LWK 80-100 (lwk80100-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: LWK 80-100 (lwk80100-il) Reynolds number: 200,000 Max Cl/Cd: 38.32 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lwk80100-il-200000-n5.txt Download as CSV file: xf-lwk80100-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.7206 0.08852 0.08503 -0.0162 1.0000 0.0137
-11.500 -0.7737 0.06829 0.06465 -0.0308 1.0000 0.0129
-11.250 -0.8086 0.05974 0.05587 -0.0355 1.0000 0.0125
-11.000 -0.8370 0.05379 0.04967 -0.0365 1.0000 0.0124
-10.750 -0.8588 0.04936 0.04499 -0.0354 1.0000 0.0125
-10.500 -0.8773 0.04567 0.04102 -0.0327 1.0000 0.0127
-10.250 -0.8909 0.04230 0.03734 -0.0292 1.0000 0.0128
-10.000 -0.8959 0.03903 0.03371 -0.0263 1.0000 0.0128
-9.750 -0.8952 0.03605 0.03036 -0.0237 1.0000 0.0132
-9.500 -0.8897 0.03333 0.02728 -0.0213 1.0000 0.0135
-9.250 -0.8800 0.03093 0.02452 -0.0193 1.0000 0.0139
-9.000 -0.8669 0.02884 0.02209 -0.0174 1.0000 0.0147
-8.750 -0.8511 0.02709 0.02004 -0.0159 1.0000 0.0152
-8.500 -0.8357 0.02532 0.01809 -0.0143 1.0000 0.0160
-8.250 -0.8184 0.02420 0.01689 -0.0130 1.0000 0.0169
-8.000 -0.8000 0.02353 0.01612 -0.0119 1.0000 0.0184
-7.750 -0.7818 0.02237 0.01482 -0.0104 1.0000 0.0195
-7.500 -0.7639 0.02127 0.01359 -0.0088 1.0000 0.0207
-7.250 -0.7466 0.02036 0.01254 -0.0072 1.0000 0.0218
-7.000 -0.7333 0.01925 0.01143 -0.0049 0.9962 0.0237
-6.750 -0.7019 0.01850 0.01061 -0.0063 0.9850 0.0271
-6.500 -0.6697 0.01781 0.00978 -0.0078 0.9759 0.0307
-6.250 -0.6387 0.01691 0.00886 -0.0091 0.9670 0.0358
-6.000 -0.6059 0.01635 0.00820 -0.0106 0.9597 0.0413
-5.750 -0.5749 0.01561 0.00746 -0.0118 0.9526 0.0486
-5.500 -0.5440 0.01504 0.00684 -0.0130 0.9458 0.0569
-5.250 -0.5127 0.01456 0.00627 -0.0141 0.9397 0.0662
-5.000 -0.4836 0.01404 0.00578 -0.0148 0.9328 0.0800
-4.750 -0.4539 0.01354 0.00532 -0.0156 0.9271 0.0989
-4.500 -0.4284 0.01307 0.00492 -0.0155 0.9203 0.1264
-4.250 -0.4026 0.01251 0.00455 -0.0156 0.9148 0.1743
-4.000 -0.3809 0.01188 0.00422 -0.0149 0.9085 0.2450
-3.750 -0.3624 0.01112 0.00389 -0.0136 0.9022 0.3489
-3.500 -0.3472 0.01031 0.00363 -0.0115 0.8965 0.4769
-3.250 -0.3317 0.00980 0.00368 -0.0088 0.8907 0.6043
-3.000 -0.3079 0.00976 0.00381 -0.0076 0.8865 0.6729
-2.750 -0.2829 0.00981 0.00387 -0.0067 0.8822 0.7073
-2.500 -0.2581 0.00987 0.00390 -0.0059 0.8776 0.7289
-2.250 -0.2325 0.00996 0.00395 -0.0052 0.8737 0.7486
-2.000 -0.2072 0.01007 0.00402 -0.0043 0.8702 0.7694
-1.750 -0.1829 0.01021 0.00417 -0.0032 0.8657 0.7860
-1.500 -0.1580 0.01031 0.00426 -0.0023 0.8616 0.7995
-1.250 -0.1315 0.01039 0.00430 -0.0018 0.8581 0.8096
-1.000 -0.1047 0.01043 0.00433 -0.0014 0.8547 0.8173
