LWK 80-100 (lwk80100-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: LWK 80-100 (lwk80100-il) Reynolds number: 50,000 Max Cl/Cd: 26.44 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lwk80100-il-50000-n5.txt Download as CSV file: xf-lwk80100-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6523 0.09359 0.08647 -0.0225 1.0000 0.0491
-10.500 -0.6674 0.08632 0.07922 -0.0273 1.0000 0.0485
-10.250 -0.6863 0.07999 0.07287 -0.0310 1.0000 0.0475
-10.000 -0.7070 0.07455 0.06737 -0.0330 1.0000 0.0463
-9.750 -0.7278 0.07007 0.06280 -0.0331 1.0000 0.0460
-9.500 -0.7456 0.06629 0.05887 -0.0317 1.0000 0.0459
-9.250 -0.7572 0.06260 0.05498 -0.0302 1.0000 0.0464
-9.000 -0.7654 0.05890 0.05102 -0.0284 1.0000 0.0473
-8.750 -0.7700 0.05516 0.04695 -0.0263 1.0000 0.0481
-8.500 -0.7700 0.05153 0.04294 -0.0243 1.0000 0.0487
-8.250 -0.7663 0.04798 0.03894 -0.0221 1.0000 0.0495
-8.000 -0.7589 0.04458 0.03503 -0.0200 1.0000 0.0508
-7.750 -0.7488 0.04162 0.03154 -0.0179 1.0000 0.0537
-7.500 -0.7335 0.03959 0.02945 -0.0167 1.0000 0.0575
-7.250 -0.7162 0.03724 0.02678 -0.0153 1.0000 0.0610
-7.000 -0.6954 0.03481 0.02384 -0.0139 1.0000 0.0650
-6.750 -0.6761 0.03305 0.02203 -0.0128 1.0000 0.0715
-6.500 -0.6522 0.03129 0.01992 -0.0118 1.0000 0.0785
-6.250 -0.6286 0.02967 0.01834 -0.0111 1.0000 0.0861
-6.000 -0.6063 0.02838 0.01697 -0.0100 1.0000 0.0975
-5.750 -0.5836 0.02712 0.01559 -0.0088 1.0000 0.1087
-5.500 -0.5669 0.02605 0.01456 -0.0071 1.0000 0.1245
-5.250 -0.5526 0.02500 0.01353 -0.0049 1.0000 0.1419
-5.000 -0.5412 0.02394 0.01259 -0.0023 1.0000 0.1662
-4.750 -0.5329 0.02282 0.01174 0.0006 1.0000 0.2038
-4.500 -0.5280 0.02153 0.01094 0.0039 1.0000 0.2693
-4.250 -0.5281 0.02001 0.01034 0.0083 1.0000 0.4034
-4.000 -0.5145 0.01986 0.01143 0.0139 1.0000 0.6372
-3.750 -0.5054 0.02018 0.01162 0.0186 1.0000 0.7149
-3.500 -0.4945 0.02054 0.01182 0.0230 1.0000 0.7640
-3.250 -0.4781 0.02101 0.01213 0.0267 1.0000 0.8049
-3.000 -0.4510 0.02164 0.01258 0.0290 1.0000 0.8455
-2.750 -0.4001 0.02245 0.01306 0.0272 1.0000 0.8854
-2.500 -0.3308 0.02289 0.01313 0.0206 1.0000 0.9090
-2.250 -0.2830 0.02283 0.01283 0.0166 1.0000 0.9224
-2.000 -0.2441 0.02269 0.01247 0.0139 1.0000 0.9335
-1.750 -0.2118 0.02253 0.01216 0.0121 1.0000 0.9442
-1.500 -0.1782 0.02237 0.01187 0.0100 1.0000 0.9535
-1.250 -0.1451 0.02221 0.01160 0.0079 1.0000 0.9617
-1.000 -0.1160 0.02210 0.01140 0.0065 1.0000 0.9706
-0.750 -0.0843 0.02198 0.01123 0.0045 1.0000 0.9785
