GOE 746 AIRFOIL (goe746-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 746 AIRFOIL (goe746-il) Reynolds number: 500,000 Max Cl/Cd: 102.39 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe746-il-500000-n5.txt Download as CSV file: xf-goe746-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4207 0.09942 0.09594 0.0186 0.5456 0.0087
-8.500 -0.4186 0.09571 0.09223 0.0168 0.5428 0.0087
-8.250 -0.4193 0.09163 0.08817 0.0149 0.5401 0.0089
-8.000 -0.4152 0.08900 0.08555 0.0136 0.5367 0.0090
-7.750 -0.4053 0.08768 0.08421 0.0128 0.5329 0.0095
-7.500 -0.4092 0.08434 0.08088 0.0113 0.5304 0.0094
-7.250 -0.4039 0.08132 0.07784 0.0092 0.5279 0.0097
-7.000 -0.3966 0.07793 0.07444 0.0068 0.5255 0.0101
-6.750 -0.3885 0.07394 0.07043 0.0040 0.5231 0.0106
-6.500 -0.3791 0.06934 0.06578 0.0009 0.5207 0.0109
-6.250 -0.3705 0.06220 0.05854 -0.0036 0.5189 0.0115
-6.000 -0.3541 0.05847 0.05472 -0.0057 0.5160 0.0119
-5.750 -0.3347 0.05636 0.05253 -0.0069 0.5129 0.0122
-5.500 -0.3144 0.05403 0.05012 -0.0080 0.5103 0.0129
-5.250 -0.2943 0.05004 0.04600 -0.0097 0.5081 0.0137
-5.000 -0.2754 0.04077 0.03636 -0.0120 0.5067 0.0152
-4.750 -0.2524 0.03936 0.03487 -0.0122 0.5038 0.0155
-4.500 -0.2288 0.03814 0.03354 -0.0124 0.5008 0.0161
-4.000 -0.1854 0.02677 0.02125 -0.0110 0.4966 0.0196
-3.750 -0.1605 0.02625 0.02067 -0.0109 0.4940 0.0200
-3.500 -0.1353 0.02554 0.01988 -0.0108 0.4913 0.0206
-3.250 -0.1106 0.02384 0.01796 -0.0102 0.4887 0.0214
-3.000 -0.0858 0.02164 0.01542 -0.0094 0.4862 0.0223
-2.750 -0.0600 0.01975 0.01316 -0.0085 0.4837 0.0237
-2.500 -0.0334 0.01863 0.01173 -0.0079 0.4812 0.0243
-2.250 -0.0065 0.01786 0.01074 -0.0074 0.4787 0.0247
-2.000 0.0193 0.01614 0.00878 -0.0069 0.4762 0.0251
-1.750 0.0462 0.01529 0.00783 -0.0067 0.4736 0.0257
-1.500 0.0735 0.01476 0.00721 -0.0066 0.4709 0.0264
-1.250 0.1010 0.01416 0.00649 -0.0063 0.4683 0.0267
-1.000 0.1287 0.01363 0.00585 -0.0061 0.4657 0.0270
-0.750 0.1565 0.01314 0.00531 -0.0060 0.4633 0.0275
-0.500 0.1843 0.01272 0.00484 -0.0058 0.4607 0.0279
-0.250 0.2120 0.01235 0.00442 -0.0056 0.4579 0.0283
0.000 0.2395 0.01202 0.00405 -0.0054 0.4551 0.0287
0.250 0.2670 0.01174 0.00373 -0.0052 0.4525 0.0290
0.500 0.2944 0.01152 0.00348 -0.0051 0.4501 0.0296
0.750 0.3219 0.01131 0.00327 -0.0049 0.4473 0.0303
1.000 0.3492 0.01109 0.00306 -0.0047 0.4443 0.0305
1.250 0.3764 0.01090 0.00286 -0.0045 0.4413 0.0307
1.500 0.4037 0.01076 0.00269 -0.0043 0.4384 0.0310
1.750 0.4309 0.01065 0.00256 -0.0041 0.4354 0.0313
2.000 0.4585 0.01054 0.00247 -0.0040 0.4313 0.0317
2.250 0.4858 0.01043 0.00237 -0.0038 0.4265 0.0323
2.500 0.5131 0.01036 0.00225 -0.0037 0.4222 0.0336
