LWK 80-100 (lwk80100-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: LWK 80-100 (lwk80100-il) Reynolds number: 200,000 Max Cl/Cd: 44 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lwk80100-il-200000.txt Download as CSV file: xf-lwk80100-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6531 0.08752 0.08408 -0.0210 1.0000 0.0579
-10.000 -0.6732 0.07911 0.07568 -0.0286 1.0000 0.0576
-9.750 -0.6939 0.07334 0.06985 -0.0320 1.0000 0.0580
-9.500 -0.7153 0.06881 0.06525 -0.0329 1.0000 0.0581
-9.250 -0.7075 0.04239 0.03846 -0.0340 1.0000 0.0399
-9.000 -0.7211 0.03720 0.03315 -0.0317 1.0000 0.0382
-8.750 -0.8180 0.04242 0.03702 -0.0215 1.0000 0.0315
-8.500 -0.8068 0.04054 0.03482 -0.0192 1.0000 0.0308
-8.250 -0.7973 0.03744 0.03141 -0.0170 1.0000 0.0304
-8.000 -0.7908 0.03400 0.02756 -0.0142 1.0000 0.0307
-7.750 -0.7827 0.02967 0.02281 -0.0118 1.0000 0.0314
-7.500 -0.7678 0.02792 0.02101 -0.0104 1.0000 0.0338
-7.250 -0.7517 0.02628 0.01919 -0.0085 1.0000 0.0352
-7.000 -0.7363 0.02456 0.01726 -0.0063 1.0000 0.0368
-6.750 -0.7243 0.02317 0.01566 -0.0034 1.0000 0.0386
-6.500 -0.7146 0.02223 0.01451 -0.0001 1.0000 0.0403
-6.250 -0.7030 0.02052 0.01267 0.0026 1.0000 0.0432
-6.000 -0.6921 0.01994 0.01212 0.0052 1.0000 0.0474
-5.750 -0.6783 0.01937 0.01141 0.0076 1.0000 0.0521
-5.500 -0.6529 0.01803 0.01010 0.0075 0.9978 0.0585
-5.250 -0.6209 0.01717 0.00916 0.0062 0.9938 0.0677
-5.000 -0.5881 0.01643 0.00839 0.0047 0.9902 0.0788
-4.750 -0.5588 0.01558 0.00757 0.0039 0.9859 0.0930
-4.500 -0.5294 0.01466 0.00681 0.0028 0.9820 0.1161
-4.250 -0.5036 0.01375 0.00617 0.0025 0.9772 0.1609
-4.000 -0.4833 0.01224 0.00556 0.0027 0.9720 0.3254
-3.750 -0.4738 0.01079 0.00541 0.0057 0.9662 0.5863
-3.500 -0.4501 0.01083 0.00580 0.0073 0.9615 0.7035
-3.250 -0.4182 0.01109 0.00605 0.0070 0.9583 0.7498
-3.000 -0.3831 0.01135 0.00626 0.0060 0.9561 0.7759
-2.750 -0.3626 0.01160 0.00644 0.0079 0.9503 0.7954
-2.500 -0.3325 0.01185 0.00663 0.0079 0.9468 0.8138
-2.250 -0.2981 0.01204 0.00678 0.0070 0.9444 0.8283
-2.000 -0.2620 0.01228 0.00696 0.0059 0.9426 0.8431
-1.750 -0.2381 0.01254 0.00722 0.0074 0.9381 0.8585
-1.500 -0.2097 0.01279 0.00746 0.0081 0.9345 0.8733
-1.250 -0.1771 0.01295 0.00760 0.0076 0.9317 0.8857
-1.000 -0.1357 0.01310 0.00771 0.0053 0.9300 0.8934
-0.750 -0.0983 0.01311 0.00769 0.0034 0.9278 0.9003
-0.500 -0.0685 0.01321 0.00778 0.0029 0.9231 0.9059
-0.250 -0.0442 0.01318 0.00772 0.0034 0.9178 0.9133
