GOE 389 AIRFOIL (goe389-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 389 AIRFOIL (goe389-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.71 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe389-il-1000000.txt Download as CSV file: xf-goe389-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 389 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2741 0.11135 0.10978 -0.0325 1.0000 0.0160
-11.000 -0.2723 0.10796 0.10640 -0.0333 1.0000 0.0170
-10.500 -0.7415 0.02617 0.02344 -0.0776 0.9972 0.0146
-10.250 -0.7095 0.02557 0.02282 -0.0793 0.9958 0.0151
-10.000 -0.6740 0.02632 0.02367 -0.0805 0.9948 0.0153
-9.750 -0.6393 0.02693 0.02435 -0.0816 0.9937 0.0156
-9.500 -0.6070 0.02714 0.02457 -0.0826 0.9915 0.0159
-9.250 -0.5756 0.02647 0.02383 -0.0842 0.9888 0.0165
-9.000 -0.5458 0.02433 0.02142 -0.0866 0.9861 0.0174
-8.750 -0.5124 0.02309 0.01996 -0.0888 0.9840 0.0181
-8.500 -0.4896 0.01987 0.01634 -0.0902 0.9772 0.0190
-8.250 -0.4571 0.01961 0.01608 -0.0915 0.9726 0.0194
-8.000 -0.4269 0.01939 0.01583 -0.0922 0.9651 0.0199
-7.750 -0.3950 0.01912 0.01553 -0.0933 0.9579 0.0205
-7.500 -0.3660 0.01862 0.01494 -0.0938 0.9470 0.0213
-7.250 -0.3382 0.01788 0.01403 -0.0941 0.9350 0.0222
-7.000 -0.3115 0.01729 0.01325 -0.0940 0.9228 0.0228
-6.750 -0.2841 0.01733 0.01315 -0.0937 0.9109 0.0231
-6.500 -0.2635 0.01450 0.00995 -0.0934 0.8992 0.0244
-6.250 -0.2372 0.01422 0.00961 -0.0932 0.8877 0.0252
-6.000 -0.2107 0.01383 0.00914 -0.0930 0.8766 0.0259
-5.750 -0.1844 0.01330 0.00848 -0.0927 0.8643 0.0265
-5.500 -0.1581 0.01275 0.00780 -0.0924 0.8503 0.0271
-5.250 -0.1314 0.01235 0.00728 -0.0921 0.8347 0.0279
-5.000 -0.1046 0.01191 0.00671 -0.0918 0.8188 0.0285
-4.750 -0.0778 0.01149 0.00616 -0.0915 0.8024 0.0289
-4.500 -0.0508 0.01121 0.00576 -0.0912 0.7867 0.0292
-4.250 -0.0236 0.01096 0.00538 -0.0910 0.7728 0.0295
-4.000 0.0018 0.00978 0.00405 -0.0907 0.7616 0.0308
-3.750 0.0288 0.00939 0.00359 -0.0905 0.7518 0.0315
-3.500 0.0564 0.00910 0.00324 -0.0904 0.7433 0.0321
-3.250 0.0838 0.00887 0.00294 -0.0902 0.7349 0.0326
-3.000 0.1117 0.00864 0.00267 -0.0902 0.7269 0.0333
-2.750 0.1395 0.00847 0.00243 -0.0901 0.7196 0.0339
-2.500 0.1677 0.00829 0.00221 -0.0900 0.7123 0.0348
-2.250 0.1955 0.00817 0.00203 -0.0899 0.7046 0.0359
-2.000 0.2238 0.00805 0.00188 -0.0899 0.6964 0.0369
-1.750 0.2519 0.00796 0.00174 -0.0899 0.6885 0.0375
-1.500 0.2799 0.00781 0.00153 -0.0898 0.6776 0.0398
-1.250 0.3079 0.00771 0.00141 -0.0897 0.6647 0.0432
-1.000 0.3358 0.00763 0.00132 -0.0897 0.6487 0.0514
-0.750 0.3633 0.00751 0.00124 -0.0895 0.6293 0.0833
-0.500 0.3900 0.00734 0.00119 -0.0894 0.5987 0.1574
-0.250 0.4156 0.00729 0.00120 -0.0891 0.5560 0.2408
0.000 0.4417 0.00732 0.00125 -0.0889 0.5226 0.3047
0.250 0.4682 0.00728 0.00131 -0.0887 0.4988 0.3764
0.500 0.4941 0.00701 0.00140 -0.0886 0.4816 0.5415
0.750 0.5204 0.00686 0.00147 -0.0884 0.4667 0.6468
1.000 0.5382 0.00620 0.00160 -0.0859 0.4549 0.9425
1.250 0.5793 0.00628 0.00162 -0.0888 0.4437 1.0000
1.500 0.6063 0.00641 0.00168 -0.0886 0.4351 1.0000
1.750 0.6337 0.00651 0.00173 -0.0884 0.4272 1.0000
2.000 0.6608 0.00663 0.00179 -0.0883 0.4199 1.0000
2.250 0.6884 0.00673 0.00185 -0.0882 0.4135 1.0000
2.500 0.7155 0.00686 0.00193 -0.0881 0.4069 1.0000
2.750 0.7432 0.00695 0.00200 -0.0880 0.4013 1.0000
3.000 0.7703 0.00708 0.00209 -0.0879 0.3935 1.0000
3.250 0.7978 0.00719 0.00217 -0.0878 0.3858 1.0000
