LWK 80-080 (lwk80080-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: LWK 80-080 (lwk80080-il) Reynolds number: 100,000 Max Cl/Cd: 33.95 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lwk80080-il-100000-n5.txt Download as CSV file: xf-lwk80080-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6507 0.08724 0.08231 -0.0131 1.0000 0.0196
-9.500 -0.6601 0.07970 0.07481 -0.0192 1.0000 0.0196
-9.250 -0.6720 0.07380 0.06888 -0.0231 1.0000 0.0192
-9.000 -0.6855 0.06908 0.06410 -0.0248 1.0000 0.0190
-8.750 -0.6996 0.06476 0.05969 -0.0245 1.0000 0.0190
-8.500 -0.7092 0.06021 0.05498 -0.0240 1.0000 0.0190
-8.250 -0.7144 0.05589 0.05042 -0.0230 1.0000 0.0193
-8.000 -0.7165 0.05163 0.04590 -0.0215 1.0000 0.0191
-7.750 -0.7151 0.04745 0.04127 -0.0197 1.0000 0.0205
-7.500 -0.7100 0.04374 0.03713 -0.0177 1.0000 0.0209
-7.250 -0.7012 0.04055 0.03344 -0.0156 1.0000 0.0214
-7.000 -0.6935 0.03641 0.02881 -0.0133 1.0000 0.0220
-6.750 -0.6809 0.03300 0.02498 -0.0114 1.0000 0.0224
-6.500 -0.6646 0.03031 0.02193 -0.0097 1.0000 0.0229
-6.250 -0.6462 0.02799 0.01931 -0.0083 1.0000 0.0238
-6.000 -0.6262 0.02603 0.01709 -0.0069 1.0000 0.0250
-5.750 -0.6052 0.02425 0.01509 -0.0055 1.0000 0.0268
-5.500 -0.5840 0.02291 0.01346 -0.0042 1.0000 0.0303
-5.250 -0.5640 0.02149 0.01191 -0.0028 1.0000 0.0340
-5.000 -0.5456 0.02032 0.01074 -0.0012 1.0000 0.0381
-4.750 -0.5269 0.01936 0.00964 0.0006 1.0000 0.0449
-4.500 -0.5106 0.01843 0.00874 0.0025 1.0000 0.0538
-4.250 -0.4953 0.01754 0.00781 0.0047 1.0000 0.0621
-4.000 -0.4798 0.01684 0.00714 0.0068 1.0000 0.0789
-3.750 -0.4652 0.01612 0.00649 0.0091 1.0000 0.1024
-3.500 -0.4512 0.01536 0.00592 0.0113 1.0000 0.1475
-3.250 -0.4404 0.01431 0.00548 0.0139 1.0000 0.2658
-3.000 -0.4327 0.01281 0.00518 0.0172 0.9980 0.5076
-2.750 -0.4101 0.01246 0.00560 0.0193 0.9922 0.7179
-2.500 -0.3822 0.01258 0.00569 0.0200 0.9863 0.7801
-2.250 -0.3524 0.01273 0.00572 0.0203 0.9814 0.8231
-2.000 -0.3235 0.01288 0.00582 0.0210 0.9767 0.8605
-1.750 -0.2878 0.01314 0.00601 0.0206 0.9744 0.8962
-1.500 -0.2454 0.01332 0.00608 0.0182 0.9730 0.9166
-1.250 -0.2049 0.01338 0.00597 0.0155 0.9702 0.9275
-1.000 -0.1609 0.01341 0.00590 0.0119 0.9682 0.9331
-0.750 -0.1247 0.01340 0.00581 0.0098 0.9632 0.9404
-0.500 -0.0825 0.01341 0.00577 0.0064 0.9599 0.9444
-0.250 -0.0400 0.01341 0.00572 0.0030 0.9568 0.9483
0.000 0.0001 0.01340 0.00570 0.0000 0.9529 0.9530
0.250 0.0400 0.01340 0.00572 -0.0030 0.9483 0.9568
0.500 0.0826 0.01340 0.00577 -0.0064 0.9444 0.9599
0.750 0.1247 0.01340 0.00582 -0.0098 0.9404 0.9631
1.000 0.1608 0.01341 0.00590 -0.0119 0.9331 0.9681
1.250 0.2050 0.01338 0.00598 -0.0155 0.9274 0.9702
1.500 0.2459 0.01331 0.00607 -0.0183 0.9162 0.9729
1.750 0.2879 0.01313 0.00600 -0.0206 0.8953 0.9745
2.000 0.3237 0.01288 0.00582 -0.0210 0.8601 0.9767
2.250 0.3522 0.01271 0.00570 -0.0202 0.8211 0.9814
2.500 0.3824 0.01258 0.00571 -0.0200 0.7817 0.9863
2.750 0.4105 0.01247 0.00562 -0.0195 0.7226 0.9922
3.000 0.4335 0.01277 0.00521 -0.0173 0.5164 0.9981
3.250 0.4400 0.01434 0.00548 -0.0138 0.2608 1.0000
3.500 0.4510 0.01538 0.00591 -0.0113 0.1454 1.0000
3.750 0.4651 0.01611 0.00650 -0.0091 0.1022 1.0000
4.000 0.4798 0.01684 0.00715 -0.0068 0.0791 1.0000
4.250 0.4952 0.01756 0.00784 -0.0047 0.0618 1.0000
4.500 0.5107 0.01843 0.00875 -0.0025 0.0525 1.0000
4.750 0.5275 0.01929 0.00960 -0.0007 0.0427 1.0000
5.000 0.5455 0.02035 0.01075 0.0012 0.0373 1.0000
5.250 0.5634 0.02165 0.01204 0.0028 0.0331 1.0000
5.500 0.5842 0.02275 0.01334 0.0042 0.0280 1.0000
5.750 0.6052 0.02429 0.01507 0.0056 0.0263 1.0000
6.000 0.6258 0.02602 0.01707 0.0069 0.0243 1.0000
6.250 0.6459 0.02802 0.01932 0.0083 0.0234 1.0000
6.500 0.6641 0.03041 0.02202 0.0097 0.0226 1.0000
6.750 0.6795 0.03344 0.02542 0.0115 0.0221 1.0000
7.000 0.6920 0.03688 0.02931 0.0134 0.0218 1.0000
7.250 0.7006 0.04084 0.03374 0.0155 0.0216 1.0000
7.500 0.7084 0.04429 0.03760 0.0176 0.0214 1.0000
7.750 0.7139 0.04791 0.04158 0.0194 0.0214 1.0000
8.000 0.7168 0.05148 0.04552 0.0211 0.0212 1.0000
8.250 0.7157 0.05548 0.04992 0.0228 0.0204 1.0000
8.500 0.7087 0.06031 0.05506 0.0240 0.0194 1.0000
8.750 0.7014 0.06437 0.05926 0.0246 0.0197 1.0000
9.000 0.6878 0.06865 0.06365 0.0249 0.0196 1.0000
9.250 0.6740 0.07328 0.06834 0.0236 0.0199 1.0000
9.500 0.6620 0.07893 0.07403 0.0200 0.0201 1.0000
9.750 0.6539 0.08510 0.08017 0.0156 0.0208 1.0000
10.000 0.6472 0.09280 0.08782 0.0096 0.0202 1.0000
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Polar data table (+)
Polar graphs
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