WORTMANN FX 80-080 (fx80080-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 80-080 (fx80080-il) Reynolds number: 500,000 Max Cl/Cd: 113.19 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx80080-il-500000.txt Download as CSV file: xf-fx80080-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 80-080
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4616 0.07694 0.07486 -0.0388 1.0000 0.0135
-7.750 -0.4777 0.07221 0.07020 -0.0413 1.0000 0.0137
-7.500 -0.4827 0.06797 0.06595 -0.0434 0.9989 0.0137
-7.250 -0.4646 0.06133 0.05922 -0.0516 0.9937 0.0143
-7.000 -0.4419 0.05667 0.05446 -0.0575 0.9894 0.0149
-6.750 -0.4185 0.05135 0.04900 -0.0632 0.9833 0.0153
-6.500 -0.3917 0.04659 0.04405 -0.0682 0.9790 0.0169
-6.250 -0.3541 0.04314 0.04028 -0.0712 0.9742 0.0208
-6.000 -0.3269 0.03871 0.03552 -0.0741 0.9690 0.0209
-5.000 -0.2113 0.01683 0.01167 -0.0831 0.9532 0.0166
-4.750 -0.1753 0.01430 0.00875 -0.0848 0.9510 0.0167
-4.500 -0.1455 0.01306 0.00734 -0.0852 0.9449 0.0178
-4.250 -0.1112 0.01229 0.00643 -0.0867 0.9407 0.0197
-4.000 -0.0755 0.01152 0.00554 -0.0885 0.9374 0.0207
-3.750 -0.0501 0.01012 0.00400 -0.0881 0.9304 0.0230
-3.500 -0.0186 0.00956 0.00339 -0.0891 0.9256 0.0274
-3.250 0.0106 0.00918 0.00294 -0.0894 0.9201 0.0334
-3.000 0.0380 0.00871 0.00247 -0.0894 0.9142 0.0532
-2.750 0.0681 0.00831 0.00220 -0.0902 0.9098 0.0992
-2.500 0.0910 0.00765 0.00204 -0.0897 0.9035 0.2411
-2.250 0.1115 0.00644 0.00190 -0.0891 0.8981 0.5600
-2.000 0.1343 0.00614 0.00201 -0.0879 0.8931 0.7145
-1.750 0.1596 0.00615 0.00207 -0.0871 0.8880 0.7565
-1.500 0.1871 0.00618 0.00208 -0.0869 0.8839 0.7785
-1.250 0.2136 0.00625 0.00213 -0.0865 0.8796 0.7992
-1.000 0.2389 0.00629 0.00217 -0.0858 0.8748 0.8156
-0.750 0.2656 0.00633 0.00220 -0.0854 0.8705 0.8303
-0.500 0.2908 0.00639 0.00227 -0.0846 0.8662 0.8469
-0.250 0.3143 0.00643 0.00234 -0.0833 0.8610 0.8635
0.000 0.3397 0.00645 0.00236 -0.0826 0.8561 0.8764
0.250 0.3643 0.00645 0.00237 -0.0817 0.8501 0.8862
0.500 0.3902 0.00645 0.00236 -0.0812 0.8438 0.8938
0.750 0.4163 0.00644 0.00234 -0.0807 0.8374 0.8996
1.000 0.4419 0.00641 0.00232 -0.0801 0.8298 0.9060
1.250 0.4673 0.00638 0.00231 -0.0795 0.8216 0.9125
1.500 0.4934 0.00635 0.00225 -0.0789 0.8126 0.9189
1.750 0.5175 0.00629 0.00221 -0.0779 0.8014 0.9261
2.000 0.5421 0.00623 0.00218 -0.0771 0.7900 0.9342
2.250 0.5676 0.00618 0.00217 -0.0764 0.7780 0.9431
2.500 0.5950 0.00614 0.00216 -0.0762 0.7656 0.9535
2.750 0.6260 0.00612 0.00215 -0.0768 0.7487 0.9646
3.000 0.6607 0.00614 0.00216 -0.0783 0.7271 0.9756
3.500 0.7199 0.00636 0.00228 -0.0793 0.6585 1.0000
3.750 0.7326 0.00693 0.00239 -0.0762 0.5512 1.0000
4.000 0.7413 0.00805 0.00280 -0.0727 0.4025 1.0000
4.250 0.7543 0.00915 0.00326 -0.0702 0.2699 1.0000
4.500 0.7710 0.01008 0.00371 -0.0685 0.1708 1.0000
4.750 0.7908 0.01078 0.00414 -0.0673 0.1114 1.0000
5.000 0.8122 0.01136 0.00456 -0.0663 0.0781 1.0000
5.250 0.8339 0.01193 0.00501 -0.0653 0.0559 1.0000
5.500 0.8555 0.01252 0.00557 -0.0642 0.0406 1.0000
5.750 0.8754 0.01331 0.00635 -0.0628 0.0305 1.0000
6.000 0.8992 0.01367 0.00677 -0.0621 0.0263 1.0000
6.250 0.9184 0.01453 0.00769 -0.0606 0.0217 1.0000
6.500 0.9390 0.01527 0.00851 -0.0594 0.0193 1.0000
6.750 0.9625 0.01562 0.00888 -0.0588 0.0159 1.0000
7.000 0.9742 0.01773 0.01113 -0.0559 0.0131 1.0000
7.250 0.9969 0.01831 0.01181 -0.0550 0.0122 1.0000
7.500 1.0177 0.01930 0.01290 -0.0538 0.0108 1.0000
7.750 1.0380 0.02048 0.01420 -0.0526 0.0099 1.0000
8.000 1.0578 0.02191 0.01580 -0.0513 0.0093 1.0000
8.250 1.0768 0.02383 0.01791 -0.0500 0.0089 1.0000
8.500 1.0945 0.02624 0.02058 -0.0485 0.0087 1.0000
8.750 1.1047 0.03026 0.02500 -0.0462 0.0082 1.0000
9.000 1.1125 0.03322 0.02839 -0.0434 0.0077 1.0000
9.250 1.1203 0.03582 0.03132 -0.0407 0.0076 1.0000
9.500 1.1192 0.03947 0.03535 -0.0372 0.0076 1.0000
9.750 1.1137 0.04308 0.03930 -0.0333 0.0076 1.0000
10.000 1.1059 0.04603 0.04253 -0.0291 0.0073 1.0000
10.250 1.0738 0.05085 0.04761 -0.0233 0.0078 1.0000
10.500 1.0437 0.05901 0.05628 -0.0185 0.0095 1.0000
10.750 1.0383 0.05783 0.05500 -0.0177 0.0077 1.0000
11.000 0.9382 0.05301 0.05044 -0.0138 0.0081 1.0000
11.250 0.9188 0.05836 0.05593 -0.0144 0.0081 1.0000
11.500 0.9027 0.06367 0.06138 -0.0159 0.0082 1.0000
11.750 0.8803 0.07069 0.06853 -0.0189 0.0082 1.0000
12.000 0.8583 0.07854 0.07653 -0.0233 0.0083 1.0000
12.250 0.8388 0.08716 0.08528 -0.0290 0.0084 1.0000
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Polar data table (+)
Polar graphs
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