-0.500 -0.0540 0.02189 0.01110 0.0027 1.0000 0.9861
-0.250 -0.0237 0.02183 0.01101 0.0008 1.0000 0.9940
0.000 0.0001 0.02186 0.01103 0.0000 1.0000 1.0000
0.250 0.0238 0.02183 0.01101 -0.0007 0.9940 1.0000
0.500 0.0543 0.02189 0.01110 -0.0027 0.9861 1.0000
0.750 0.0847 0.02198 0.01123 -0.0045 0.9783 1.0000
1.000 0.1160 0.02210 0.01140 -0.0064 0.9706 1.0000
1.250 0.1454 0.02221 0.01159 -0.0079 0.9616 1.0000
1.500 0.1784 0.02237 0.01187 -0.0100 0.9534 1.0000
1.750 0.2120 0.02253 0.01216 -0.0121 0.9441 1.0000
2.000 0.2442 0.02269 0.01247 -0.0138 0.9335 1.0000
2.250 0.2833 0.02283 0.01280 -0.0166 0.9223 1.0000
2.500 0.3315 0.02288 0.01313 -0.0207 0.9087 1.0000
2.750 0.4044 0.02239 0.01300 -0.0278 0.8845 1.0000
3.000 0.4531 0.02158 0.01251 -0.0292 0.8442 1.0000
3.250 0.4786 0.02097 0.01209 -0.0266 0.8035 1.0000
3.500 0.4946 0.02054 0.01182 -0.0229 0.7641 1.0000
3.750 0.5056 0.02019 0.01163 -0.0186 0.7154 1.0000
4.000 0.5148 0.01986 0.01143 -0.0139 0.6392 1.0000
4.250 0.5286 0.01999 0.01034 -0.0083 0.4074 1.0000
4.500 0.5286 0.02148 0.01093 -0.0039 0.2732 1.0000
4.750 0.5334 0.02279 0.01174 -0.0006 0.2070 1.0000
5.000 0.5418 0.02390 0.01260 0.0023 0.1690 1.0000
5.250 0.5530 0.02496 0.01350 0.0049 0.1441 1.0000
5.500 0.5672 0.02602 0.01451 0.0071 0.1254 1.0000
5.750 0.5837 0.02709 0.01557 0.0088 0.1090 1.0000
6.000 0.6062 0.02834 0.01694 0.0100 0.0979 1.0000
6.250 0.6283 0.02964 0.01831 0.0111 0.0860 1.0000
6.500 0.6523 0.03130 0.01995 0.0119 0.0782 1.0000
6.750 0.6754 0.03300 0.02196 0.0129 0.0706 1.0000
7.000 0.6952 0.03481 0.02389 0.0140 0.0644 1.0000
7.250 0.7161 0.03726 0.02681 0.0153 0.0606 1.0000
7.500 0.7330 0.03942 0.02923 0.0167 0.0564 1.0000
7.750 0.7475 0.04165 0.03153 0.0180 0.0526 1.0000
8.000 0.7579 0.04472 0.03522 0.0202 0.0502 1.0000
8.250 0.7652 0.04815 0.03915 0.0223 0.0489 1.0000
8.500 0.7685 0.05175 0.04319 0.0245 0.0480 1.0000
8.750 0.7685 0.05530 0.04710 0.0265 0.0473 1.0000
9.000 0.7649 0.05886 0.05098 0.0284 0.0465 1.0000
9.250 0.7580 0.06240 0.05477 0.0302 0.0457 1.0000
9.500 0.7481 0.06591 0.05846 0.0317 0.0447 1.0000
9.750 0.7297 0.06980 0.06249 0.0332 0.0451 1.0000
10.000 0.7081 0.07438 0.06719 0.0330 0.0458 1.0000
10.250 0.6860 0.07993 0.07280 0.0309 0.0463 1.0000
10.500 0.6660 0.08656 0.07945 0.0269 0.0475 1.0000
10.750 0.6512 0.09406 0.08692 0.0220 0.0487 1.0000
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Polar data table (+)
Polar graphs
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