LWK 80-120/K25 (lwk80120k25-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: LWK 80-120/K25 (lwk80120k25-il) Reynolds number: 200,000 Max Cl/Cd: 37.98 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lwk80120k25-il-200000-n5.txt Download as CSV file: xf-lwk80120k25-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.8504 0.08662 0.08264 -0.0282 1.0000 0.0160
-14.250 -0.8881 0.07476 0.07053 -0.0364 1.0000 0.0159
-14.000 -0.9151 0.06678 0.06231 -0.0411 1.0000 0.0158
-13.750 -0.9358 0.06078 0.05611 -0.0437 1.0000 0.0156
-13.500 -0.9547 0.05560 0.05068 -0.0450 1.0000 0.0157
-13.250 -0.9688 0.05142 0.04626 -0.0454 1.0000 0.0159
-13.000 -0.9790 0.04785 0.04245 -0.0450 1.0000 0.0160
-12.750 -0.9851 0.04488 0.03922 -0.0442 1.0000 0.0162
-12.500 -0.9910 0.04196 0.03601 -0.0429 1.0000 0.0167
-12.250 -0.9917 0.03955 0.03337 -0.0414 1.0000 0.0170
-12.000 -0.9901 0.03732 0.03087 -0.0398 1.0000 0.0173
-11.750 -0.9857 0.03534 0.02869 -0.0382 1.0000 0.0176
-11.500 -0.9799 0.03364 0.02690 -0.0366 1.0000 0.0181
-11.250 -0.9718 0.03239 0.02558 -0.0350 1.0000 0.0187
-11.000 -0.9622 0.03125 0.02436 -0.0334 1.0000 0.0193
-10.750 -0.9518 0.03022 0.02321 -0.0316 1.0000 0.0204
-10.500 -0.9401 0.02899 0.02180 -0.0299 1.0000 0.0213
-10.250 -0.9270 0.02782 0.02044 -0.0282 1.0000 0.0223
-10.000 -0.9148 0.02658 0.01911 -0.0263 1.0000 0.0231
-9.750 -0.9032 0.02555 0.01805 -0.0243 1.0000 0.0240
-9.500 -0.8900 0.02473 0.01719 -0.0224 1.0000 0.0251
-9.250 -0.8751 0.02398 0.01636 -0.0207 1.0000 0.0268
-9.000 -0.8601 0.02323 0.01551 -0.0190 1.0000 0.0284
-8.750 -0.8464 0.02236 0.01459 -0.0171 0.9992 0.0302
-8.500 -0.8150 0.02149 0.01367 -0.0189 0.9745 0.0329
-8.250 -0.7828 0.02067 0.01273 -0.0206 0.9621 0.0361
-8.000 -0.7516 0.01978 0.01181 -0.0223 0.9524 0.0399
-7.750 -0.7198 0.01910 0.01103 -0.0239 0.9438 0.0441
-7.500 -0.6908 0.01840 0.01025 -0.0248 0.9354 0.0488
-7.250 -0.6623 0.01780 0.00962 -0.0257 0.9283 0.0540
-7.000 -0.6370 0.01728 0.00902 -0.0257 0.9211 0.0594
-6.750 -0.6117 0.01676 0.00847 -0.0258 0.9147 0.0662
-6.500 -0.5875 0.01630 0.00796 -0.0255 0.9087 0.0730
-6.250 -0.5643 0.01588 0.00752 -0.0250 0.9026 0.0815
-6.000 -0.5409 0.01544 0.00708 -0.0246 0.8977 0.0919
-5.750 -0.5195 0.01505 0.00669 -0.0237 0.8925 0.1041
-5.500 -0.4983 0.01465 0.00634 -0.0227 0.8877 0.1208
-5.250 -0.4768 0.01425 0.00599 -0.0218 0.8835 0.1430
-5.000 -0.4574 0.01380 0.00567 -0.0206 0.8788 0.1750
-4.750 -0.4389 0.01331 0.00535 -0.0192 0.8740 0.2188
-4.500 -0.4211 0.01276 0.00504 -0.0176 0.8700 0.2768
-4.250 -0.4056 0.01212 0.00474 -0.0157 0.8664 0.3551
-4.000 -0.3928 0.01146 0.00449 -0.0131 0.8616 0.4461
-3.500 -0.3579 0.01077 0.00459 -0.0086 0.8542 0.6264
-3.250 -0.3334 0.01083 0.00470 -0.0076 0.8516 0.6672
-3.000 -0.3092 0.01091 0.00479 -0.0067 0.8479 0.6914
-2.750 -0.2845 0.01100 0.00484 -0.0059 0.8443 0.7106
-2.500 -0.2591 0.01110 0.00491 -0.0052 0.8412 0.7267
-2.250 -0.2335 0.01124 0.00501 -0.0045 0.8387 0.7424
-2.000 -0.2079 0.01142 0.00518 -0.0037 0.8359 0.7565
-1.750 -0.1827 0.01158 0.00534 -0.0029 0.8322 0.7679
-1.500 -0.1580 0.01168 0.00541 -0.0021 0.8289 0.7779
-1.250 -0.1310 0.01179 0.00551 -0.0017 0.8259 0.7853
