FX74_CL5_140 (fx74cl5140-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: FX74_CL5_140 (fx74cl5140-il) Reynolds number: 500,000 Max Cl/Cd: 118.76 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx74cl5140-il-500000.txt Download as CSV file: xf-fx74cl5140-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX74_CL5_140
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
------ -------- --------- --------- -------- -------- --------
-11.500 0.1865 0.09706 0.09273 -0.1149 0.5619 0.0065
-11.250 0.1937 0.09461 0.09024 -0.1156 0.5581 0.0066
-11.000 0.2009 0.09217 0.08776 -0.1163 0.5546 0.0068
-10.750 0.2082 0.08958 0.08518 -0.1170 0.5516 0.0070
-10.500 0.2156 0.08710 0.08269 -0.1177 0.5480 0.0072
-10.250 0.2228 0.08461 0.08018 -0.1184 0.5451 0.0074
-10.000 0.2299 0.08211 0.07766 -0.1190 0.5426 0.0075
-9.750 0.2371 0.07965 0.07516 -0.1197 0.5399 0.0075
-9.500 0.2444 0.07713 0.07265 -0.1203 0.5374 0.0077
-9.250 0.2517 0.07461 0.07014 -0.1209 0.5351 0.0077
-9.000 0.2588 0.07212 0.06765 -0.1215 0.5330 0.0078
-8.750 0.2660 0.06969 0.06521 -0.1221 0.5308 0.0078
-8.500 0.2732 0.06729 0.06280 -0.1227 0.5289 0.0079
-8.250 0.2804 0.06495 0.06044 -0.1232 0.5269 0.0079
-8.000 0.2875 0.06260 0.05807 -0.1238 0.5251 0.0080
-7.750 0.2945 0.06026 0.05575 -0.1244 0.5236 0.0081
-7.500 0.3014 0.05796 0.05347 -0.1250 0.5220 0.0081
-7.250 0.3083 0.05568 0.05120 -0.1255 0.5205 0.0081
-7.000 0.3141 0.05352 0.04906 -0.1261 0.5188 0.0082
-6.750 0.3206 0.05129 0.04683 -0.1265 0.5170 0.0082
-6.500 0.3245 0.04927 0.04484 -0.1271 0.5155 0.0082
-6.250 0.3291 0.04721 0.04279 -0.1272 0.5140 0.0083
-6.000 0.3117 0.06574 0.06108 -0.1338 0.5162 0.0082
-5.750 0.3226 0.06370 0.05903 -0.1352 0.5146 0.0082
-5.500 0.3353 0.06151 0.05683 -0.1376 0.5129 0.0082
-5.250 0.3514 0.05911 0.05441 -0.1409 0.5112 0.0082
-5.000 0.3714 0.05643 0.05172 -0.1453 0.5098 0.0083
-4.750 0.3930 0.05364 0.04894 -0.1498 0.5085 0.0083
-4.500 0.4206 0.05035 0.04563 -0.1562 0.5071 0.0083
-4.250 0.4502 0.04709 0.04234 -0.1621 0.5056 0.0083
-4.000 0.4696 0.04408 0.03931 -0.1648 0.5041 0.0085
-3.750 0.4932 0.04164 0.03684 -0.1679 0.5026 0.0088
-3.500 0.5267 0.03876 0.03388 -0.1734 0.5011 0.0090
-3.250 0.5655 0.03568 0.03067 -0.1796 0.4995 0.0094
-3.000 0.6090 0.03248 0.02729 -0.1862 0.4980 0.0101
-2.750 0.6583 0.02918 0.02373 -0.1928 0.4963 0.0110
-2.500 0.7158 0.02512 0.01921 -0.2003 0.4947 0.0118
-2.250 0.7507 0.02336 0.01739 -0.2038 0.4936 0.0128
-2.000 0.7948 0.02216 0.01570 -0.2066 0.4922 0.0156
-1.750 0.8349 0.01958 0.01303 -0.2111 0.4906 0.0178
-1.500 0.8742 0.01837 0.01149 -0.2138 0.4889 0.0229
-1.250 0.9081 0.01759 0.01058 -0.2156 0.4872 0.0267
-1.000 0.9439 0.01667 0.00947 -0.2177 0.4858 0.0341
