LWK 80-080 (lwk80080-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: LWK 80-080 (lwk80080-il) Reynolds number: 500,000 Max Cl/Cd: 47.17 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lwk80080-il-500000-n5.txt Download as CSV file: xf-lwk80080-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LWK 80-080
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.7608 0.07206 0.07000 -0.0134 1.0000 0.0043
-10.000 -0.7724 0.06516 0.06303 -0.0187 1.0000 0.0042
-9.750 -0.7988 0.05861 0.05634 -0.0212 1.0000 0.0040
-9.500 -0.8341 0.04900 0.04643 -0.0202 1.0000 0.0040
-9.250 -0.8668 0.03740 0.03419 -0.0171 1.0000 0.0041
-9.000 -0.8672 0.03280 0.02913 -0.0148 1.0000 0.0041
-8.750 -0.8681 0.02784 0.02358 -0.0119 1.0000 0.0043
-8.500 -0.8571 0.02527 0.02068 -0.0101 1.0000 0.0047
-8.250 -0.8433 0.02283 0.01787 -0.0083 1.0000 0.0048
-8.000 -0.8231 0.02197 0.01689 -0.0074 1.0000 0.0051
-7.750 -0.7989 0.02234 0.01732 -0.0072 1.0000 0.0057
-7.500 -0.7814 0.02042 0.01511 -0.0057 1.0000 0.0059
-7.250 -0.7624 0.01886 0.01327 -0.0043 1.0000 0.0062
-7.000 -0.7419 0.01768 0.01190 -0.0030 1.0000 0.0069
-6.750 -0.7204 0.01689 0.01097 -0.0020 1.0000 0.0074
-6.250 -0.6741 0.01476 0.00855 -0.0007 0.9855 0.0077
-6.000 -0.6431 0.01355 0.00721 -0.0019 0.9732 0.0090
-5.750 -0.6077 0.01289 0.00648 -0.0040 0.9642 0.0098
-5.500 -0.5713 0.01216 0.00561 -0.0062 0.9557 0.0106
-5.250 -0.5349 0.01156 0.00490 -0.0084 0.9465 0.0114
-5.000 -0.4984 0.01107 0.00431 -0.0105 0.9375 0.0128
-4.750 -0.4643 0.01056 0.00378 -0.0122 0.9280 0.0195
-4.500 -0.4328 0.01026 0.00342 -0.0132 0.9182 0.0241
-4.250 -0.4031 0.01000 0.00313 -0.0138 0.9091 0.0307
-4.000 -0.3754 0.00972 0.00285 -0.0140 0.9008 0.0459
-3.750 -0.3491 0.00949 0.00262 -0.0138 0.8933 0.0584
-3.500 -0.3234 0.00919 0.00241 -0.0136 0.8864 0.0848
-3.250 -0.2995 0.00885 0.00221 -0.0129 0.8796 0.1249
-3.000 -0.2757 0.00849 0.00199 -0.0123 0.8736 0.1778
-2.750 -0.2533 0.00807 0.00181 -0.0115 0.8679 0.2498
-2.500 -0.2339 0.00745 0.00161 -0.0101 0.8619 0.3680
-2.250 -0.2170 0.00674 0.00141 -0.0081 0.8567 0.5090
-2.000 -0.1999 0.00625 0.00135 -0.0058 0.8512 0.6251
-1.750 -0.1772 0.00610 0.00135 -0.0046 0.8465 0.6812
-1.500 -0.1526 0.00604 0.00133 -0.0038 0.8423 0.7141
-1.250 -0.1277 0.00601 0.00134 -0.0031 0.8375 0.7381
-1.000 -0.1029 0.00600 0.00138 -0.0023 0.8332 0.7633
-0.750 -0.0774 0.00600 0.00140 -0.0016 0.8292 0.7807
-0.500 -0.0517 0.00600 0.00142 -0.0011 0.8245 0.7927
-0.250 -0.0260 0.00601 0.00144 -0.0005 0.8196 0.8047
0.000 0.0000 0.00601 0.00145 0.0000 0.8134 0.8136
0.250 0.0260 0.00601 0.00143 0.0005 0.8045 0.8195
0.500 0.0517 0.00600 0.00142 0.0011 0.7928 0.8245
0.750 0.0774 0.00600 0.00140 0.0016 0.7804 0.8292
1.000 0.1028 0.00600 0.00137 0.0023 0.7623 0.8332
1.250 0.1278 0.00601 0.00135 0.0031 0.7390 0.8375
1.500 0.1526 0.00604 0.00134 0.0038 0.7143 0.8422
1.750 0.1770 0.00611 0.00134 0.0047 0.6793 0.8465
2.000 0.1999 0.00625 0.00135 0.0058 0.6254 0.8511
2.250 0.2183 0.00667 0.00140 0.0078 0.5243 0.8566
2.500 0.2324 0.00756 0.00162 0.0103 0.3455 0.8622
2.750 0.2527 0.00811 0.00181 0.0115 0.2406 0.8680
3.000 0.2753 0.00852 0.00202 0.0124 0.1721 0.8736
3.250 0.2995 0.00885 0.00220 0.0130 0.1244 0.8795
3.500 0.3232 0.00921 0.00241 0.0136 0.0829 0.8862
3.750 0.3489 0.00950 0.00263 0.0138 0.0566 0.8932
4.000 0.3750 0.00976 0.00284 0.0140 0.0387 0.9009
4.250 0.4031 0.01000 0.00313 0.0138 0.0296 0.9095
4.500 0.4327 0.01029 0.00344 0.0132 0.0224 0.9185
4.750 0.4642 0.01059 0.00378 0.0122 0.0165 0.9281
5.000 0.4984 0.01107 0.00432 0.0106 0.0122 0.9373
5.250 0.5345 0.01158 0.00492 0.0085 0.0111 0.9462
5.500 0.5709 0.01220 0.00565 0.0063 0.0099 0.9555
5.750 0.6076 0.01288 0.00646 0.0040 0.0096 0.9641
6.000 0.6426 0.01367 0.00733 0.0020 0.0084 0.9734
6.250 0.6732 0.01508 0.00891 0.0009 0.0077 0.9861
6.750 0.7206 0.01688 0.01096 0.0020 0.0072 1.0000
7.000 0.7411 0.01796 0.01221 0.0032 0.0069 1.0000
7.250 0.7614 0.01917 0.01361 0.0044 0.0064 1.0000
7.500 0.7802 0.02081 0.01555 0.0059 0.0061 1.0000
7.750 0.7990 0.02234 0.01732 0.0072 0.0059 1.0000
8.000 0.8170 0.02388 0.01910 0.0085 0.0056 1.0000
8.250 0.8407 0.02363 0.01880 0.0087 0.0050 1.0000
8.500 0.8579 0.02509 0.02046 0.0100 0.0047 1.0000
8.750 0.8718 0.02718 0.02283 0.0115 0.0045 1.0000
9.000 0.8763 0.03108 0.02722 0.0139 0.0044 1.0000
9.250 0.8660 0.03737 0.03415 0.0171 0.0042 1.0000
9.500 0.8397 0.04764 0.04503 0.0199 0.0041 1.0000
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Polar data table (+)
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