LWK 79-100 (lwk79100-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: LWK 79-100 (lwk79100-il) Reynolds number: 200,000 Max Cl/Cd: 47.73 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lwk79100-il-200000.txt Download as CSV file: xf-lwk79100-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: LWK 79-100
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7779 0.09684 0.09322 0.0054 1.0000 0.0379
-11.750 -0.7991 0.08724 0.08365 -0.0001 1.0000 0.0369
-11.500 -0.8327 0.07593 0.07227 -0.0087 1.0000 0.0358
-11.250 -0.8653 0.06711 0.06330 -0.0157 1.0000 0.0351
-11.000 -0.8960 0.06030 0.05631 -0.0203 1.0000 0.0345
-10.750 -0.9247 0.05514 0.05093 -0.0217 1.0000 0.0339
-10.500 -0.9487 0.05080 0.04630 -0.0203 1.0000 0.0335
-10.250 -0.9625 0.04608 0.04119 -0.0191 1.0000 0.0333
-10.000 -0.9649 0.04211 0.03683 -0.0178 1.0000 0.0335
-9.750 -0.9598 0.03875 0.03310 -0.0165 1.0000 0.0341
-9.500 -0.9497 0.03590 0.02988 -0.0153 1.0000 0.0352
-9.250 -0.9358 0.03372 0.02732 -0.0142 1.0000 0.0369
-9.000 -0.9188 0.03230 0.02550 -0.0130 1.0000 0.0382
-8.750 -0.9038 0.02830 0.02124 -0.0121 1.0000 0.0401
-8.500 -0.8830 0.02671 0.01957 -0.0115 1.0000 0.0420
-8.250 -0.8612 0.02545 0.01817 -0.0107 1.0000 0.0449
-8.000 -0.8385 0.02447 0.01694 -0.0099 1.0000 0.0477
-7.750 -0.8174 0.02229 0.01468 -0.0091 1.0000 0.0508
-7.500 -0.7945 0.02130 0.01367 -0.0085 1.0000 0.0546
-7.250 -0.7706 0.02044 0.01267 -0.0078 1.0000 0.0585
-7.000 -0.7488 0.01893 0.01116 -0.0070 1.0000 0.0625
-6.750 -0.7254 0.01812 0.01035 -0.0063 1.0000 0.0680
-6.500 -0.7025 0.01713 0.00931 -0.0055 1.0000 0.0737
-6.250 -0.6797 0.01626 0.00846 -0.0047 1.0000 0.0813
-6.000 -0.6570 0.01537 0.00762 -0.0039 1.0000 0.0921
-5.750 -0.6340 0.01454 0.00685 -0.0032 1.0000 0.1091
-5.500 -0.6115 0.01364 0.00612 -0.0024 1.0000 0.1373
-5.250 -0.5888 0.01282 0.00553 -0.0018 1.0000 0.1783
-5.000 -0.5655 0.01212 0.00504 -0.0012 1.0000 0.2252
-4.750 -0.5425 0.01145 0.00464 -0.0006 1.0000 0.2772
-4.500 -0.5194 0.01088 0.00434 0.0001 1.0000 0.3378
-4.250 -0.4959 0.01043 0.00412 0.0009 1.0000 0.3956
-4.000 -0.4720 0.01012 0.00399 0.0017 1.0000 0.4470
-3.750 -0.4480 0.00991 0.00394 0.0026 1.0000 0.4905
-3.500 -0.4236 0.00980 0.00392 0.0034 1.0000 0.5244
-3.250 -0.3993 0.00974 0.00390 0.0043 1.0000 0.5524
-3.000 -0.3757 0.00969 0.00392 0.0052 1.0000 0.5753
-2.750 -0.3510 0.00969 0.00396 0.0055 0.9973 0.5963
-2.500 -0.3021 0.00970 0.00399 0.0012 0.9696 0.6180
-2.250 -0.2566 0.00971 0.00397 -0.0022 0.9375 0.6376
-2.000 -0.2158 0.00972 0.00392 -0.0046 0.9048 0.6550
-1.750 -0.1833 0.00975 0.00387 -0.0050 0.8757 0.6703
-1.500 -0.1558 0.00979 0.00384 -0.0044 0.8521 0.6839
-1.250 -0.1297 0.00983 0.00382 -0.0036 0.8334 0.6967
-1.000 -0.1039 0.00987 0.00381 -0.0028 0.8169 0.7096
