20-32C AIRFOIL (2032c-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: 20-32C AIRFOIL (2032c-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.87 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-2032c-il-1000000-n5.txt Download as CSV file: xf-2032c-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1513 0.10998 0.10829 -0.0282 0.8796 0.0041
-10.250 -0.1460 0.10724 0.10546 -0.0286 0.8572 0.0042
-10.000 -0.2625 0.12001 0.11851 -0.0157 0.9896 0.0038
-9.750 -0.2494 0.11680 0.11526 -0.0183 0.9562 0.0039
-9.500 -0.2425 0.11431 0.11268 -0.0188 0.9188 0.0040
-9.250 -0.2359 0.11189 0.11013 -0.0191 0.8851 0.0042
-9.000 -0.2286 0.10936 0.10746 -0.0199 0.8528 0.0044
-8.750 -0.2205 0.10671 0.10468 -0.0208 0.8200 0.0046
-8.500 -0.2120 0.10396 0.10180 -0.0220 0.7896 0.0051
-8.250 -0.2027 0.10081 0.09855 -0.0237 0.7639 0.0056
-8.000 -0.1936 0.09788 0.09552 -0.0253 0.7397 0.0057
-7.750 -0.1842 0.09494 0.09251 -0.0272 0.7202 0.0057
-7.500 -0.1745 0.09204 0.08956 -0.0289 0.7035 0.0057
-7.250 -0.1645 0.08914 0.08660 -0.0308 0.6874 0.0057
-7.000 -0.1547 0.08632 0.08374 -0.0327 0.6720 0.0057
-6.750 -0.1408 0.08317 0.08053 -0.0357 0.6574 0.0057
-6.500 -0.0586 0.06098 0.05831 -0.0415 0.6062 0.0047
-6.250 -0.1106 0.07720 0.07446 -0.0417 0.6303 0.0049
-4.750 0.1600 0.01406 0.00929 -0.1269 0.5720 0.0057
-4.500 0.1917 0.01198 0.00670 -0.1284 0.5573 0.0061
-4.250 0.2215 0.01118 0.00564 -0.1289 0.5434 0.0067
-4.000 0.2508 0.01069 0.00494 -0.1292 0.5290 0.0073
-3.750 0.2799 0.01031 0.00436 -0.1295 0.5138 0.0079
-3.500 0.3089 0.01001 0.00387 -0.1296 0.4974 0.0085
-3.250 0.3379 0.00979 0.00355 -0.1298 0.4820 0.0104
-3.000 0.3666 0.00967 0.00332 -0.1299 0.4683 0.0123
-2.750 0.3951 0.00971 0.00331 -0.1299 0.4551 0.0147
-2.500 0.4233 0.00987 0.00342 -0.1298 0.4418 0.0169
-2.250 0.4515 0.01001 0.00347 -0.1297 0.4280 0.0185
-2.000 0.4798 0.01009 0.00347 -0.1297 0.4143 0.0192
-1.750 0.5085 0.00995 0.00323 -0.1299 0.4015 0.0208
-1.500 0.5367 0.01003 0.00326 -0.1299 0.3907 0.0222
-1.250 0.5652 0.00999 0.00312 -0.1299 0.3803 0.0233
-1.000 0.5937 0.00994 0.00299 -0.1300 0.3697 0.0245
-0.750 0.6223 0.00983 0.00278 -0.1301 0.3592 0.0254
-0.500 0.6508 0.00977 0.00263 -0.1302 0.3490 0.0264
-0.250 0.6792 0.00974 0.00251 -0.1302 0.3385 0.0273
0.000 0.7076 0.00974 0.00245 -0.1303 0.3303 0.0281
0.250 0.7358 0.00978 0.00243 -0.1303 0.3228 0.0286
0.500 0.7640 0.00981 0.00243 -0.1304 0.3158 0.0289
0.750 0.7925 0.00974 0.00227 -0.1305 0.3091 0.0301
1.000 0.8208 0.00974 0.00222 -0.1306 0.3030 0.0309
1.250 0.8489 0.00979 0.00222 -0.1306 0.2962 0.0315
1.500 0.8770 0.00983 0.00222 -0.1306 0.2910 0.0319
1.750 0.9051 0.00988 0.00224 -0.1307 0.2859 0.0327