3.500 0.8248 0.00733 0.00226 -0.0876 0.3777 1.0000
3.750 0.8523 0.00744 0.00235 -0.0876 0.3694 1.0000
4.000 0.8792 0.00759 0.00246 -0.0874 0.3602 1.0000
4.250 0.9064 0.00772 0.00256 -0.0873 0.3507 1.0000
4.500 0.9333 0.00787 0.00267 -0.0872 0.3392 1.0000
4.750 0.9599 0.00805 0.00280 -0.0870 0.3262 1.0000
5.000 0.9864 0.00824 0.00294 -0.0868 0.3126 1.0000
5.250 1.0126 0.00846 0.00309 -0.0866 0.2975 1.0000
5.500 1.0377 0.00878 0.00330 -0.0862 0.2746 1.0000
5.750 1.0614 0.00922 0.00357 -0.0857 0.2400 1.0000
6.000 1.0822 0.00998 0.00402 -0.0847 0.1850 1.0000
6.250 1.0998 0.01106 0.00470 -0.0832 0.1176 1.0000
6.500 1.1237 0.01149 0.00506 -0.0827 0.1022 1.0000
6.750 1.1433 0.01234 0.00561 -0.0815 0.0563 1.0000
7.000 1.1617 0.01330 0.00635 -0.0801 0.0188 1.0000
7.250 1.1851 0.01373 0.00679 -0.0795 0.0152 1.0000
7.500 1.2088 0.01411 0.00722 -0.0788 0.0142 1.0000
7.750 1.2316 0.01456 0.00772 -0.0781 0.0133 1.0000
8.000 1.2532 0.01511 0.00832 -0.0772 0.0123 1.0000
8.250 1.2731 0.01579 0.00907 -0.0759 0.0115 1.0000
8.500 1.2951 0.01624 0.00956 -0.0751 0.0111 1.0000
8.750 1.3158 0.01677 0.01013 -0.0741 0.0106 1.0000
9.000 1.3354 0.01736 0.01078 -0.0729 0.0102 1.0000
9.250 1.3538 0.01801 0.01148 -0.0716 0.0097 1.0000
9.500 1.3705 0.01875 0.01227 -0.0700 0.0094 1.0000
9.750 1.3834 0.01968 0.01327 -0.0679 0.0090 1.0000
10.000 1.3864 0.02097 0.01466 -0.0641 0.0087 1.0000
10.250 1.3891 0.02230 0.01608 -0.0606 0.0085 1.0000
10.500 1.4018 0.02308 0.01692 -0.0587 0.0084 1.0000
10.750 1.4123 0.02403 0.01794 -0.0567 0.0082 1.0000
11.000 1.4209 0.02516 0.01914 -0.0546 0.0081 1.0000
11.250 1.4290 0.02640 0.02045 -0.0527 0.0078 1.0000
11.500 1.4367 0.02773 0.02186 -0.0510 0.0076 1.0000
11.750 1.4435 0.02922 0.02342 -0.0494 0.0074 1.0000
12.000 1.4489 0.03089 0.02517 -0.0479 0.0072 1.0000
12.250 1.4532 0.03277 0.02712 -0.0466 0.0070 1.0000
12.500 1.4564 0.03485 0.02927 -0.0455 0.0069 1.0000
12.750 1.4583 0.03716 0.03166 -0.0446 0.0068 1.0000
13.000 1.4589 0.03972 0.03430 -0.0438 0.0066 1.0000
13.250 1.4573 0.04256 0.03722 -0.0432 0.0065 1.0000
13.500 1.4540 0.04568 0.04041 -0.0426 0.0064 1.0000
13.750 1.4478 0.04912 0.04395 -0.0420 0.0063 1.0000
14.000 1.4398 0.05275 0.04766 -0.0413 0.0062 1.0000
14.250 1.4310 0.05637 0.05135 -0.0401 0.0062 1.0000
14.500 1.4282 0.05952 0.05459 -0.0395 0.0061 1.0000
14.750 1.4282 0.06272 0.05790 -0.0399 0.0060 1.0000
15.000 1.4277 0.06609 0.06136 -0.0405 0.0060 1.0000
15.250 1.4261 0.06957 0.06495 -0.0410 0.0060 1.0000
15.500 1.4240 0.07318 0.06866 -0.0415 0.0059 1.0000
15.750 1.4215 0.07693 0.07252 -0.0423 0.0059 1.0000
16.000 1.4184 0.08083 0.07652 -0.0431 0.0058 1.0000
16.250 1.4146 0.08486 0.08065 -0.0440 0.0058 1.0000
16.500 1.4102 0.08902 0.08492 -0.0451 0.0057 1.0000
16.750 1.4051 0.09335 0.08936 -0.0462 0.0057 1.0000
17.000 1.3995 0.09786 0.09399 -0.0476 0.0056 1.0000
17.250 1.3931 0.10254 0.09879 -0.0491 0.0056 1.0000
17.500 1.3860 0.10739 0.10375 -0.0508 0.0055 1.0000
17.750 1.3784 0.11242 0.10890 -0.0527 0.0055 1.0000
18.000 1.3704 0.11761 0.11421 -0.0548 0.0054 1.0000
18.250 1.3618 0.12301 0.11974 -0.0571 0.0054 1.0000
18.500 1.3530 0.12860 0.12545 -0.0598 0.0054 1.0000
18.750 1.3429 0.13447 0.13144 -0.0627 0.0053 1.0000
19.000 1.3324 0.14065 0.13776 -0.0659 0.0053 1.0000
19.250 1.3218 0.14705 0.14428 -0.0695 0.0053 1.0000
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