GOE 746 AIRFOIL (goe746-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 746 AIRFOIL (goe746-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.65 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe746-il-1000000.txt Download as CSV file: xf-goe746-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 746 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4038 0.09009 0.08721 0.0156 0.5376 0.0133
-7.500 -0.4032 0.08728 0.08443 0.0144 0.5352 0.0139
-7.000 -0.4039 0.07965 0.07680 0.0078 0.5307 0.0151
-6.750 -0.3957 0.07511 0.07222 0.0044 0.5283 0.0152
-6.500 -0.3845 0.07078 0.06783 0.0018 0.5257 0.0152
-6.250 -0.3713 0.06647 0.06345 -0.0005 0.5230 0.0152
-6.000 -0.3637 0.06162 0.05856 -0.0020 0.5209 0.0156
-5.750 -0.3473 0.05933 0.05623 -0.0026 0.5181 0.0158
-5.500 -0.3293 0.05687 0.05373 -0.0036 0.5152 0.0161
-5.250 -0.3101 0.05413 0.05091 -0.0048 0.5123 0.0167
-5.000 -0.2809 0.04909 0.04566 -0.0074 0.5099 0.0190
-4.750 -0.2588 0.04460 0.04098 -0.0082 0.5072 0.0192
-4.500 -0.2442 0.03717 0.03328 -0.0084 0.5059 0.0195
-4.250 -0.2239 0.03544 0.03148 -0.0084 0.5035 0.0198
-4.000 -0.2015 0.03416 0.03015 -0.0083 0.5007 0.0202
-3.750 -0.1783 0.03262 0.02851 -0.0082 0.4978 0.0210
-3.500 -0.1476 0.03028 0.02586 -0.0072 0.4952 0.0240
-3.250 -0.1245 0.02750 0.02277 -0.0062 0.4924 0.0241
-3.000 -0.1083 0.02191 0.01673 -0.0046 0.4908 0.0249
-2.750 -0.0833 0.02098 0.01578 -0.0044 0.4885 0.0254
-2.500 -0.0578 0.02026 0.01500 -0.0042 0.4859 0.0261
-2.250 -0.0318 0.01933 0.01395 -0.0038 0.4832 0.0274
-2.000 -0.0023 0.01954 0.01397 -0.0033 0.4803 0.0302
-1.750 0.0244 0.01879 0.01300 -0.0027 0.4772 0.0304
-1.500 0.0474 0.01546 0.00928 -0.0015 0.4755 0.0314
-1.250 0.0740 0.01452 0.00832 -0.0014 0.4731 0.0325
-1.000 0.1013 0.01397 0.00774 -0.0012 0.4705 0.0338
-0.750 0.1290 0.01348 0.00716 -0.0010 0.4677 0.0357
-0.500 0.1577 0.01400 0.00762 -0.0008 0.4649 0.0385
-0.250 0.1840 0.01230 0.00573 -0.0005 0.4619 0.0415
0.000 0.2119 0.01184 0.00529 -0.0004 0.4598 0.0432
0.250 0.2408 0.01050 0.00375 0.0004 0.4573 0.0321
0.500 0.2686 0.01015 0.00337 0.0006 0.4546 0.0316
0.750 0.2961 0.00983 0.00303 0.0009 0.4517 0.0314
1.000 0.3229 0.00949 0.00265 0.0012 0.4481 0.0319
1.250 0.3500 0.00921 0.00238 0.0015 0.4448 0.0325
1.500 0.3775 0.00900 0.00218 0.0017 0.4410 0.0330
1.750 0.4049 0.00886 0.00203 0.0019 0.4375 0.0334
2.000 0.4324 0.00878 0.00192 0.0021 0.4341 0.0339
2.250 0.4600 0.00869 0.00184 0.0022 0.4310 0.0347
2.500 0.4879 0.00861 0.00177 0.0023 0.4280 0.0357
2.750 0.5156 0.00854 0.00170 0.0024 0.4245 0.0366
3.000 0.5434 0.00852 0.00166 0.0025 0.4209 0.0381
3.250 0.5711 0.00853 0.00165 0.0025 0.4174 0.0404
3.500 0.5991 0.00849 0.00166 0.0026 0.4144 0.0486