2.000 0.9329 0.00997 0.00229 -0.1307 0.2812 0.0339
2.250 0.9609 0.01003 0.00234 -0.1307 0.2778 0.0344
2.500 0.9888 0.01010 0.00239 -0.1307 0.2741 0.0353
2.750 1.0165 0.01019 0.00247 -0.1307 0.2702 0.0377
3.000 1.0444 0.01024 0.00260 -0.1308 0.2660 0.0942
3.250 1.0726 0.01020 0.00276 -0.1310 0.2630 0.1933
3.500 1.1004 0.01023 0.00292 -0.1311 0.2597 0.2756
4.000 1.1517 0.00938 0.00335 -0.1307 0.2536 1.0000
4.250 1.1790 0.00953 0.00348 -0.1307 0.2510 1.0000
4.500 1.2064 0.00967 0.00362 -0.1306 0.2473 1.0000
4.750 1.2329 0.00992 0.00379 -0.1305 0.2374 1.0000
5.000 1.2599 0.01009 0.00394 -0.1305 0.2304 1.0000
5.250 1.2862 0.01035 0.00414 -0.1304 0.2201 1.0000
5.500 1.3120 0.01067 0.00437 -0.1302 0.2052 1.0000
5.750 1.3364 0.01118 0.00471 -0.1298 0.1793 1.0000
6.000 1.3446 0.01404 0.00668 -0.1274 0.0216 1.0000
6.250 1.3696 0.01438 0.00704 -0.1271 0.0137 1.0000
6.500 1.3945 0.01473 0.00742 -0.1268 0.0112 1.0000
6.750 1.4189 0.01514 0.00785 -0.1263 0.0086 1.0000
7.000 1.4433 0.01550 0.00824 -0.1259 0.0075 1.0000
7.250 1.4670 0.01595 0.00871 -0.1254 0.0063 1.0000
7.500 1.4905 0.01639 0.00920 -0.1249 0.0055 1.0000
7.750 1.5137 0.01683 0.00966 -0.1244 0.0048 1.0000
8.000 1.5362 0.01734 0.01020 -0.1237 0.0042 1.0000
8.250 1.5576 0.01795 0.01087 -0.1229 0.0038 1.0000
8.500 1.5791 0.01852 0.01149 -0.1221 0.0035 1.0000
8.750 1.5998 0.01912 0.01217 -0.1212 0.0032 1.0000
9.000 1.6202 0.01971 0.01280 -0.1203 0.0029 1.0000
9.250 1.6394 0.02036 0.01350 -0.1193 0.0027 1.0000
9.500 1.6555 0.02127 0.01449 -0.1178 0.0024 1.0000
9.750 1.6719 0.02207 0.01537 -0.1163 0.0023 1.0000
10.000 1.6862 0.02297 0.01637 -0.1146 0.0022 1.0000
10.250 1.6976 0.02395 0.01745 -0.1124 0.0021 1.0000
10.500 1.7042 0.02499 0.01857 -0.1095 0.0020 1.0000
10.750 1.7089 0.02618 0.01987 -0.1066 0.0019 1.0000
11.000 1.7128 0.02755 0.02136 -0.1039 0.0018 1.0000
11.250 1.7156 0.02915 0.02306 -0.1016 0.0018 1.0000
11.500 1.7184 0.03091 0.02492 -0.0996 0.0017 1.0000
11.750 1.7197 0.03299 0.02710 -0.0980 0.0016 1.0000
12.000 1.7184 0.03553 0.02975 -0.0967 0.0016 1.0000
12.250 1.7151 0.03855 0.03289 -0.0958 0.0016 1.0000
12.500 1.7083 0.04222 0.03669 -0.0954 0.0015 1.0000
12.750 1.6977 0.04670 0.04132 -0.0955 0.0015 1.0000
13.000 1.6839 0.05187 0.04663 -0.0960 0.0015 1.0000
13.250 1.6664 0.05783 0.05275 -0.0970 0.0014 1.0000
13.500 1.6454 0.06444 0.05952 -0.0982 0.0014 1.0000
13.750 1.6252 0.07105 0.06627 -0.0996 0.0014 1.0000
14.000 1.6047 0.07783 0.07319 -0.1010 0.0014 1.0000
14.250 1.5867 0.08431 0.07979 -0.1024 0.0014 1.0000
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Polar data table (+)
Polar graphs
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