GOE 746 AIRFOIL (goe746-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 746 AIRFOIL (goe746-il) Reynolds number: 500,000 Max Cl/Cd: 106.31 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe746-il-500000.txt Download as CSV file: xf-goe746-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3672 0.11583 0.11279 0.0298 0.5978 0.0169
-9.500 -0.3622 0.11210 0.10905 0.0282 0.5935 0.0174
-9.250 -0.4231 0.11184 0.10862 0.0255 0.6076 0.0170
-9.000 -0.4173 0.10858 0.10533 0.0239 0.6021 0.0174
-8.750 -0.4122 0.10533 0.10205 0.0221 0.5977 0.0185
-8.500 -0.4106 0.10220 0.09894 0.0193 0.5933 0.0189
-8.250 -0.4120 0.09908 0.09584 0.0164 0.5894 0.0191
-8.000 -0.4136 0.09584 0.09259 0.0139 0.5856 0.0191
-7.750 -0.4157 0.09273 0.08948 0.0119 0.5821 0.0191
-7.500 -0.4135 0.08919 0.08594 0.0093 0.5787 0.0192
-7.250 -0.4070 0.08520 0.08192 0.0063 0.5751 0.0192
-7.000 -0.4027 0.08041 0.07711 0.0055 0.5717 0.0194
-6.750 -0.3928 0.07747 0.07411 0.0058 0.5678 0.0197
-6.500 -0.3817 0.07452 0.07116 0.0049 0.5640 0.0200
-6.250 -0.3696 0.07145 0.06805 0.0034 0.5603 0.0203
-6.000 -0.3561 0.06826 0.06480 0.0016 0.5568 0.0209
-5.750 -0.3408 0.06492 0.06137 -0.0004 0.5538 0.0217
-5.500 -0.3126 0.06037 0.05662 -0.0054 0.5513 0.0239
-5.250 -0.2902 0.05597 0.05206 -0.0076 0.5485 0.0241
-5.000 -0.2764 0.04988 0.04582 -0.0087 0.5458 0.0244
-4.750 -0.2610 0.04728 0.04317 -0.0087 0.5425 0.0248
-4.500 -0.2422 0.04512 0.04092 -0.0088 0.5391 0.0253
-4.250 -0.2212 0.04281 0.03850 -0.0090 0.5361 0.0260
-4.000 -0.1983 0.04029 0.03586 -0.0093 0.5330 0.0275
-3.750 -0.1642 0.03735 0.03243 -0.0088 0.5303 0.0304
-3.500 -0.1485 0.03181 0.02663 -0.0083 0.5279 0.0313
-3.250 -0.1266 0.03010 0.02483 -0.0081 0.5249 0.0320
-3.000 -0.1034 0.02869 0.02330 -0.0079 0.5218 0.0329
-2.750 -0.0787 0.02714 0.02162 -0.0075 0.5189 0.0348
-2.500 -0.0473 0.02727 0.02135 -0.0063 0.5157 0.0387
-2.250 -0.0280 0.02289 0.01672 -0.0056 0.5133 0.0406
-2.000 -0.0029 0.02179 0.01553 -0.0054 0.5105 0.0421
-1.750 0.0230 0.02089 0.01447 -0.0050 0.5075 0.0445
-1.500 0.0505 0.02004 0.01323 -0.0041 0.5048 0.0506
-1.250 0.0760 0.01867 0.01190 -0.0040 0.5017 0.0530
-1.000 0.1030 0.01803 0.01118 -0.0038 0.4988 0.0572
-0.750 0.1299 0.01715 0.01008 -0.0034 0.4961 0.0649
-0.500 0.1567 0.01650 0.00938 -0.0032 0.4932 0.0694
-0.250 0.1838 0.01583 0.00858 -0.0029 0.4904 0.0796
0.000 0.2156 0.01412 0.00649 -0.0019 0.4877 0.0522
0.250 0.2445 0.01340 0.00573 -0.0015 0.4847 0.0462
0.500 0.2725 0.01257 0.00480 -0.0011 0.4818 0.0429
0.750 0.2998 0.01211 0.00428 -0.0008 0.4790 0.0421
1.000 0.3268 0.01182 0.00396 -0.0004 0.4762 0.0422
1.250 0.3540 0.01152 0.00369 -0.0001 0.4732 0.0427
1.500 0.3811 0.01129 0.00346 0.0002 0.4698 0.0431
1.750 0.4082 0.01111 0.00328 0.0004 0.4665 0.0445
2.000 0.4352 0.01102 0.00313 0.0007 0.4628 0.0459
2.250 0.4626 0.01087 0.00302 0.0009 0.4589 0.0468
2.500 0.4902 0.01077 0.00292 0.0011 0.4551 0.0482
2.750 0.5177 0.01069 0.00282 0.0013 0.4516 0.0515
3.000 0.5449 0.01066 0.00279 0.0015 0.4484 0.0679
3.250 0.6714 0.00876 0.00313 -0.0198 0.4418 1.0000
