LWK 80-120/K25 (lwk80120k25-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: LWK 80-120/K25 (lwk80120k25-il) Reynolds number: 1,000,000 Max Cl/Cd: 62.17 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lwk80120k25-il-1000000.txt Download as CSV file: xf-lwk80120k25-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.0412 0.11305 0.11087 -0.0017 1.0000 0.0081
-17.500 -1.0937 0.09776 0.09535 -0.0100 1.0000 0.0080
-17.250 -1.1138 0.08928 0.08677 -0.0150 1.0000 0.0082
-17.000 -1.1606 0.07602 0.07320 -0.0227 1.0000 0.0079
-16.750 -1.1756 0.06925 0.06630 -0.0267 1.0000 0.0079
-16.500 -1.1946 0.06234 0.05922 -0.0304 1.0000 0.0079
-16.250 -1.2119 0.05639 0.05309 -0.0330 1.0000 0.0079
-16.000 -1.2222 0.05189 0.04846 -0.0346 1.0000 0.0080
-15.750 -1.2192 0.04934 0.04587 -0.0354 1.0000 0.0082
-15.500 -1.2356 0.04471 0.04102 -0.0359 1.0000 0.0080
-15.250 -1.2238 0.04341 0.03974 -0.0361 1.0000 0.0084
-15.000 -1.2309 0.04016 0.03633 -0.0358 1.0000 0.0084
-14.750 -1.2308 0.03777 0.03382 -0.0353 1.0000 0.0085
-14.500 -1.2240 0.03612 0.03210 -0.0349 1.0000 0.0087
-14.250 -1.2255 0.03372 0.02955 -0.0338 1.0000 0.0088
-14.000 -1.2176 0.03225 0.02800 -0.0331 1.0000 0.0090
-13.750 -1.2110 0.03069 0.02634 -0.0321 1.0000 0.0090
-13.500 -1.2068 0.02892 0.02444 -0.0307 1.0000 0.0092
-13.250 -1.1949 0.02786 0.02330 -0.0298 1.0000 0.0095
-13.000 -1.1852 0.02663 0.02197 -0.0286 1.0000 0.0095
-12.750 -1.1710 0.02580 0.02107 -0.0277 1.0000 0.0097
-12.500 -1.1584 0.02482 0.01999 -0.0265 1.0000 0.0100
-12.250 -1.1499 0.02349 0.01856 -0.0248 1.0000 0.0101
-12.000 -1.1459 0.02186 0.01679 -0.0224 1.0000 0.0105
-11.750 -1.1357 0.02079 0.01565 -0.0205 1.0000 0.0108
-11.500 -1.1221 0.02001 0.01482 -0.0188 1.0000 0.0111
-11.250 -1.1075 0.01934 0.01409 -0.0171 1.0000 0.0115
-11.000 -1.0927 0.01869 0.01339 -0.0154 1.0000 0.0118
-10.750 -1.0640 0.01814 0.01281 -0.0164 0.9681 0.0125
-10.500 -1.0189 0.01727 0.01185 -0.0211 0.9575 0.0130
-10.250 -0.9745 0.01619 0.01064 -0.0259 0.9455 0.0139
-10.000 -0.9329 0.01528 0.00964 -0.0300 0.9313 0.0151
-9.750 -0.9006 0.01476 0.00902 -0.0317 0.9157 0.0160
-9.500 -0.8775 0.01439 0.00855 -0.0312 0.9030 0.0169
-9.250 -0.8577 0.01395 0.00803 -0.0301 0.8935 0.0183
-9.000 -0.8384 0.01352 0.00756 -0.0288 0.8856 0.0198
-8.750 -0.8176 0.01320 0.00719 -0.0278 0.8794 0.0213
-8.500 -0.7959 0.01296 0.00689 -0.0268 0.8736 0.0225
-8.250 -0.7770 0.01250 0.00639 -0.0253 0.8682 0.0253
-8.000 -0.7555 0.01221 0.00609 -0.0244 0.8637 0.0274
-7.750 -0.7326 0.01201 0.00585 -0.0236 0.8595 0.0293
