WORTMANN FX 74-080 (fx74080-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 74-080 (fx74080-il) Reynolds number: 200,000 Max Cl/Cd: 86.97 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74080-il-200000-n5.txt Download as CSV file: xf-fx74080-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 74-080
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3394 0.13062 0.12709 -0.0432 1.0000 0.0094
-11.000 -0.3354 0.12753 0.12397 -0.0435 1.0000 0.0097
-10.750 -0.3304 0.12431 0.12080 -0.0441 0.9930 0.0099
-10.500 -0.3185 0.12041 0.11690 -0.0471 0.9816 0.0103
-10.250 -0.3057 0.11651 0.11298 -0.0506 0.9727 0.0104
-9.750 -0.2779 0.10856 0.10501 -0.0581 0.9592 0.0114
-9.500 -0.2621 0.10456 0.10099 -0.0625 0.9542 0.0114
-9.250 -0.2456 0.10046 0.09686 -0.0672 0.9492 0.0115
-9.000 -0.2286 0.09650 0.09288 -0.0719 0.9435 0.0118
-8.750 -0.2112 0.09233 0.08867 -0.0769 0.9381 0.0126
-8.500 -0.1944 0.08837 0.08468 -0.0818 0.9315 0.0132
-8.250 -0.1763 0.08444 0.08072 -0.0869 0.9260 0.0135
-8.000 -0.1611 0.08063 0.07689 -0.0915 0.9194 0.0138
-7.750 -0.1406 0.07726 0.07349 -0.0996 0.9120 0.0171
-7.500 -0.1277 0.07407 0.07030 -0.1046 0.9043 0.0174
-7.000 -0.0986 0.06673 0.06288 -0.1145 0.8931 0.0176
-6.750 -0.0832 0.06290 0.05899 -0.1189 0.8885 0.0177
-6.250 -0.0691 0.05480 0.05083 -0.1217 0.8800 0.0148
-6.000 -0.0536 0.05092 0.04686 -0.1249 0.8759 0.0141
-5.750 -0.0350 0.04698 0.04278 -0.1281 0.8727 0.0137
-5.250 -0.0001 0.04102 0.03656 -0.1313 0.8647 0.0228
-5.000 0.0219 0.03726 0.03254 -0.1328 0.8615 0.0221
-4.750 0.0479 0.03343 0.02827 -0.1332 0.8587 0.0163
-4.500 0.0668 0.03036 0.02494 -0.1331 0.8550 0.0154
-4.250 0.0891 0.02744 0.02169 -0.1330 0.8517 0.0145
-4.000 0.1136 0.02470 0.01857 -0.1328 0.8490 0.0137
-3.750 0.1398 0.02223 0.01566 -0.1327 0.8467 0.0131
-3.500 0.1632 0.02011 0.01315 -0.1317 0.8434 0.0127
-3.250 0.1880 0.01831 0.01096 -0.1309 0.8404 0.0127
-3.000 0.2141 0.01680 0.00910 -0.1303 0.8377 0.0129
-2.750 0.2408 0.01558 0.00764 -0.1299 0.8354 0.0135
-2.500 0.2678 0.01461 0.00650 -0.1296 0.8334 0.0154
-2.250 0.2905 0.01406 0.00591 -0.1288 0.8301 0.0211
-2.000 0.3144 0.01345 0.00516 -0.1281 0.8270 0.0241
-1.750 0.3400 0.01305 0.00462 -0.1277 0.8244 0.0281
-1.500 0.3664 0.01262 0.00416 -0.1275 0.8220 0.0511
-1.250 0.3881 0.01152 0.00408 -0.1272 0.8197 0.3545
-1.000 0.3936 0.01043 0.00442 -0.1221 0.8158 0.8210
-0.750 0.4179 0.01031 0.00436 -0.1208 0.8129 0.9169
-0.500 0.4809 0.01014 0.00408 -0.1284 0.8118 1.0000
-0.250 0.5061 0.01021 0.00401 -0.1281 0.8091 1.0000
0.000 0.5330 0.01028 0.00397 -0.1281 0.8070 1.0000
0.250 0.5538 0.01042 0.00408 -0.1269 0.8027 1.0000
0.500 0.5783 0.01052 0.00413 -0.1264 0.7992 1.0000
0.750 0.6046 0.01060 0.00416 -0.1263 0.7964 1.0000
1.000 0.6324 0.01067 0.00420 -0.1265 0.7941 1.0000
1.250 0.6544 0.01083 0.00438 -0.1256 0.7897 1.0000
1.500 0.6792 0.01095 0.00451 -0.1252 0.7860 1.0000
1.750 0.7060 0.01103 0.00459 -0.1251 0.7831 1.0000
2.000 0.7342 0.01110 0.00467 -0.1254 0.7806 1.0000
2.250 0.7554 0.01129 0.00494 -0.1243 0.7754 1.0000
2.500 0.7810 0.01139 0.00518 -0.1240 0.7715 1.0000
2.750 0.8087 0.01146 0.00531 -0.1241 0.7686 1.0000
3.000 0.8319 0.01162 0.00558 -0.1234 0.7638 1.0000
3.250 0.8564 0.01175 0.00583 -0.1228 0.7591 1.0000
3.500 0.8826 0.01167 0.00586 -0.1224 0.7517 1.0000
3.750 0.9019 0.01088 0.00505 -0.1194 0.7145 1.0000
4.000 0.9210 0.01059 0.00474 -0.1169 0.6657 1.0000
4.250 0.9188 0.01149 0.00452 -0.1100 0.4737 1.0000
4.500 0.8900 0.01428 0.00576 -0.1000 0.2096 1.0000
4.750 0.8772 0.01660 0.00716 -0.0934 0.0279 1.0000
5.000 0.8887 0.01744 0.00810 -0.0904 0.0181 1.0000
5.250 0.9012 0.01829 0.00913 -0.0875 0.0149 1.0000
5.500 0.9128 0.01919 0.01011 -0.0849 0.0115 1.0000
5.750 0.9206 0.02039 0.01142 -0.0817 0.0089 1.0000
6.000 0.9309 0.02156 0.01268 -0.0789 0.0081 1.0000
6.250 0.9426 0.02291 0.01413 -0.0763 0.0076 1.0000
6.500 0.9593 0.02445 0.01575 -0.0745 0.0072 1.0000
6.750 0.9860 0.02629 0.01770 -0.0741 0.0070 1.0000
7.000 1.0275 0.02882 0.02044 -0.0761 0.0068 1.0000
7.250 1.0696 0.03194 0.02388 -0.0782 0.0070 1.0000
7.500 1.1000 0.03513 0.02744 -0.0783 0.0071 1.0000
7.750 1.1226 0.03851 0.03132 -0.0771 0.0074 1.0000
8.000 1.1385 0.04179 0.03498 -0.0751 0.0077 1.0000
8.250 1.1495 0.04521 0.03876 -0.0725 0.0079 1.0000
8.500 1.1554 0.04873 0.04262 -0.0694 0.0082 1.0000
8.750 1.1574 0.05216 0.04636 -0.0661 0.0084 1.0000
9.000 1.1542 0.05586 0.05036 -0.0623 0.0087 1.0000
9.250 1.1456 0.05956 0.05432 -0.0582 0.0090 1.0000
9.500 1.1332 0.06304 0.05801 -0.0539 0.0092 1.0000
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Polar data table (+)
Polar graphs
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