3.500 0.6975 0.00880 0.00315 -0.0195 0.4381 1.0000
3.750 0.7235 0.00886 0.00316 -0.0191 0.4346 1.0000
4.000 0.7495 0.00896 0.00323 -0.0188 0.4312 1.0000
4.250 0.7757 0.00899 0.00330 -0.0185 0.4271 1.0000
4.500 0.8017 0.00904 0.00335 -0.0181 0.4229 1.0000
4.750 0.8275 0.00914 0.00340 -0.0178 0.4190 1.0000
5.000 0.8536 0.00921 0.00352 -0.0175 0.4149 1.0000
5.250 0.8795 0.00927 0.00363 -0.0172 0.4104 1.0000
5.500 0.9053 0.00936 0.00370 -0.0168 0.4061 1.0000
5.750 0.9311 0.00945 0.00382 -0.0165 0.4008 1.0000
6.000 0.9569 0.00949 0.00388 -0.0162 0.3927 1.0000
6.250 0.9826 0.00956 0.00398 -0.0159 0.3834 1.0000
6.500 1.0081 0.00966 0.00406 -0.0156 0.3719 1.0000
6.750 1.0335 0.00980 0.00421 -0.0153 0.3617 1.0000
7.000 1.0588 0.00996 0.00439 -0.0151 0.3491 1.0000
7.250 1.0836 0.01021 0.00460 -0.0148 0.3326 1.0000
7.500 1.1080 0.01052 0.00487 -0.0145 0.3116 1.0000
7.750 1.1314 0.01101 0.00526 -0.0143 0.2846 1.0000
8.000 1.1527 0.01185 0.00590 -0.0140 0.2443 1.0000
8.250 1.1697 0.01333 0.00699 -0.0137 0.1807 1.0000
8.500 1.1676 0.01714 0.00991 -0.0128 0.0370 1.0000
8.750 1.1823 0.01832 0.01109 -0.0119 0.0251 1.0000
9.000 1.1968 0.01939 0.01223 -0.0109 0.0219 1.0000
9.250 1.2100 0.02048 0.01343 -0.0100 0.0203 1.0000
9.500 1.2216 0.02169 0.01476 -0.0093 0.0194 1.0000
9.750 1.2270 0.02355 0.01673 -0.0091 0.0186 1.0000
10.000 1.2214 0.02558 0.01884 -0.0073 0.0182 1.0000
10.250 1.2187 0.02784 0.02119 -0.0063 0.0176 1.0000
10.500 1.2165 0.03034 0.02377 -0.0058 0.0172 1.0000
10.750 1.2118 0.03321 0.02673 -0.0054 0.0167 1.0000
11.000 1.2055 0.03636 0.02996 -0.0053 0.0163 1.0000
11.250 1.1989 0.03958 0.03328 -0.0052 0.0161 1.0000
11.500 1.1866 0.04346 0.03725 -0.0053 0.0157 1.0000
11.750 1.1741 0.04739 0.04128 -0.0053 0.0155 1.0000
12.000 1.1721 0.05022 0.04417 -0.0054 0.0154 1.0000
12.250 1.1785 0.05228 0.04631 -0.0054 0.0148 1.0000
12.500 1.1774 0.05520 0.04931 -0.0056 0.0146 1.0000
12.750 1.1755 0.05828 0.05246 -0.0059 0.0143 1.0000
13.000 1.1744 0.06127 0.05551 -0.0061 0.0142 1.0000
13.250 1.1745 0.06420 0.05849 -0.0064 0.0135 1.0000
13.500 1.1744 0.06707 0.06142 -0.0065 0.0134 1.0000
13.750 1.1754 0.06982 0.06422 -0.0066 0.0132 1.0000
14.000 1.1775 0.07246 0.06690 -0.0068 0.0129 1.0000
14.250 1.1802 0.07498 0.06946 -0.0069 0.0126 1.0000
14.500 1.1835 0.07728 0.07178 -0.0067 0.0122 1.0000
14.750 1.1901 0.07906 0.07360 -0.0061 0.0122 1.0000
15.000 1.2040 0.07880 0.07326 -0.0034 0.0117 1.0000
15.250 1.2199 0.07865 0.07314 -0.0006 0.0113 1.0000
15.500 1.2213 0.08174 0.07634 -0.0014 0.0112 1.0000
15.750 1.2233 0.08470 0.07943 -0.0019 0.0110 1.0000
16.000 1.2251 0.08772 0.08256 -0.0027 0.0108 1.0000
16.250 1.2313 0.08978 0.08472 -0.0021 0.0107 1.0000
16.500 1.2351 0.09234 0.08739 -0.0020 0.0106 1.0000
16.750 1.2357 0.09552 0.09070 -0.0026 0.0105 1.0000
17.000 1.2360 0.09877 0.09408 -0.0029 0.0104 1.0000
17.250 1.2348 0.10233 0.09778 -0.0036 0.0104 1.0000
17.500 1.2313 0.10640 0.10199 -0.0048 0.0103 1.0000
17.750 1.2267 0.11065 0.10639 -0.0058 0.0104 1.0000
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