2.750 0.5407 0.01033 0.00222 -0.0036 0.4187 0.0349
3.000 0.5684 0.01031 0.00222 -0.0035 0.4148 0.0362
3.250 0.5959 0.01030 0.00223 -0.0035 0.4108 0.0389
3.750 0.6505 0.01026 0.00232 -0.0033 0.4035 0.1012
4.250 0.7589 0.00869 0.00279 -0.0150 0.3926 0.9916
4.500 0.8160 0.00875 0.00286 -0.0215 0.3871 0.9996
4.750 0.8445 0.00884 0.00294 -0.0217 0.3818 1.0000
5.000 0.8703 0.00896 0.00304 -0.0215 0.3767 1.0000
5.250 0.8963 0.00906 0.00317 -0.0212 0.3697 1.0000
5.500 0.9219 0.00921 0.00329 -0.0209 0.3624 1.0000
5.750 0.9477 0.00934 0.00344 -0.0206 0.3557 1.0000
6.000 0.9731 0.00952 0.00361 -0.0204 0.3457 1.0000
6.250 0.9983 0.00975 0.00380 -0.0201 0.3307 1.0000
6.500 1.0232 0.01001 0.00402 -0.0198 0.3157 1.0000
6.750 1.0477 0.01036 0.00431 -0.0196 0.2955 1.0000
7.000 1.0714 0.01082 0.00468 -0.0193 0.2726 1.0000
7.250 1.0938 0.01152 0.00521 -0.0191 0.2401 1.0000
7.500 1.1160 0.01216 0.00574 -0.0188 0.2161 1.0000
7.750 1.1370 0.01296 0.00640 -0.0184 0.1864 1.0000
8.000 1.1542 0.01425 0.00740 -0.0179 0.1361 1.0000
8.250 1.1557 0.01733 0.00988 -0.0168 0.0270 1.0000
8.500 1.1726 0.01822 0.01078 -0.0160 0.0181 1.0000
8.750 1.1902 0.01894 0.01157 -0.0153 0.0158 1.0000
9.000 1.2056 0.01983 0.01251 -0.0145 0.0139 1.0000
9.250 1.2180 0.02093 0.01373 -0.0135 0.0125 1.0000
9.500 1.2302 0.02211 0.01500 -0.0131 0.0120 1.0000
9.750 1.2348 0.02372 0.01670 -0.0124 0.0114 1.0000
10.000 1.2345 0.02547 0.01852 -0.0109 0.0110 1.0000
10.250 1.2367 0.02734 0.02046 -0.0101 0.0105 1.0000
10.500 1.2392 0.02937 0.02256 -0.0096 0.0100 1.0000
10.750 1.2406 0.03160 0.02485 -0.0092 0.0094 1.0000
11.000 1.2393 0.03419 0.02752 -0.0089 0.0092 1.0000
11.250 1.2338 0.03727 0.03071 -0.0088 0.0087 1.0000
11.500 1.2342 0.03977 0.03329 -0.0087 0.0085 1.0000
11.750 1.2333 0.04245 0.03606 -0.0086 0.0084 1.0000
12.000 1.2332 0.04508 0.03876 -0.0086 0.0081 1.0000
12.250 1.2311 0.04794 0.04171 -0.0087 0.0079 1.0000
12.500 1.2273 0.05109 0.04494 -0.0089 0.0076 1.0000
12.750 1.2238 0.05430 0.04824 -0.0092 0.0076 1.0000
13.000 1.2228 0.05734 0.05135 -0.0095 0.0072 1.0000
13.250 1.2222 0.06034 0.05442 -0.0099 0.0071 1.0000
13.500 1.2196 0.06369 0.05784 -0.0105 0.0069 1.0000
13.750 1.2185 0.06692 0.06115 -0.0110 0.0066 1.0000
14.000 1.2154 0.07042 0.06471 -0.0117 0.0064 1.0000
14.250 1.2108 0.07424 0.06861 -0.0125 0.0064 1.0000
14.500 1.2070 0.07796 0.07239 -0.0133 0.0062 1.0000
14.750 1.1979 0.08245 0.07696 -0.0142 0.0060 1.0000
15.000 1.1962 0.08597 0.08055 -0.0150 0.0060 1.0000
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Polar data table (+)
Polar graphs
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