LWK 80-120/K25 (lwk80120k25-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: LWK 80-120/K25 (lwk80120k25-il) Reynolds number: 200,000 Max Cl/Cd: 41.43 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lwk80120k25-il-200000.txt Download as CSV file: xf-lwk80120k25-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: LWK 80-120/K25
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7177 0.08976 0.08602 -0.0329 1.0000 0.0367
-12.500 -0.7492 0.08010 0.07627 -0.0391 1.0000 0.0364
-12.250 -0.7708 0.07365 0.06974 -0.0424 1.0000 0.0358
-12.000 -0.7970 0.06759 0.06355 -0.0447 1.0000 0.0353
-11.750 -0.8215 0.06250 0.05830 -0.0455 1.0000 0.0349
-11.500 -0.8453 0.05798 0.05359 -0.0449 1.0000 0.0345
-11.250 -0.8684 0.05391 0.04930 -0.0430 1.0000 0.0342
-11.000 -0.8885 0.05028 0.04544 -0.0400 1.0000 0.0338
-10.750 -0.9076 0.04695 0.04183 -0.0357 1.0000 0.0339
-10.500 -0.9179 0.04356 0.03813 -0.0321 1.0000 0.0337
-10.250 -0.9220 0.04037 0.03458 -0.0288 1.0000 0.0341
-10.000 -0.9202 0.03763 0.03150 -0.0259 1.0000 0.0347
-9.750 -0.9142 0.03546 0.02899 -0.0232 1.0000 0.0357
-9.500 -0.9056 0.03379 0.02698 -0.0206 1.0000 0.0367
-9.250 -0.8953 0.03059 0.02352 -0.0187 1.0000 0.0385
-9.000 -0.8802 0.02903 0.02189 -0.0171 1.0000 0.0398
-8.750 -0.8681 0.02786 0.02061 -0.0148 1.0000 0.0414
-8.500 -0.8647 0.02703 0.01969 -0.0109 1.0000 0.0430
-8.250 -0.8651 0.02639 0.01891 -0.0063 1.0000 0.0445
-8.000 -0.8595 0.02584 0.01818 -0.0027 0.9998 0.0462
-7.750 -0.8281 0.02383 0.01613 -0.0043 0.9967 0.0504
-7.500 -0.7959 0.02287 0.01507 -0.0058 0.9925 0.0553
-7.250 -0.7638 0.02153 0.01364 -0.0073 0.9894 0.0608
-7.000 -0.7329 0.02070 0.01280 -0.0085 0.9854 0.0672
-6.750 -0.7019 0.01961 0.01169 -0.0098 0.9820 0.0745
-6.500 -0.6691 0.01897 0.01098 -0.0113 0.9788 0.0830
-6.250 -0.6418 0.01803 0.01011 -0.0120 0.9741 0.0927
-6.000 -0.6105 0.01718 0.00929 -0.0134 0.9708 0.1048
-5.750 -0.5812 0.01644 0.00861 -0.0144 0.9673 0.1203
-5.500 -0.5563 0.01578 0.00800 -0.0145 0.9626 0.1415
-5.250 -0.5289 0.01484 0.00735 -0.0154 0.9591 0.1821
-5.000 -0.5057 0.01359 0.00670 -0.0157 0.9555 0.2848
-4.750 -0.4997 0.01255 0.00634 -0.0124 0.9480 0.4169
-4.500 -0.4852 0.01171 0.00641 -0.0098 0.9438 0.5918
-4.250 -0.4582 0.01188 0.00676 -0.0091 0.9408 0.6715
-4.000 -0.4383 0.01221 0.00709 -0.0071 0.9353 0.7055
-3.750 -0.4111 0.01252 0.00732 -0.0066 0.9316 0.7311
-3.500 -0.3790 0.01291 0.00766 -0.0068 0.9293 0.7492
-3.250 -0.3455 0.01330 0.00800 -0.0074 0.9273 0.7648
-3.000 -0.3292 0.01364 0.00829 -0.0048 0.9215 0.7776
-2.750 -0.3022 0.01399 0.00860 -0.0042 0.9180 0.7899
-2.500 -0.2690 0.01437 0.00896 -0.0045 0.9156 0.7997
-2.250 -0.2366 0.01474 0.00930 -0.0046 0.9134 0.8115
-2.000 -0.2159 0.01509 0.00963 -0.0028 0.9092 0.8237
-1.750 -0.1901 0.01547 0.00999 -0.0017 0.9053 0.8339
-1.500 -0.1589 0.01571 0.01022 -0.0018 0.9023 0.8421
-1.250 -0.1325 0.01581 0.01028 -0.0014 0.8991 0.8514
