20-32C AIRFOIL (2032c-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: 20-32C AIRFOIL (2032c-il) Reynolds number: 500,000 Max Cl/Cd: 103.63 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-2032c-il-500000-n5.txt Download as CSV file: xf-2032c-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: 20-32C 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1785 0.09811 0.09595 -0.0313 0.9026 0.0085
-7.750 -0.1711 0.09539 0.09315 -0.0322 0.8758 0.0085
-7.500 -0.1629 0.09265 0.09031 -0.0333 0.8497 0.0085
-7.250 -0.1542 0.08988 0.08744 -0.0346 0.8238 0.0085
-7.000 -0.1438 0.08705 0.08451 -0.0366 0.7989 0.0086
-6.750 -0.1300 0.08395 0.08130 -0.0394 0.7759 0.0086
-6.500 -0.1146 0.08074 0.07800 -0.0426 0.7548 0.0086
-6.250 -0.0975 0.07742 0.07460 -0.0461 0.7365 0.0086
-6.000 -0.0319 0.05505 0.05214 -0.0472 0.6738 0.0081
-5.750 -0.0657 0.07106 0.06808 -0.0510 0.7030 0.0080
-5.500 -0.0442 0.06774 0.06469 -0.0553 0.6869 0.0076
-5.250 -0.0193 0.06408 0.06094 -0.0605 0.6717 0.0073
-5.000 0.0085 0.06026 0.05703 -0.0662 0.6573 0.0072
-4.750 0.0391 0.05636 0.05303 -0.0724 0.6432 0.0075
-4.500 0.0773 0.05147 0.04801 -0.0805 0.6293 0.0083
-4.250 0.1129 0.04738 0.04379 -0.0870 0.6144 0.0082
-4.000 0.1531 0.04282 0.03907 -0.0943 0.5996 0.0082
-3.750 0.2010 0.03697 0.03299 -0.1032 0.5860 0.0084
-3.500 0.2496 0.03130 0.02703 -0.1113 0.5731 0.0090
-3.250 0.2863 0.02865 0.02418 -0.1150 0.5588 0.0099
-3.000 0.3595 0.01350 0.00732 -0.1279 0.5506 0.0136
-2.750 0.3875 0.01364 0.00735 -0.1278 0.5343 0.0149
-2.500 0.4168 0.01315 0.00657 -0.1281 0.5180 0.0179
-2.250 0.4461 0.01260 0.00573 -0.1284 0.5021 0.0198
-2.000 0.4741 0.01268 0.00574 -0.1284 0.4874 0.0214
-1.750 0.5024 0.01268 0.00561 -0.1285 0.4733 0.0239
-1.500 0.5312 0.01241 0.00514 -0.1286 0.4595 0.0259
-1.250 0.5595 0.01235 0.00492 -0.1286 0.4451 0.0277
-1.000 0.5879 0.01221 0.00462 -0.1286 0.4310 0.0284
-0.750 0.6161 0.01213 0.00440 -0.1287 0.4178 0.0289
-0.500 0.6453 0.01149 0.00357 -0.1290 0.4064 0.0305
-0.250 0.6738 0.01126 0.00323 -0.1291 0.3954 0.0316
0.000 0.7022 0.01115 0.00303 -0.1292 0.3844 0.0331
0.250 0.7304 0.01110 0.00291 -0.1292 0.3736 0.0345
0.500 0.7585 0.01109 0.00282 -0.1293 0.3632 0.0357
0.750 0.7864 0.01113 0.00277 -0.1293 0.3530 0.0367
1.000 0.8144 0.01116 0.00273 -0.1293 0.3440 0.0374
1.250 0.8422 0.01122 0.00273 -0.1293 0.3364 0.0387
1.500 0.8700 0.01130 0.00275 -0.1293 0.3288 0.0399
1.750 0.8977 0.01139 0.00278 -0.1293 0.3222 0.0404