-7.500 -0.7123 0.01162 0.00546 -0.0223 0.8554 0.0335
-7.250 -0.6891 0.01142 0.00522 -0.0216 0.8517 0.0363
-7.000 -0.6671 0.01112 0.00492 -0.0206 0.8482 0.0401
-6.750 -0.6447 0.01085 0.00467 -0.0198 0.8445 0.0444
-6.500 -0.6210 0.01065 0.00444 -0.0191 0.8411 0.0486
-6.250 -0.5983 0.01039 0.00419 -0.0182 0.8379 0.0548
-6.000 -0.5743 0.01019 0.00398 -0.0176 0.8351 0.0600
-5.750 -0.5512 0.00993 0.00376 -0.0168 0.8321 0.0679
-5.500 -0.5277 0.00969 0.00355 -0.0161 0.8290 0.0772
-5.250 -0.5040 0.00947 0.00336 -0.0154 0.8260 0.0886
-5.000 -0.4805 0.00923 0.00316 -0.0147 0.8232 0.1039
-4.750 -0.4571 0.00898 0.00299 -0.0139 0.8206 0.1242
-4.500 -0.4345 0.00866 0.00279 -0.0131 0.8179 0.1530
-4.250 -0.4129 0.00829 0.00260 -0.0120 0.8150 0.1944
-4.000 -0.3921 0.00787 0.00239 -0.0109 0.8122 0.2499
-3.750 -0.3722 0.00740 0.00219 -0.0095 0.8096 0.3184
-3.500 -0.3526 0.00695 0.00200 -0.0081 0.8068 0.3938
-3.250 -0.3352 0.00636 0.00179 -0.0062 0.8042 0.4872
-2.750 -0.2958 0.00562 0.00158 -0.0030 0.7987 0.6366
-2.500 -0.2706 0.00554 0.00156 -0.0024 0.7963 0.6665
-2.250 -0.2440 0.00551 0.00155 -0.0021 0.7939 0.6852
-2.000 -0.2170 0.00553 0.00156 -0.0018 0.7913 0.6992
-1.750 -0.1902 0.00551 0.00157 -0.0016 0.7891 0.7098
-1.500 -0.1630 0.00550 0.00157 -0.0014 0.7865 0.7191
-1.250 -0.1356 0.00551 0.00157 -0.0012 0.7837 0.7275
-1.000 -0.1083 0.00551 0.00158 -0.0011 0.7809 0.7354
-0.750 -0.0811 0.00555 0.00159 -0.0008 0.7775 0.7439
-0.500 -0.0541 0.00555 0.00162 -0.0006 0.7734 0.7509
-0.250 -0.0272 0.00555 0.00162 -0.0002 0.7680 0.7573
0.000 0.0000 0.00555 0.00160 0.0000 0.7629 0.7628
0.250 0.0272 0.00556 0.00163 0.0002 0.7576 0.7682
0.500 0.0542 0.00555 0.00162 0.0006 0.7511 0.7734
0.750 0.0811 0.00555 0.00159 0.0008 0.7437 0.7775
1.000 0.1083 0.00551 0.00158 0.0011 0.7354 0.7809
1.250 0.1356 0.00551 0.00157 0.0013 0.7268 0.7838
1.500 0.1630 0.00550 0.00157 0.0014 0.7188 0.7865
1.750 0.1903 0.00551 0.00157 0.0016 0.7106 0.7891
2.000 0.2170 0.00553 0.00156 0.0018 0.6995 0.7913
2.250 0.2440 0.00552 0.00155 0.0021 0.6849 0.7939
2.500 0.2705 0.00554 0.00156 0.0024 0.6661 0.7963
2.750 0.2957 0.00562 0.00158 0.0030 0.6353 0.7987
3.000 0.3182 0.00583 0.00163 0.0041 0.5831 0.8014
3.250 0.3355 0.00635 0.00179 0.0062 0.4903 0.8043
3.500 0.3527 0.00694 0.00200 0.0081 0.3946 0.8068
3.750 0.3720 0.00741 0.00219 0.0095 0.3164 0.8096
4.000 0.3921 0.00787 0.00239 0.0109 0.2496 0.8122
4.250 0.4129 0.00829 0.00260 0.0120 0.1943 0.8150
4.500 0.4344 0.00867 0.00280 0.0131 0.1513 0.8180
4.750 0.4571 0.00898 0.00299 0.0139 0.1241 0.8206