-1.000 -0.1053 0.01182 0.00549 -0.0012 0.8232 0.7925
-0.750 -0.0779 0.01188 0.00556 -0.0010 0.8203 0.7969
-0.500 -0.0527 0.01191 0.00559 -0.0005 0.8164 0.8018
-0.250 -0.0279 0.01190 0.00555 0.0000 0.8127 0.8069
0.000 0.0000 0.01190 0.00556 0.0000 0.8096 0.8096
0.250 0.0280 0.01190 0.00555 0.0001 0.8069 0.8127
0.500 0.0527 0.01191 0.00559 0.0005 0.8019 0.8163
0.750 0.0780 0.01188 0.00556 0.0010 0.7969 0.8203
1.000 0.1054 0.01182 0.00549 0.0012 0.7925 0.8232
1.250 0.1310 0.01178 0.00551 0.0017 0.7853 0.8259
1.500 0.1580 0.01168 0.00541 0.0021 0.7779 0.8289
1.750 0.1828 0.01158 0.00534 0.0029 0.7681 0.8322
2.000 0.2079 0.01142 0.00518 0.0037 0.7566 0.8359
2.250 0.2335 0.01124 0.00501 0.0045 0.7424 0.8387
2.500 0.2592 0.01110 0.00491 0.0052 0.7268 0.8412
2.750 0.2844 0.01099 0.00483 0.0060 0.7094 0.8443
3.000 0.3092 0.01091 0.00478 0.0067 0.6911 0.8479
3.250 0.3334 0.01083 0.00470 0.0076 0.6673 0.8516
3.500 0.3580 0.01077 0.00459 0.0086 0.6269 0.8542
3.750 0.3790 0.01090 0.00442 0.0103 0.5480 0.8573
4.000 0.3926 0.01147 0.00449 0.0131 0.4446 0.8617
4.250 0.4052 0.01214 0.00474 0.0157 0.3530 0.8665
4.500 0.4210 0.01277 0.00505 0.0177 0.2766 0.8701
4.750 0.4390 0.01330 0.00535 0.0192 0.2191 0.8740
5.000 0.4574 0.01380 0.00567 0.0206 0.1750 0.8788
5.250 0.4769 0.01425 0.00599 0.0218 0.1432 0.8835
5.500 0.4983 0.01466 0.00634 0.0227 0.1208 0.8877
5.750 0.5196 0.01505 0.00669 0.0237 0.1041 0.8926
6.000 0.5410 0.01544 0.00708 0.0246 0.0912 0.8978
6.250 0.5644 0.01588 0.00752 0.0250 0.0814 0.9027
6.500 0.5876 0.01631 0.00796 0.0255 0.0728 0.9088
6.750 0.6118 0.01676 0.00848 0.0258 0.0662 0.9148
7.000 0.6371 0.01728 0.00902 0.0257 0.0593 0.9211
7.250 0.6625 0.01780 0.00962 0.0256 0.0542 0.9283
7.500 0.6910 0.01840 0.01025 0.0248 0.0485 0.9354
7.750 0.7200 0.01910 0.01103 0.0238 0.0440 0.9438
8.000 0.7517 0.01979 0.01182 0.0223 0.0399 0.9524
8.250 0.7828 0.02071 0.01277 0.0206 0.0362 0.9622
8.500 0.8152 0.02149 0.01368 0.0189 0.0329 0.9746
8.750 0.8466 0.02235 0.01456 0.0171 0.0299 0.9993
9.000 0.8605 0.02319 0.01547 0.0189 0.0283 1.0000
9.250 0.8757 0.02391 0.01629 0.0206 0.0264 1.0000
9.500 0.8903 0.02475 0.01721 0.0224 0.0252 1.0000
9.750 0.9036 0.02557 0.01807 0.0242 0.0240 1.0000
10.000 0.9149 0.02659 0.01911 0.0263 0.0230 1.0000
10.250 0.9276 0.02777 0.02043 0.0281 0.0220 1.0000
10.500 0.9405 0.02898 0.02180 0.0298 0.0212 1.0000
10.750 0.9520 0.03016 0.02314 0.0316 0.0201 1.0000
11.000 0.9628 0.03121 0.02431 0.0333 0.0193 1.0000
11.250 0.9722 0.03238 0.02556 0.0349 0.0186 1.0000
11.500 0.9803 0.03360 0.02684 0.0365 0.0180 1.0000
11.750 0.9868 0.03530 0.02866 0.0381 0.0177 1.0000
12.000 0.9902 0.03741 0.03098 0.0398 0.0172 1.0000
12.250 0.9920 0.03960 0.03343 0.0413 0.0168 1.0000
12.500 0.9909 0.04203 0.03613 0.0428 0.0164 1.0000
12.750 0.9853 0.04497 0.03932 0.0440 0.0161 1.0000
13.250 0.9675 0.05170 0.04656 0.0452 0.0157 1.0000
13.500 0.9530 0.05602 0.05112 0.0448 0.0157 1.0000
13.750 0.9362 0.06094 0.05627 0.0434 0.0157 1.0000
14.000 0.9163 0.06682 0.06238 0.0408 0.0156 1.0000
14.250 0.8866 0.07535 0.07115 0.0356 0.0155 1.0000
14.500 0.8465 0.08800 0.08405 0.0269 0.0160 1.0000
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