-0.750 0.9768 0.01620 0.00888 -0.2193 0.4843 0.0486
0.250 1.1086 0.01457 0.00678 -0.2229 0.4788 0.0405
0.500 1.1410 0.01432 0.00649 -0.2237 0.4776 0.0287
0.750 1.1726 0.01421 0.00633 -0.2244 0.4761 0.0220
1.000 1.2051 0.01408 0.00618 -0.2255 0.4745 0.0197
1.250 1.2361 0.01404 0.00608 -0.2262 0.4728 0.0195
1.500 1.2664 0.01405 0.00600 -0.2269 0.4711 0.0256
1.750 1.2998 0.01393 0.00610 -0.2284 0.4694 0.1859
2.000 1.3383 0.01354 0.00675 -0.2313 0.4677 0.7816
2.250 1.3601 0.01367 0.00700 -0.2298 0.4662 0.8508
2.500 1.3861 0.01387 0.00721 -0.2296 0.4648 0.8695
2.750 1.4132 0.01396 0.00733 -0.2297 0.4636 0.8738
3.000 1.4406 0.01409 0.00747 -0.2299 0.4623 0.8781
3.250 1.4680 0.01421 0.00763 -0.2301 0.4607 0.8829
3.500 1.4948 0.01433 0.00777 -0.2302 0.4591 0.8889
3.750 1.5218 0.01445 0.00791 -0.2303 0.4575 0.8964
4.000 1.5477 0.01455 0.00804 -0.2302 0.4560 0.9072
4.250 1.5670 0.01456 0.00809 -0.2286 0.4547 1.0000
4.500 1.5960 0.01478 0.00832 -0.2292 0.4533 1.0000
4.750 1.6250 0.01507 0.00858 -0.2299 0.4519 1.0000
5.000 1.6538 0.01546 0.00896 -0.2306 0.4503 1.0000
5.250 1.6806 0.01563 0.00921 -0.2308 0.4491 1.0000
5.500 1.7074 0.01583 0.00949 -0.2310 0.4477 1.0000
5.750 1.7340 0.01602 0.00975 -0.2312 0.4459 1.0000
6.000 1.7605 0.01619 0.00997 -0.2313 0.4440 1.0000
6.250 1.7871 0.01636 0.01019 -0.2315 0.4421 1.0000
6.500 1.8138 0.01654 0.01040 -0.2317 0.4404 1.0000
6.750 1.8408 0.01676 0.01065 -0.2319 0.4388 1.0000
7.000 1.8680 0.01707 0.01098 -0.2323 0.4371 1.0000
7.250 1.8926 0.01730 0.01130 -0.2321 0.4345 1.0000
7.500 1.9151 0.01732 0.01145 -0.2314 0.4312 1.0000
7.750 1.9383 0.01729 0.01149 -0.2309 0.4272 1.0000
8.000 1.9618 0.01725 0.01145 -0.2303 0.4227 1.0000
8.250 1.9821 0.01726 0.01160 -0.2292 0.4175 1.0000
8.500 2.0020 0.01717 0.01161 -0.2280 0.4112 1.0000
8.750 2.0211 0.01717 0.01169 -0.2266 0.4036 1.0000
9.000 2.0379 0.01716 0.01174 -0.2248 0.3911 1.0000
9.250 2.0495 0.01744 0.01200 -0.2221 0.3686 1.0000
9.500 2.0392 0.01886 0.01312 -0.2157 0.3163 1.0000
9.750 2.0126 0.02167 0.01554 -0.2073 0.2593 1.0000
10.000 1.9824 0.02506 0.01867 -0.1994 0.2119 1.0000
10.250 1.9504 0.02906 0.02250 -0.1925 0.1744 1.0000
10.500 1.9217 0.03349 0.02687 -0.1875 0.1468 1.0000
10.750 1.8915 0.03892 0.03229 -0.1840 0.1241 1.0000
11.000 1.8645 0.04492 0.03832 -0.1820 0.1059 1.0000
11.250 1.8338 0.05210 0.04555 -0.1809 0.0903 1.0000
11.500 1.8064 0.05924 0.05276 -0.1803 0.0761 1.0000
11.750 1.7773 0.06679 0.06037 -0.1799 0.0624 1.0000
12.000 1.7470 0.07466 0.06827 -0.1797 0.0464 1.0000
12.250 1.7224 0.08190 0.07554 -0.1798 0.0329 1.0000
12.500 1.6978 0.08934 0.08298 -0.1801 0.0197 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX74_CL5_140 (fx74cl5140-il)