20-32C AIRFOIL (2032c-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: 20-32C AIRFOIL (2032c-il) Reynolds number: 200,000 Max Cl/Cd: 76.59 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-2032c-il-200000-n5.txt Download as CSV file: xf-2032c-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2015 0.10516 0.10205 -0.0243 1.0000 0.0171
-8.000 -0.1961 0.10295 0.09990 -0.0251 1.0000 0.0177
-7.750 -0.1895 0.10098 0.09798 -0.0267 0.9963 0.0181
-7.500 -0.1699 0.09807 0.09508 -0.0325 0.9788 0.0185
-7.250 -0.1511 0.09505 0.09207 -0.0379 0.9598 0.0186
-7.000 -0.1295 0.09171 0.08871 -0.0439 0.9423 0.0187
-6.750 -0.1077 0.08823 0.08520 -0.0495 0.9248 0.0188
-6.500 -0.0872 0.08482 0.08176 -0.0540 0.9058 0.0188
-6.250 -0.0661 0.08149 0.07837 -0.0582 0.8866 0.0189
-6.000 -0.0449 0.07810 0.07490 -0.0623 0.8677 0.0190
-5.750 -0.0248 0.07435 0.07110 -0.0659 0.8485 0.0190
-5.500 -0.0131 0.06943 0.06612 -0.0673 0.8303 0.0195
-5.250 0.0023 0.06609 0.06269 -0.0680 0.8111 0.0199
-5.000 0.0227 0.06291 0.05941 -0.0704 0.7915 0.0202
-4.750 0.0487 0.05953 0.05591 -0.0747 0.7725 0.0203
-4.500 0.0856 0.05585 0.05205 -0.0817 0.7547 0.0184
-4.250 0.1067 0.05255 0.04862 -0.0837 0.7378 0.0174
-4.000 0.1393 0.04888 0.04481 -0.0889 0.7213 0.0168
-3.750 0.1850 0.04442 0.04012 -0.0971 0.7053 0.0181
-3.500 0.2268 0.04016 0.03563 -0.1034 0.6895 0.0184
-3.250 0.2678 0.03589 0.03109 -0.1090 0.6738 0.0184
-3.000 0.3146 0.03079 0.02562 -0.1153 0.6590 0.0189
-2.750 0.3418 0.02960 0.02427 -0.1168 0.6418 0.0211
-2.500 0.3785 0.02695 0.02130 -0.1197 0.6256 0.0233
-2.250 0.4229 0.02235 0.01607 -0.1238 0.6108 0.0250
-2.000 0.4615 0.01953 0.01246 -0.1258 0.5955 0.0290
-1.750 0.4934 0.01757 0.01006 -0.1271 0.5798 0.0316
-1.500 0.5223 0.01707 0.00929 -0.1274 0.5639 0.0358
-1.250 0.5525 0.01613 0.00790 -0.1277 0.5480 0.0377
-1.000 0.5812 0.01574 0.00717 -0.1277 0.5318 0.0401
-0.750 0.6100 0.01513 0.00625 -0.1278 0.5160 0.0412
-0.500 0.6385 0.01452 0.00544 -0.1279 0.5008 0.0422
0.000 0.6944 0.01396 0.00462 -0.1278 0.4722 0.0455
0.250 0.7222 0.01385 0.00439 -0.1278 0.4580 0.0474
0.500 0.7498 0.01383 0.00425 -0.1277 0.4440 0.0502
0.750 0.7772 0.01386 0.00416 -0.1276 0.4307 0.0536
1.000 0.8048 0.01385 0.00405 -0.1276 0.4186 0.0557
1.250 0.8323 0.01390 0.00401 -0.1275 0.4077 0.0595
1.750 0.8868 0.01393 0.00413 -0.1274 0.3866 0.1467
2.000 0.9139 0.01391 0.00432 -0.1274 0.3767 0.2788
3.000 1.0151 0.01366 0.00486 -0.1255 0.3450 1.0000
3.250 1.0413 0.01395 0.00505 -0.1253 0.3387 1.0000
3.500 1.0680 0.01420 0.00525 -0.1251 0.3321 1.0000
3.750 1.0940 0.01450 0.00548 -0.1249 0.3260 1.0000
4.000 1.1203 0.01478 0.00573 -0.1247 0.3205 1.0000
4.250 1.1464 0.01506 0.00599 -0.1244 0.3152 1.0000
4.500 1.1721 0.01539 0.00627 -0.1242 0.3108 1.0000
4.750 1.1981 0.01568 0.00659 -0.1239 0.3066 1.0000
5.000 1.2239 0.01598 0.00691 -0.1237 0.3022 1.0000
5.250 1.2493 0.01632 0.00724 -0.1234 0.2980 1.0000
5.500 1.2745 0.01669 0.00762 -0.1231 0.2942 1.0000
5.750 1.3001 0.01698 0.00799 -0.1228 0.2897 1.0000
6.000 1.3241 0.01735 0.00831 -0.1224 0.2806 1.0000
6.250 1.3483 0.01764 0.00860 -0.1220 0.2671 1.0000
6.500 1.3724 0.01795 0.00896 -0.1215 0.2542 1.0000
6.750 1.3958 0.01834 0.00932 -0.1211 0.2384 1.0000
7.000 1.4183 0.01883 0.00973 -0.1205 0.2124 1.0000
7.250 1.4362 0.01985 0.01043 -0.1194 0.1633 1.0000
7.500 1.4304 0.02364 0.01331 -0.1156 0.0210 1.0000
7.750 1.4485 0.02455 0.01439 -0.1143 0.0166 1.0000
8.000 1.4657 0.02550 0.01556 -0.1128 0.0144 1.0000
8.250 1.4820 0.02644 0.01669 -0.1113 0.0129 1.0000
8.500 1.4964 0.02750 0.01795 -0.1096 0.0119 1.0000
8.750 1.5078 0.02873 0.01939 -0.1076 0.0112 1.0000
9.000 1.5143 0.03010 0.02098 -0.1049 0.0106 1.0000
9.250 1.5165 0.03172 0.02279 -0.1019 0.0101 1.0000
9.500 1.5147 0.03377 0.02504 -0.0991 0.0096 1.0000
9.750 1.5065 0.03657 0.02809 -0.0965 0.0092 1.0000
10.250 1.4868 0.04366 0.03558 -0.0938 0.0086 1.0000
10.500 1.4820 0.04721 0.03929 -0.0936 0.0084 1.0000
10.750 1.4727 0.05163 0.04388 -0.0938 0.0083 1.0000
11.000 1.4619 0.05649 0.04891 -0.0945 0.0082 1.0000
11.250 1.4503 0.06167 0.05424 -0.0954 0.0081 1.0000
11.500 1.4382 0.06700 0.05972 -0.0964 0.0080 1.0000
11.750 1.4261 0.07237 0.06522 -0.0974 0.0079 1.0000
12.000 1.4145 0.07764 0.07061 -0.0983 0.0079 1.0000
12.250 1.4044 0.08269 0.07577 -0.0991 0.0078 1.0000
12.500 1.3960 0.08747 0.08064 -0.0998 0.0077 1.0000
12.750 1.3898 0.09184 0.08510 -0.1003 0.0076 1.0000
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Polar data table (+)
Polar graphs
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