3.750 0.6358 0.00654 0.00198 0.0003 0.4104 0.9771
4.000 0.7358 0.00685 0.00219 -0.0153 0.4035 0.9969
4.250 0.7822 0.00685 0.00221 -0.0194 0.3996 1.0000
4.500 0.8085 0.00690 0.00225 -0.0191 0.3954 1.0000
4.750 0.8347 0.00698 0.00230 -0.0188 0.3909 1.0000
5.000 0.8609 0.00703 0.00237 -0.0185 0.3864 1.0000
5.250 0.8870 0.00711 0.00243 -0.0183 0.3779 1.0000
5.500 0.9131 0.00719 0.00250 -0.0180 0.3683 1.0000
5.750 0.9390 0.00732 0.00259 -0.0178 0.3590 1.0000
6.000 0.9648 0.00747 0.00270 -0.0175 0.3471 1.0000
6.250 0.9905 0.00764 0.00285 -0.0173 0.3339 1.0000
6.500 1.0159 0.00785 0.00301 -0.0171 0.3191 1.0000
6.750 1.0411 0.00812 0.00322 -0.0168 0.3019 1.0000
7.000 1.0657 0.00850 0.00351 -0.0166 0.2778 1.0000
7.250 1.0892 0.00910 0.00393 -0.0164 0.2436 1.0000
7.500 1.1119 0.00983 0.00446 -0.0162 0.2071 1.0000
7.750 1.1317 0.01106 0.00532 -0.0159 0.1468 1.0000
8.000 1.1400 0.01404 0.00761 -0.0154 0.0217 1.0000
8.250 1.1613 0.01458 0.00818 -0.0147 0.0183 1.0000
8.500 1.1812 0.01526 0.00891 -0.0140 0.0158 1.0000
8.750 1.2016 0.01580 0.00950 -0.0134 0.0150 1.0000
9.000 1.2211 0.01639 0.01014 -0.0126 0.0141 1.0000
9.250 1.2392 0.01708 0.01088 -0.0118 0.0133 1.0000
9.500 1.2552 0.01791 0.01176 -0.0109 0.0126 1.0000
9.750 1.2661 0.01915 0.01310 -0.0097 0.0118 1.0000
10.000 1.2732 0.02077 0.01484 -0.0090 0.0113 1.0000
10.250 1.2827 0.02217 0.01629 -0.0088 0.0110 1.0000
10.500 1.2766 0.02413 0.01834 -0.0069 0.0109 1.0000
10.750 1.2793 0.02595 0.02023 -0.0061 0.0105 1.0000
11.000 1.2800 0.02821 0.02255 -0.0056 0.0103 1.0000
11.250 1.2818 0.03045 0.02487 -0.0054 0.0101 1.0000
11.500 1.2836 0.03276 0.02724 -0.0052 0.0097 1.0000
11.750 1.2825 0.03543 0.02998 -0.0052 0.0095 1.0000
12.000 1.2809 0.03819 0.03280 -0.0052 0.0094 1.0000
12.250 1.2806 0.04081 0.03547 -0.0053 0.0090 1.0000
12.500 1.2763 0.04389 0.03862 -0.0054 0.0089 1.0000
12.750 1.2674 0.04752 0.04234 -0.0056 0.0087 1.0000
13.000 1.2627 0.05080 0.04570 -0.0059 0.0087 1.0000
13.250 1.2393 0.05637 0.05137 -0.0067 0.0082 1.0000
13.500 1.2312 0.06023 0.05531 -0.0072 0.0083 1.0000
13.750 1.2317 0.06316 0.05830 -0.0076 0.0082 1.0000
14.000 1.2363 0.06566 0.06086 -0.0080 0.0081 1.0000
14.250 1.2377 0.06859 0.06386 -0.0085 0.0079 1.0000
14.500 1.2397 0.07145 0.06678 -0.0090 0.0077 1.0000
14.750 1.2369 0.07483 0.07022 -0.0095 0.0077 1.0000
15.000 1.2391 0.07774 0.07319 -0.0101 0.0074 1.0000
15.250 1.2415 0.08072 0.07622 -0.0109 0.0072 1.0000
15.500 1.2408 0.08389 0.07945 -0.0114 0.0071 1.0000
15.750 1.2410 0.08717 0.08280 -0.0122 0.0068 1.0000
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Polar data table (+)
Polar graphs
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