-1.000 -0.0946 0.01595 0.01040 -0.0029 0.8973 0.8561
-0.750 -0.0801 0.01610 0.01055 -0.0005 0.8910 0.8634
-0.500 -0.0557 0.01608 0.01051 0.0001 0.8868 0.8694
-0.250 -0.0194 0.01612 0.01054 -0.0014 0.8842 0.8728
0.000 0.0000 0.01616 0.01058 0.0000 0.8788 0.8787
0.250 0.0193 0.01611 0.01054 0.0014 0.8727 0.8841
0.500 0.0556 0.01608 0.01051 -0.0001 0.8694 0.8868
0.750 0.0801 0.01610 0.01055 0.0005 0.8634 0.8911
1.000 0.0949 0.01595 0.01040 0.0029 0.8561 0.8974
1.250 0.1322 0.01581 0.01028 0.0015 0.8512 0.8992
1.500 0.1589 0.01571 0.01021 0.0018 0.8421 0.9023
1.750 0.1903 0.01548 0.01000 0.0016 0.8343 0.9052
2.000 0.2160 0.01509 0.00962 0.0028 0.8237 0.9092
2.250 0.2367 0.01474 0.00929 0.0047 0.8115 0.9134
2.500 0.2691 0.01437 0.00896 0.0045 0.7997 0.9156
2.750 0.3015 0.01398 0.00858 0.0043 0.7889 0.9181
3.000 0.3292 0.01364 0.00829 0.0048 0.7777 0.9215
3.250 0.3456 0.01330 0.00800 0.0074 0.7648 0.9273
3.500 0.3791 0.01291 0.00767 0.0068 0.7493 0.9293
3.750 0.4112 0.01251 0.00731 0.0066 0.7309 0.9317
4.000 0.4382 0.01220 0.00708 0.0071 0.7051 0.9353
4.250 0.4581 0.01187 0.00675 0.0091 0.6710 0.9408
4.500 0.4852 0.01171 0.00641 0.0098 0.5914 0.9438
4.750 0.4999 0.01254 0.00634 0.0123 0.4184 0.9480
5.000 0.5055 0.01359 0.00670 0.0158 0.2845 0.9556
5.250 0.5290 0.01483 0.00735 0.0153 0.1827 0.9591
5.500 0.5562 0.01579 0.00802 0.0145 0.1412 0.9627
5.750 0.5812 0.01644 0.00861 0.0144 0.1203 0.9674
6.000 0.6106 0.01717 0.00928 0.0134 0.1041 0.9709
6.250 0.6418 0.01803 0.01011 0.0120 0.0927 0.9741
6.500 0.6692 0.01898 0.01099 0.0114 0.0829 0.9788
6.750 0.7021 0.01961 0.01169 0.0098 0.0742 0.9821
7.000 0.7332 0.02068 0.01278 0.0085 0.0668 0.9855
7.250 0.7641 0.02153 0.01366 0.0072 0.0611 0.9894
7.500 0.7962 0.02295 0.01515 0.0058 0.0555 0.9925
7.750 0.8285 0.02387 0.01618 0.0043 0.0506 0.9967
8.000 0.8596 0.02566 0.01801 0.0027 0.0460 1.0000
8.250 0.8637 0.02623 0.01875 0.0065 0.0442 1.0000
8.500 0.8639 0.02697 0.01962 0.0110 0.0428 1.0000
8.750 0.8676 0.02779 0.02054 0.0149 0.0412 1.0000
9.000 0.8801 0.02896 0.02181 0.0171 0.0397 1.0000
9.250 0.8954 0.03079 0.02367 0.0185 0.0379 1.0000
9.500 0.9061 0.03404 0.02723 0.0204 0.0369 1.0000
9.750 0.9142 0.03545 0.02899 0.0232 0.0357 1.0000
10.000 0.9200 0.03760 0.03148 0.0259 0.0344 1.0000
10.250 0.9219 0.04027 0.03449 0.0289 0.0336 1.0000
10.500 0.9179 0.04355 0.03812 0.0321 0.0336 1.0000
10.750 0.9068 0.04699 0.04188 0.0358 0.0336 1.0000
11.000 0.8888 0.05029 0.04545 0.0399 0.0338 1.0000
11.250 0.8673 0.05406 0.04946 0.0430 0.0341 1.0000
11.500 0.8442 0.05812 0.05375 0.0448 0.0343 1.0000
11.750 0.8220 0.06252 0.05833 0.0453 0.0349 1.0000
12.000 0.7951 0.06795 0.06392 0.0444 0.0353 1.0000
12.250 0.7679 0.07417 0.07028 0.0418 0.0356 1.0000
12.500 0.7385 0.08207 0.07830 0.0370 0.0360 1.0000
12.750 0.7150 0.09067 0.08694 0.0319 0.0367 1.0000
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