LWK 80-080 (lwk80080-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: LWK 80-080 (lwk80080-il) Reynolds number: 1,000,000 Max Cl/Cd: 54.09 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lwk80080-il-1000000.txt Download as CSV file: xf-lwk80080-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: LWK 80-080
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.7286 0.03517 0.03353 -0.0267 1.0000 0.0047
-9.250 -0.7532 0.03059 0.02879 -0.0242 1.0000 0.0048
-9.000 -0.8617 0.03551 0.03293 -0.0143 1.0000 0.0044
-8.750 -0.8693 0.02968 0.02661 -0.0114 1.0000 0.0048
-8.500 -0.8418 0.03112 0.02815 -0.0118 1.0000 0.0052
-8.250 -0.8474 0.02390 0.02018 -0.0077 1.0000 0.0051
-8.000 -0.8279 0.02287 0.01901 -0.0068 1.0000 0.0054
-7.750 -0.8019 0.02360 0.01982 -0.0069 1.0000 0.0061
-7.500 -0.7892 0.02030 0.01610 -0.0045 1.0000 0.0061
-7.250 -0.7716 0.01821 0.01371 -0.0029 1.0000 0.0062
-7.000 -0.7515 0.01683 0.01214 -0.0015 1.0000 0.0067
-6.750 -0.7301 0.01587 0.01105 -0.0004 1.0000 0.0072
-6.500 -0.7089 0.01508 0.01015 0.0008 1.0000 0.0074
-6.250 -0.6874 0.01313 0.00798 0.0016 0.9911 0.0084
-6.000 -0.6545 0.01227 0.00706 0.0001 0.9823 0.0096
-5.750 -0.6200 0.01153 0.00623 -0.0017 0.9725 0.0102
-5.500 -0.5826 0.01083 0.00541 -0.0041 0.9647 0.0108
-5.250 -0.5425 0.01022 0.00473 -0.0071 0.9580 0.0115
-5.000 -0.5033 0.00956 0.00394 -0.0099 0.9494 0.0119
-4.750 -0.4658 0.00884 0.00310 -0.0122 0.9395 0.0172
-4.500 -0.4313 0.00852 0.00274 -0.0139 0.9290 0.0243
-4.250 -0.4010 0.00829 0.00249 -0.0146 0.9185 0.0324
-4.000 -0.3728 0.00806 0.00226 -0.0149 0.9094 0.0453
-3.750 -0.3463 0.00784 0.00207 -0.0147 0.9013 0.0632
-3.500 -0.3217 0.00757 0.00190 -0.0142 0.8938 0.0940
-3.250 -0.2987 0.00716 0.00171 -0.0134 0.8870 0.1572
-3.000 -0.2759 0.00682 0.00154 -0.0126 0.8808 0.2159
-2.750 -0.2590 0.00606 0.00133 -0.0107 0.8744 0.3703
-2.500 -0.2424 0.00537 0.00115 -0.0086 0.8685 0.5153
-2.250 -0.2254 0.00488 0.00106 -0.0064 0.8626 0.6356
-2.000 -0.2026 0.00474 0.00105 -0.0052 0.8579 0.6936
-1.750 -0.1788 0.00467 0.00106 -0.0042 0.8531 0.7244
-1.500 -0.1532 0.00465 0.00104 -0.0037 0.8486 0.7418
-1.250 -0.1268 0.00466 0.00103 -0.0033 0.8445 0.7560
-1.000 -0.1010 0.00464 0.00103 -0.0028 0.8397 0.7667
-0.750 -0.0757 0.00464 0.00104 -0.0021 0.8339 0.7802
-0.500 -0.0503 0.00465 0.00105 -0.0014 0.8270 0.7917
-0.250 -0.0257 0.00467 0.00105 -0.0006 0.8187 0.8032
0.000 0.0000 0.00465 0.00105 0.0000 0.8111 0.8109
0.250 0.0254 0.00467 0.00104 0.0007 0.8023 0.8189
0.500 0.0503 0.00465 0.00104 0.0015 0.7916 0.8270
0.750 0.0755 0.00464 0.00104 0.0021 0.7794 0.8340
1.000 0.1011 0.00464 0.00104 0.0027 0.7674 0.8396
1.250 0.1266 0.00466 0.00103 0.0033 0.7544 0.8444
1.500 0.1531 0.00465 0.00104 0.0037 0.7410 0.8486
1.750 0.1780 0.00468 0.00104 0.0044 0.7189 0.8532
2.000 0.2018 0.00476 0.00105 0.0054 0.6850 0.8580
2.250 0.2250 0.00490 0.00106 0.0064 0.6313 0.8626
2.500 0.2409 0.00547 0.00116 0.0089 0.4952 0.8685
2.750 0.2584 0.00609 0.00134 0.0108 0.3626 0.8743
3.000 0.2752 0.00687 0.00157 0.0127 0.2054 0.8808
3.250 0.2962 0.00737 0.00175 0.0138 0.1195 0.8875
3.500 0.3209 0.00763 0.00191 0.0143 0.0831 0.8941
3.750 0.3462 0.00785 0.00207 0.0148 0.0617 0.9013
4.000 0.3728 0.00807 0.00225 0.0149 0.0434 0.9093
4.250 0.4010 0.00828 0.00249 0.0146 0.0318 0.9183
4.500 0.4310 0.00856 0.00277 0.0140 0.0213 0.9289
4.750 0.4647 0.00909 0.00337 0.0125 0.0125 0.9401
5.000 0.5035 0.00959 0.00398 0.0099 0.0116 0.9496
5.250 0.5431 0.01021 0.00471 0.0070 0.0112 0.9581
5.500 0.5828 0.01087 0.00546 0.0040 0.0104 0.9649
5.750 0.6204 0.01147 0.00616 0.0015 0.0099 0.9726
6.000 0.6545 0.01231 0.00709 -0.0001 0.0093 0.9823
6.250 0.6873 0.01320 0.00807 -0.0016 0.0087 0.9912
6.500 0.7050 0.01629 0.01149 0.0001 0.0075 1.0000
6.750 0.7274 0.01680 0.01210 0.0010 0.0072 1.0000
7.000 0.7482 0.01791 0.01335 0.0022 0.0069 1.0000
7.250 0.7679 0.01943 0.01508 0.0036 0.0065 1.0000
7.500 0.7851 0.02157 0.01753 0.0053 0.0064 1.0000
7.750 0.8045 0.02288 0.01901 0.0064 0.0060 1.0000
8.000 0.8176 0.02578 0.02226 0.0084 0.0058 1.0000
8.250 0.8424 0.02531 0.02174 0.0084 0.0053 1.0000
8.500 0.8510 0.02886 0.02569 0.0106 0.0051 1.0000
8.750 0.8584 0.03235 0.02951 0.0126 0.0050 1.0000
10.750 0.6682 0.11161 0.11002 -0.0142 0.0076 1.0000
11.000 0.6694 0.11601 0.11443 -0.0163 0.0076 1.0000
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Polar data table (+)
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