0.000 0.0000 0.01318 0.00772 0.0000 0.9155 0.9155
0.250 0.0442 0.01318 0.00772 -0.0034 0.9133 0.9178
0.500 0.0686 0.01321 0.00778 -0.0029 0.9059 0.9230
0.750 0.0984 0.01312 0.00769 -0.0034 0.9004 0.9278
1.000 0.1357 0.01309 0.00771 -0.0053 0.8933 0.9300
1.250 0.1776 0.01293 0.00757 -0.0076 0.8853 0.9315
1.500 0.2100 0.01278 0.00746 -0.0081 0.8732 0.9345
1.750 0.2382 0.01255 0.00723 -0.0074 0.8587 0.9382
2.000 0.2624 0.01227 0.00695 -0.0059 0.8429 0.9426
2.250 0.2982 0.01204 0.00676 -0.0070 0.8280 0.9444
2.500 0.3328 0.01184 0.00661 -0.0079 0.8134 0.9468
2.750 0.3628 0.01161 0.00644 -0.0079 0.7954 0.9503
3.000 0.3832 0.01136 0.00627 -0.0060 0.7764 0.9561
3.250 0.4185 0.01109 0.00606 -0.0070 0.7501 0.9583
3.500 0.4504 0.01084 0.00582 -0.0073 0.7059 0.9615
3.750 0.4743 0.01078 0.00543 -0.0058 0.5908 0.9661
4.000 0.4837 0.01221 0.00555 -0.0027 0.3297 0.9720
4.250 0.5040 0.01373 0.00616 -0.0025 0.1641 0.9772
4.500 0.5298 0.01462 0.00677 -0.0029 0.1190 0.9820
4.750 0.5601 0.01543 0.00747 -0.0040 0.0949 0.9857
5.000 0.5886 0.01638 0.00834 -0.0048 0.0797 0.9902
5.250 0.6212 0.01714 0.00914 -0.0063 0.0676 0.9939
5.500 0.6533 0.01796 0.01002 -0.0076 0.0579 0.9978
5.750 0.6783 0.01923 0.01130 -0.0075 0.0511 1.0000
6.000 0.6914 0.01967 0.01183 -0.0051 0.0459 1.0000
6.250 0.7029 0.02131 0.01344 -0.0027 0.0411 1.0000
6.500 0.7138 0.02200 0.01431 0.0004 0.0392 1.0000
6.750 0.7237 0.02307 0.01558 0.0036 0.0374 1.0000
7.000 0.7360 0.02444 0.01712 0.0064 0.0358 1.0000
7.250 0.7516 0.02605 0.01892 0.0085 0.0345 1.0000
7.500 0.7676 0.02739 0.02035 0.0102 0.0326 1.0000
7.750 0.7807 0.03051 0.02368 0.0120 0.0310 1.0000
8.000 0.7889 0.03427 0.02788 0.0146 0.0304 1.0000
8.250 0.7969 0.03749 0.03149 0.0172 0.0304 1.0000
8.500 0.8019 0.04168 0.03603 0.0197 0.0307 1.0000
8.750 0.8147 0.04323 0.03784 0.0218 0.0312 1.0000
9.000 0.7434 0.06174 0.05796 0.0300 0.0597 1.0000
9.250 0.7316 0.06545 0.06181 0.0314 0.0588 1.0000
9.500 0.7148 0.06891 0.06535 0.0329 0.0578 1.0000
9.750 0.6938 0.07343 0.06994 0.0320 0.0578 1.0000
10.000 0.6724 0.07938 0.07594 0.0282 0.0578 1.0000
10.250 0.6543 0.08731 0.08387 0.0214 0.0573 1.0000
10.500 0.6501 0.09268 0.08921 0.0181 0.0563 1.0000
10.750 0.6481 0.09752 0.09403 0.0158 0.0556 1.0000
11.000 0.6476 0.10215 0.09864 0.0140 0.0550 1.0000
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Polar data table (+)
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