LWK 80-080 (lwk80080-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: LWK 80-080 (lwk80080-il) Reynolds number: 500,000 Max Cl/Cd: 47.24 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lwk80080-il-500000.txt Download as CSV file: xf-lwk80080-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6927 0.07669 0.07458 -0.0146 1.0000 0.0144
-9.250 -0.7037 0.07128 0.06912 -0.0190 1.0000 0.0146
-9.000 -0.7197 0.06580 0.06354 -0.0213 1.0000 0.0146
-8.750 -0.7250 0.06293 0.06061 -0.0209 1.0000 0.0151
-8.500 -0.7263 0.05979 0.05739 -0.0208 1.0000 0.0158
-8.250 -0.7361 0.05257 0.04989 -0.0204 1.0000 0.0149
-7.500 -0.7323 0.03624 0.03243 -0.0137 1.0000 0.0136
-7.250 -0.7120 0.03546 0.03154 -0.0126 1.0000 0.0132
-7.000 -0.7128 0.02924 0.02475 -0.0091 1.0000 0.0135
-6.750 -0.7010 0.02576 0.02088 -0.0067 1.0000 0.0135
-6.500 -0.6812 0.02448 0.01944 -0.0053 1.0000 0.0132
-6.250 -0.6653 0.02174 0.01637 -0.0032 1.0000 0.0132
-6.000 -0.6526 0.01725 0.01138 -0.0004 1.0000 0.0140
-5.750 -0.6357 0.01565 0.00964 0.0016 1.0000 0.0147
-5.250 -0.5867 0.01396 0.00779 0.0021 0.9930 0.0170
-5.000 -0.5546 0.01277 0.00648 0.0010 0.9878 0.0175
-4.750 -0.5219 0.01186 0.00547 -0.0001 0.9823 0.0202
-4.500 -0.4907 0.01088 0.00437 -0.0011 0.9758 0.0247
-4.250 -0.4560 0.01036 0.00382 -0.0027 0.9711 0.0335
-4.000 -0.4203 0.00981 0.00330 -0.0048 0.9670 0.0514
-3.750 -0.3863 0.00933 0.00293 -0.0064 0.9612 0.0799
-3.500 -0.3524 0.00860 0.00258 -0.0084 0.9561 0.1648
-3.250 -0.3258 0.00761 0.00224 -0.0090 0.9480 0.3285
-3.000 -0.3047 0.00643 0.00192 -0.0083 0.9398 0.5514
-2.750 -0.2845 0.00602 0.00191 -0.0066 0.9311 0.6758
-2.500 -0.2576 0.00596 0.00193 -0.0063 0.9251 0.7249
-2.250 -0.2327 0.00597 0.00197 -0.0054 0.9183 0.7559
-2.000 -0.2048 0.00602 0.00197 -0.0053 0.9132 0.7755
-1.750 -0.1801 0.00605 0.00199 -0.0045 0.9067 0.7894
-1.500 -0.1536 0.00609 0.00199 -0.0040 0.9015 0.8025
-1.250 -0.1278 0.00613 0.00203 -0.0035 0.8963 0.8148
-1.000 -0.1033 0.00619 0.00210 -0.0025 0.8906 0.8298
-0.750 -0.0767 0.00624 0.00215 -0.0020 0.8862 0.8420
-0.500 -0.0514 0.00625 0.00219 -0.0013 0.8807 0.8509
-0.250 -0.0259 0.00628 0.00221 -0.0006 0.8750 0.8607
0.000 -0.0001 0.00629 0.00223 0.0000 0.8686 0.8688
0.250 0.0259 0.00628 0.00221 0.0006 0.8606 0.8750
0.500 0.0514 0.00625 0.00219 0.0013 0.8510 0.8807
0.750 0.0766 0.00624 0.00215 0.0020 0.8417 0.8862
1.000 0.1030 0.00618 0.00209 0.0026 0.8290 0.8907
1.250 0.1279 0.00614 0.00204 0.0034 0.8152 0.8963
1.500 0.1536 0.00609 0.00199 0.0041 0.8026 0.9014
1.750 0.1801 0.00605 0.00198 0.0045 0.7890 0.9067
2.000 0.2048 0.00602 0.00198 0.0053 0.7755 0.9131
2.250 0.2329 0.00597 0.00197 0.0054 0.7572 0.9182
2.500 0.2570 0.00596 0.00191 0.0065 0.7201 0.9252
2.750 0.2844 0.00602 0.00190 0.0067 0.6731 0.9312
3.000 0.3039 0.00647 0.00193 0.0085 0.5423 0.9401
3.250 0.3258 0.00762 0.00224 0.0090 0.3266 0.9480
3.500 0.3515 0.00871 0.00259 0.0085 0.1464 0.9562
3.750 0.3862 0.00934 0.00293 0.0065 0.0787 0.9611
4.000 0.4203 0.00979 0.00326 0.0047 0.0499 0.9670
4.250 0.4560 0.01037 0.00382 0.0027 0.0321 0.9711
4.500 0.4893 0.01123 0.00475 0.0014 0.0212 0.9765
4.750 0.5222 0.01189 0.00550 0.0002 0.0182 0.9824
5.000 0.5546 0.01281 0.00652 -0.0010 0.0170 0.9880
5.250 0.5867 0.01400 0.00783 -0.0021 0.0167 0.9931
5.750 0.6351 0.01579 0.00979 -0.0015 0.0143 1.0000
6.000 0.6514 0.01780 0.01198 0.0007 0.0138 1.0000
6.250 0.6676 0.02085 0.01537 0.0028 0.0134 1.0000
6.500 0.6816 0.02440 0.01934 0.0053 0.0133 1.0000
6.750 0.7009 0.02590 0.02104 0.0068 0.0135 1.0000
7.500 0.6956 0.04752 0.04431 0.0170 0.0214 1.0000
7.750 0.7243 0.04701 0.04406 0.0184 0.0173 1.0000
8.000 0.7267 0.05154 0.04881 0.0197 0.0172 1.0000
8.250 0.7328 0.05401 0.05140 0.0204 0.0155 1.0000
8.500 0.7282 0.05921 0.05679 0.0208 0.0154 1.0000
8.750 0.7221 0.06409 0.06180 0.0205 0.0155 1.0000
9.000 0.7001 0.07118 0.06902 0.0185 0.0167 1.0000
9.250 0.6849 0.07783 0.07573 0.0127 0.0168 1.0000
9.500 0.6862 0.08081 0.07871 0.0096 0.0148 1.0000
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Polar data table (+)
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