-0.750 -0.0779 0.00990 0.00380 -0.0021 0.8024 0.7226
-0.500 -0.0520 0.00993 0.00381 -0.0014 0.7893 0.7361
-0.250 -0.0261 0.00994 0.00381 -0.0006 0.7762 0.7501
0.000 0.0000 0.00994 0.00382 0.0000 0.7634 0.7634
0.250 0.0261 0.00994 0.00381 0.0006 0.7501 0.7762
0.500 0.0520 0.00993 0.00381 0.0014 0.7361 0.7893
0.750 0.0779 0.00990 0.00380 0.0021 0.7226 0.8024
1.000 0.1039 0.00987 0.00381 0.0028 0.7097 0.8169
1.250 0.1298 0.00983 0.00382 0.0036 0.6967 0.8334
1.500 0.1558 0.00979 0.00384 0.0044 0.6839 0.8521
1.750 0.1833 0.00975 0.00387 0.0050 0.6703 0.8758
2.000 0.2158 0.00972 0.00392 0.0046 0.6550 0.9048
2.250 0.2566 0.00971 0.00397 0.0022 0.6376 0.9375
2.500 0.3021 0.00970 0.00399 -0.0012 0.6179 0.9697
2.750 0.3511 0.00969 0.00396 -0.0055 0.5964 0.9974
3.000 0.3756 0.00969 0.00392 -0.0051 0.5755 1.0000
3.250 0.3992 0.00974 0.00390 -0.0042 0.5525 1.0000
3.500 0.4236 0.00980 0.00392 -0.0034 0.5245 1.0000
3.750 0.4479 0.00991 0.00394 -0.0026 0.4906 1.0000
4.000 0.4720 0.01012 0.00399 -0.0017 0.4470 1.0000
4.250 0.4958 0.01043 0.00412 -0.0009 0.3955 1.0000
4.500 0.5193 0.01088 0.00434 -0.0001 0.3378 1.0000
4.750 0.5425 0.01145 0.00464 0.0006 0.2773 1.0000
5.000 0.5655 0.01212 0.00504 0.0012 0.2252 1.0000
5.250 0.5887 0.01282 0.00553 0.0018 0.1783 1.0000
5.500 0.6115 0.01364 0.00612 0.0024 0.1373 1.0000
5.750 0.6340 0.01454 0.00685 0.0032 0.1091 1.0000
6.000 0.6570 0.01537 0.00762 0.0039 0.0921 1.0000
6.250 0.6797 0.01626 0.00846 0.0047 0.0812 1.0000
6.500 0.7026 0.01713 0.00931 0.0054 0.0737 1.0000
6.750 0.7255 0.01812 0.01035 0.0063 0.0679 1.0000
7.000 0.7488 0.01894 0.01116 0.0069 0.0624 1.0000
7.250 0.7707 0.02045 0.01267 0.0078 0.0585 1.0000
7.500 0.7946 0.02128 0.01365 0.0085 0.0545 1.0000
7.750 0.8175 0.02229 0.01468 0.0091 0.0508 1.0000
8.000 0.8386 0.02447 0.01695 0.0099 0.0477 1.0000
8.250 0.8614 0.02543 0.01815 0.0107 0.0448 1.0000
8.500 0.8831 0.02672 0.01958 0.0114 0.0421 1.0000
8.750 0.9040 0.02832 0.02126 0.0121 0.0400 1.0000
9.000 0.9189 0.03239 0.02559 0.0129 0.0383 1.0000
9.250 0.9359 0.03380 0.02741 0.0141 0.0369 1.0000
9.500 0.9501 0.03586 0.02984 0.0153 0.0351 1.0000
9.750 0.9600 0.03878 0.03313 0.0165 0.0341 1.0000
10.000 0.9648 0.04221 0.03693 0.0177 0.0336 1.0000
10.250 0.9632 0.04605 0.04115 0.0190 0.0332 1.0000
10.500 0.9494 0.05078 0.04628 0.0202 0.0335 1.0000
10.750 0.9252 0.05516 0.05095 0.0216 0.0338 1.0000
11.000 0.8966 0.06032 0.05633 0.0201 0.0344 1.0000
11.250 0.8662 0.06709 0.06328 0.0156 0.0350 1.0000
11.500 0.8336 0.07597 0.07231 0.0086 0.0358 1.0000
11.750 0.7966 0.08815 0.08457 -0.0009 0.0369 1.0000
12.000 0.7763 0.09764 0.09403 -0.0062 0.0379 1.0000
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Polar data table (+)
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