5.000 0.4806 0.00923 0.00316 0.0147 0.1044 0.8232
5.250 0.5040 0.00947 0.00335 0.0154 0.0886 0.8261
5.500 0.5275 0.00970 0.00355 0.0161 0.0765 0.8290
5.750 0.5512 0.00993 0.00376 0.0168 0.0678 0.8321
6.000 0.5743 0.01020 0.00399 0.0176 0.0597 0.8351
6.250 0.5983 0.01039 0.00419 0.0182 0.0550 0.8379
6.500 0.6210 0.01066 0.00444 0.0191 0.0482 0.8411
6.750 0.6447 0.01085 0.00466 0.0198 0.0442 0.8445
7.000 0.6671 0.01112 0.00492 0.0206 0.0397 0.8481
7.250 0.6892 0.01141 0.00522 0.0216 0.0362 0.8517
7.500 0.7123 0.01162 0.00546 0.0223 0.0333 0.8554
7.750 0.7324 0.01203 0.00588 0.0236 0.0292 0.8596
8.000 0.7556 0.01221 0.00610 0.0244 0.0276 0.8637
8.250 0.7771 0.01250 0.00638 0.0253 0.0250 0.8683
8.500 0.7963 0.01294 0.00687 0.0267 0.0225 0.8737
8.750 0.8180 0.01319 0.00717 0.0277 0.0212 0.8794
9.000 0.8388 0.01351 0.00754 0.0288 0.0197 0.8856
9.250 0.8555 0.01413 0.00821 0.0304 0.0175 0.8939
9.500 0.8769 0.01445 0.00862 0.0314 0.0171 0.9032
9.750 0.9005 0.01480 0.00906 0.0317 0.0161 0.9157
10.000 0.9331 0.01528 0.00962 0.0299 0.0148 0.9310
10.250 0.9728 0.01650 0.01098 0.0260 0.0133 0.9460
10.500 1.0195 0.01716 0.01171 0.0211 0.0129 0.9569
10.750 1.0649 0.01799 0.01263 0.0163 0.0122 0.9673
11.000 1.0936 0.01867 0.01337 0.0152 0.0117 1.0000
11.250 1.1093 0.01926 0.01399 0.0168 0.0113 1.0000
11.500 1.1238 0.01994 0.01472 0.0185 0.0109 1.0000
11.750 1.1368 0.02076 0.01561 0.0203 0.0107 1.0000
12.000 1.1438 0.02210 0.01704 0.0226 0.0103 1.0000
12.250 1.1470 0.02384 0.01893 0.0250 0.0100 1.0000
12.500 1.1611 0.02469 0.01986 0.0262 0.0098 1.0000
12.750 1.1723 0.02578 0.02105 0.0275 0.0097 1.0000
13.000 1.1792 0.02728 0.02268 0.0291 0.0096 1.0000
13.250 1.1931 0.02815 0.02361 0.0299 0.0094 1.0000
13.500 1.2000 0.02966 0.02524 0.0311 0.0094 1.0000
13.750 1.2089 0.03101 0.02668 0.0321 0.0092 1.0000
14.000 1.2155 0.03258 0.02836 0.0331 0.0090 1.0000
14.250 1.2260 0.03382 0.02966 0.0337 0.0086 1.0000
14.500 1.2290 0.03579 0.03174 0.0345 0.0085 1.0000
14.750 1.2301 0.03801 0.03408 0.0352 0.0085 1.0000
15.000 1.2275 0.04070 0.03690 0.0357 0.0084 1.0000
15.250 1.2372 0.04217 0.03840 0.0357 0.0082 1.0000
15.500 1.2273 0.04587 0.04227 0.0356 0.0082 1.0000
15.750 1.2274 0.04859 0.04505 0.0351 0.0080 1.0000
16.000 1.2138 0.05321 0.04985 0.0340 0.0080 1.0000
16.250 1.2041 0.05777 0.05454 0.0322 0.0080 1.0000
16.500 1.1951 0.06261 0.05948 0.0298 0.0078 1.0000
16.750 1.1733 0.07007 0.06715 0.0259 0.0079 1.0000
17.000 1.1463 0.07907 0.07636 0.0206 0.0081 1.0000
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