2.250 0.9529 0.01159 0.00290 -0.1292 0.3089 0.0479
2.500 0.9808 0.01158 0.00304 -0.1293 0.3030 0.1240
2.750 1.0085 0.01157 0.00325 -0.1295 0.2976 0.2439
3.000 1.0361 0.01161 0.00343 -0.1296 0.2933 0.3257
3.750 1.1124 0.01105 0.00394 -0.1285 0.2809 1.0000
4.000 1.1396 0.01122 0.00410 -0.1284 0.2774 1.0000
4.250 1.1665 0.01140 0.00427 -0.1283 0.2733 1.0000
4.500 1.1932 0.01162 0.00447 -0.1282 0.2696 1.0000
4.750 1.2196 0.01186 0.00469 -0.1280 0.2663 1.0000
5.000 1.2464 0.01203 0.00488 -0.1279 0.2619 1.0000
5.250 1.2722 0.01233 0.00510 -0.1277 0.2521 1.0000
5.500 1.2985 0.01253 0.00532 -0.1276 0.2434 1.0000
5.750 1.3242 0.01282 0.00556 -0.1274 0.2327 1.0000
6.000 1.3493 0.01317 0.00582 -0.1271 0.2166 1.0000
6.250 1.3724 0.01377 0.00622 -0.1266 0.1852 1.0000
6.500 1.3760 0.01700 0.00848 -0.1238 0.0217 1.0000
6.750 1.3993 0.01750 0.00901 -0.1232 0.0137 1.0000
7.000 1.4228 0.01795 0.00955 -0.1226 0.0119 1.0000
7.250 1.4451 0.01853 0.01022 -0.1219 0.0097 1.0000
7.500 1.4667 0.01916 0.01098 -0.1211 0.0084 1.0000
7.750 1.4881 0.01977 0.01169 -0.1202 0.0075 1.0000
8.000 1.5086 0.02044 0.01244 -0.1193 0.0067 1.0000
8.250 1.5261 0.02139 0.01348 -0.1180 0.0059 1.0000
8.500 1.5446 0.02215 0.01434 -0.1168 0.0055 1.0000
8.750 1.5607 0.02309 0.01539 -0.1153 0.0050 1.0000
9.000 1.5750 0.02411 0.01654 -0.1136 0.0047 1.0000
9.250 1.5871 0.02521 0.01774 -0.1116 0.0044 1.0000
9.500 1.5944 0.02642 0.01905 -0.1089 0.0042 1.0000
9.750 1.5959 0.02789 0.02064 -0.1056 0.0041 1.0000
10.000 1.5918 0.02994 0.02283 -0.1022 0.0039 1.0000
10.250 1.5945 0.03168 0.02470 -0.1000 0.0037 1.0000
10.500 1.5952 0.03377 0.02694 -0.0981 0.0035 1.0000
10.750 1.5932 0.03636 0.02966 -0.0966 0.0033 1.0000
11.000 1.5888 0.03950 0.03295 -0.0957 0.0032 1.0000
11.250 1.5819 0.04323 0.03683 -0.0952 0.0031 1.0000
11.500 1.5740 0.04741 0.04116 -0.0953 0.0031 1.0000
11.750 1.5645 0.05202 0.04591 -0.0957 0.0030 1.0000
12.000 1.5534 0.05705 0.05109 -0.0965 0.0030 1.0000
12.250 1.5412 0.06234 0.05652 -0.0974 0.0029 1.0000
12.500 1.5283 0.06780 0.06211 -0.0984 0.0029 1.0000
12.750 1.5151 0.07334 0.06778 -0.0994 0.0029 1.0000
13.000 1.5022 0.07888 0.07343 -0.1004 0.0028 1.0000
13.250 1.4903 0.08433 0.07899 -0.1015 0.0028 1.0000
13.500 1.4799 0.08962 0.08438 -0.1026 0.0027 1.0000
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Polar data table (+)
Polar graphs
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