WORTMANN FX 74-080 (fx74080-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 74-080 (fx74080-il) Reynolds number: 1,000,000 Max Cl/Cd: 173.95 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx74080-il-1000000.txt Download as CSV file: xf-fx74080-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.1873 0.09008 0.08776 -0.0839 0.8579 0.0056
-8.750 -0.1748 0.08690 0.08457 -0.0871 0.8553 0.0058
-8.500 -0.1628 0.08364 0.08131 -0.0904 0.8525 0.0059
-5.250 0.0374 0.02964 0.02647 -0.1395 0.8180 0.0068
-5.000 0.0574 0.02646 0.02310 -0.1396 0.8161 0.0069
-4.750 0.0784 0.02623 0.02284 -0.1400 0.8143 0.0090
-3.000 0.2479 0.01196 0.00687 -0.1361 0.8015 0.0112
-2.750 0.2722 0.00984 0.00447 -0.1350 0.7996 0.0092
-2.500 0.2968 0.00877 0.00327 -0.1342 0.7977 0.0093
-2.250 0.3225 0.00828 0.00270 -0.1338 0.7958 0.0112
-2.000 0.3496 0.00816 0.00254 -0.1338 0.7941 0.0132
-1.750 0.3752 0.00767 0.00192 -0.1334 0.7922 0.0146
-1.500 0.4019 0.00744 0.00158 -0.1332 0.7902 0.0173
-1.250 0.4270 0.00710 0.00144 -0.1327 0.7883 0.0840
-1.000 0.4511 0.00667 0.00140 -0.1324 0.7861 0.2344
-0.750 0.4718 0.00595 0.00141 -0.1315 0.7837 0.5114
-0.500 0.4846 0.00521 0.00157 -0.1282 0.7813 0.8475
-0.250 0.5106 0.00521 0.00156 -0.1278 0.7794 0.8687
0.000 0.5362 0.00523 0.00159 -0.1274 0.7772 0.8916
0.250 0.5587 0.00515 0.00161 -0.1261 0.7749 0.9225
0.500 0.5837 0.00509 0.00160 -0.1254 0.7722 0.9456
0.750 0.6186 0.00503 0.00157 -0.1271 0.7699 0.9681
1.000 0.6619 0.00503 0.00157 -0.1309 0.7678 0.9817
1.250 0.7010 0.00505 0.00158 -0.1337 0.7656 0.9869
1.500 0.7368 0.00508 0.00161 -0.1358 0.7630 0.9904
2.000 0.7885 0.00512 0.00170 -0.1354 0.7564 1.0000
2.250 0.8141 0.00514 0.00175 -0.1351 0.7528 1.0000
2.500 0.8368 0.00508 0.00171 -0.1340 0.7426 1.0000
2.750 0.8582 0.00501 0.00160 -0.1326 0.7250 1.0000
3.000 0.8767 0.00504 0.00153 -0.1305 0.6863 1.0000
3.250 0.8880 0.00551 0.00166 -0.1269 0.6101 1.0000
3.500 0.8862 0.00678 0.00217 -0.1210 0.4496 1.0000
4.000 0.8719 0.01065 0.00405 -0.1080 0.0145 1.0000
4.250 0.8930 0.01101 0.00447 -0.1068 0.0099 1.0000
4.500 0.9102 0.01164 0.00521 -0.1047 0.0076 1.0000
4.750 0.9240 0.01247 0.00617 -0.1020 0.0068 1.0000
5.000 0.9463 0.01273 0.00644 -0.1011 0.0056 1.0000
5.250 0.9594 0.01356 0.00736 -0.0982 0.0050 1.0000
5.500 0.9684 0.01458 0.00848 -0.0945 0.0049 1.0000
5.750 0.9772 0.01598 0.00998 -0.0909 0.0050 1.0000
6.000 0.9957 0.01762 0.01171 -0.0891 0.0054 1.0000
8.750 1.2128 0.04631 0.04269 -0.0733 0.0042 1.0000
9.000 1.2159 0.04828 0.04481 -0.0704 0.0038 1.0000
9.250 1.2161 0.04956 0.04618 -0.0676 0.0035 1.0000
9.500 1.2124 0.05277 0.04964 -0.0636 0.0035 1.0000
9.750 1.1995 0.05481 0.05181 -0.0589 0.0033 1.0000
10.000 1.1878 0.05756 0.05472 -0.0543 0.0033 1.0000
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Polar data table (+)
Polar graphs
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