-0.750 -0.0798 0.01046 0.00434 -0.0008 0.8502 0.8243
-0.500 -0.0534 0.01046 0.00433 -0.0005 0.8463 0.8295
-0.250 -0.0256 0.01047 0.00432 -0.0004 0.8429 0.8338
0.000 0.0000 0.01047 0.00432 0.0000 0.8386 0.8386
0.250 0.0257 0.01047 0.00432 0.0004 0.8338 0.8429
0.500 0.0535 0.01046 0.00433 0.0005 0.8295 0.8462
0.750 0.0799 0.01046 0.00434 0.0008 0.8243 0.8503
1.000 0.1048 0.01044 0.00433 0.0014 0.8173 0.8548
1.250 0.1315 0.01038 0.00430 0.0018 0.8095 0.8581
1.500 0.1581 0.01030 0.00425 0.0024 0.7992 0.8616
1.750 0.1830 0.01020 0.00416 0.0033 0.7855 0.8657
2.000 0.2073 0.01007 0.00402 0.0043 0.7693 0.8702
2.250 0.2324 0.00995 0.00394 0.0052 0.7477 0.8737
2.500 0.2582 0.00987 0.00390 0.0059 0.7288 0.8776
2.750 0.2829 0.00981 0.00387 0.0067 0.7065 0.8822
3.000 0.3079 0.00976 0.00381 0.0076 0.6724 0.8865
3.250 0.3315 0.00981 0.00366 0.0089 0.5997 0.8908
3.500 0.3473 0.01031 0.00363 0.0115 0.4771 0.8965
3.750 0.3634 0.01106 0.00388 0.0135 0.3577 0.9022
4.000 0.3819 0.01181 0.00421 0.0148 0.2548 0.9085
4.250 0.4028 0.01250 0.00455 0.0156 0.1755 0.9148
4.500 0.4287 0.01305 0.00494 0.0155 0.1286 0.9202
4.750 0.4542 0.01352 0.00531 0.0156 0.1007 0.9271
5.000 0.4840 0.01401 0.00577 0.0147 0.0820 0.9327
5.250 0.5132 0.01450 0.00624 0.0140 0.0677 0.9396
5.500 0.5442 0.01501 0.00681 0.0129 0.0576 0.9458
5.750 0.5752 0.01559 0.00744 0.0118 0.0486 0.9526
6.000 0.6062 0.01630 0.00814 0.0105 0.0410 0.9595
6.250 0.6392 0.01684 0.00879 0.0090 0.0350 0.9669
6.500 0.6704 0.01770 0.00966 0.0077 0.0298 0.9756
6.750 0.7028 0.01834 0.01044 0.0062 0.0255 0.9848
7.000 0.7328 0.01933 0.01147 0.0050 0.0227 0.9987
7.250 0.7468 0.02035 0.01256 0.0072 0.0215 1.0000
7.500 0.7640 0.02130 0.01364 0.0089 0.0200 1.0000
7.750 0.7817 0.02241 0.01487 0.0105 0.0189 1.0000
8.000 0.7998 0.02348 0.01606 0.0119 0.0178 1.0000
8.250 0.8179 0.02433 0.01700 0.0132 0.0166 1.0000
8.500 0.8337 0.02576 0.01853 0.0146 0.0153 1.0000
8.750 0.8509 0.02721 0.02022 0.0160 0.0148 1.0000
9.000 0.8663 0.02902 0.02232 0.0176 0.0143 1.0000
9.250 0.8791 0.03114 0.02476 0.0194 0.0138 1.0000
9.500 0.8886 0.03354 0.02751 0.0215 0.0132 1.0000
9.750 0.8943 0.03620 0.03053 0.0238 0.0130 1.0000
10.000 0.8954 0.03910 0.03378 0.0264 0.0128 1.0000
10.250 0.8898 0.04239 0.03742 0.0293 0.0125 1.0000
10.500 0.8780 0.04551 0.04083 0.0327 0.0124 1.0000
10.750 0.8584 0.04941 0.04502 0.0355 0.0124 1.0000
11.000 0.8304 0.05471 0.05063 0.0365 0.0126 1.0000
11.250 0.8069 0.06006 0.05619 0.0353 0.0126 1.0000
11.500 0.7737 0.06838 0.06473 0.0306 0.0126 1.0000
11.750 0.7125 0.09140 0.08789 0.0144 0.0136 1.0000
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