LWK 80-100 (lwk80100-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: LWK 80-100 (lwk80100-il) Reynolds number: 50,000 Max Cl/Cd: 26.16 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lwk80100-il-50000.txt Download as CSV file: xf-lwk80100-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: LWK 80-100
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5453 0.09877 0.09166 0.0099 1.0000 0.3896
-8.750 -0.5983 0.06101 0.05472 -0.0291 1.0000 0.1591
-8.500 -0.7268 0.07008 0.06324 -0.0244 1.0000 0.1516
-8.250 -0.7373 0.06428 0.05715 -0.0241 1.0000 0.1382
-8.000 -0.7400 0.05943 0.05197 -0.0228 1.0000 0.1303
-7.750 -0.7429 0.05471 0.04685 -0.0210 1.0000 0.1252
-7.500 -0.7487 0.05110 0.04234 -0.0177 1.0000 0.1208
-7.250 -0.7332 0.04738 0.03870 -0.0167 1.0000 0.1256
-7.000 -0.7237 0.04416 0.03510 -0.0144 1.0000 0.1278
-6.750 -0.7121 0.04086 0.03134 -0.0120 1.0000 0.1286
-6.500 -0.6983 0.03798 0.02798 -0.0096 1.0000 0.1313
-6.250 -0.6831 0.03548 0.02524 -0.0076 1.0000 0.1397
-6.000 -0.6652 0.03321 0.02256 -0.0055 1.0000 0.1474
-5.750 -0.6434 0.03084 0.02009 -0.0042 1.0000 0.1578
-5.500 -0.6230 0.02899 0.01812 -0.0026 1.0000 0.1746
-5.250 -0.5949 0.02695 0.01600 -0.0018 1.0000 0.1938
-5.000 -0.5702 0.02521 0.01452 -0.0008 1.0000 0.2277
-4.750 -0.5490 0.02336 0.01299 0.0009 1.0000 0.2783
-4.500 -0.5452 0.02099 0.01174 0.0051 1.0000 0.3790
-4.250 -0.5468 0.02196 0.01479 0.0196 1.0000 0.7613
-4.000 -0.2009 0.02697 0.01717 -0.0189 1.0000 0.9651
-3.750 -0.1119 0.02484 0.01451 -0.0326 1.0000 1.0000
-3.500 -0.0974 0.02418 0.01375 -0.0321 1.0000 1.0000
-3.250 -0.0828 0.02360 0.01308 -0.0315 1.0000 1.0000
-3.000 -0.0684 0.02311 0.01251 -0.0307 1.0000 1.0000
-2.750 -0.0546 0.02268 0.01203 -0.0297 1.0000 1.0000
-2.500 -0.0417 0.02234 0.01164 -0.0284 1.0000 1.0000
-2.250 -0.0304 0.02206 0.01133 -0.0269 1.0000 1.0000
-2.000 -0.0211 0.02188 0.01112 -0.0249 1.0000 1.0000
-1.750 -0.0142 0.02177 0.01101 -0.0226 1.0000 1.0000
-1.500 -0.0098 0.02174 0.01097 -0.0198 1.0000 1.0000
-1.250 -0.0075 0.02176 0.01098 -0.0166 1.0000 1.0000
-1.000 -0.0060 0.02179 0.01099 -0.0133 1.0000 1.0000
-0.750 -0.0048 0.02182 0.01101 -0.0099 1.0000 1.0000
-0.500 -0.0033 0.02185 0.01102 -0.0066 1.0000 1.0000
-0.250 -0.0017 0.02186 0.01103 -0.0033 1.0000 1.0000
0.000 0.0001 0.02186 0.01103 0.0000 1.0000 1.0000
0.250 0.0018 0.02186 0.01103 0.0033 1.0000 1.0000
0.500 0.0034 0.02185 0.01102 0.0066 1.0000 1.0000
0.750 0.0049 0.02182 0.01101 0.0099 1.0000 1.0000
1.000 0.0062 0.02179 0.01100 0.0133 1.0000 1.0000
1.250 0.0076 0.02175 0.01097 0.0166 1.0000 1.0000
1.500 0.0099 0.02174 0.01097 0.0198 1.0000 1.0000
1.750 0.0143 0.02177 0.01101 0.0226 1.0000 1.0000
2.000 0.0213 0.02187 0.01112 0.0250 1.0000 1.0000
2.250 0.0305 0.02206 0.01132 0.0269 1.0000 1.0000
2.500 0.0419 0.02233 0.01162 0.0285 1.0000 1.0000
2.750 0.0548 0.02268 0.01203 0.0297 1.0000 1.0000
3.000 0.0686 0.02310 0.01251 0.0307 1.0000 1.0000
3.250 0.0830 0.02360 0.01308 0.0315 1.0000 1.0000
3.500 0.0976 0.02417 0.01374 0.0321 1.0000 1.0000
3.750 0.1123 0.02483 0.01451 0.0326 1.0000 1.0000
4.000 0.2024 0.02697 0.01717 0.0187 0.9643 1.0000
4.250 0.5471 0.02201 0.01484 -0.0198 0.7628 1.0000
4.500 0.5465 0.02089 0.01173 -0.0053 0.3854 1.0000
4.750 0.5502 0.02330 0.01302 -0.0010 0.2815 1.0000
5.000 0.5706 0.02516 0.01448 0.0008 0.2303 1.0000
5.250 0.5947 0.02686 0.01598 0.0019 0.1955 1.0000
5.500 0.6229 0.02896 0.01809 0.0026 0.1748 1.0000
5.750 0.6430 0.03080 0.02005 0.0042 0.1569 1.0000
6.000 0.6651 0.03320 0.02256 0.0056 0.1472 1.0000
6.250 0.6832 0.03545 0.02516 0.0076 0.1385 1.0000
6.500 0.6977 0.03796 0.02800 0.0098 0.1303 1.0000
6.750 0.7118 0.04093 0.03143 0.0121 0.1278 1.0000
7.000 0.7237 0.04408 0.03499 0.0144 0.1260 1.0000
7.250 0.7401 0.04759 0.03838 0.0155 0.1208 1.0000
7.500 0.7445 0.05089 0.04230 0.0183 0.1199 1.0000
7.750 0.7547 0.05519 0.04681 0.0198 0.1209 1.0000
8.000 0.7386 0.05956 0.05212 0.0230 0.1296 1.0000
8.250 0.7432 0.06443 0.05720 0.0240 0.1367 1.0000
8.500 0.6326 0.05467 0.04829 0.0293 0.1430 1.0000
8.750 0.6242 0.06000 0.05369 0.0297 0.1510 1.0000
9.000 0.5883 0.06640 0.06013 0.0288 0.1648 1.0000
9.250 0.5512 0.10236 0.09524 -0.0093 0.3708 1.0000
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Polar data table (+)
Polar graphs
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