 1.0000
16.250 1.2959 0.12065 0.11524 -0.0565 0.0052 1.0000
16.500 1.2908 0.12559 0.12035 -0.0586 0.0052 1.0000
16.750 1.2849 0.13076 0.12570 -0.0610 0.0052 1.0000
17.000 1.2783 0.13626 0.13137 -0.0638 0.0052 1.0000
17.250 1.2710 0.14197 0.13725 -0.0669 0.0052 1.0000
17.500 1.2635 0.14789 0.14334 -0.0703 0.0053 1.0000
17.750 1.2556 0.15409 0.14971 -0.0741 0.0053 1.0000
18.000 1.2480 0.16041 0.15617 -0.0780 0.0053 1.0000
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