AS5046 (16%) (as5046-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AS5046 (16%) (as5046-il) Reynolds number: 100,000 Max Cl/Cd: 42.24 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-as5046-il-100000.txt Download as CSV file: xf-as5046-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AS5046 (16%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4014 0.11307 0.10867 -0.0361 1.0000 0.1718
-11.250 -0.4880 0.11685 0.11201 -0.0226 1.0000 0.1615
-11.000 -0.5291 0.11061 0.10594 -0.0295 1.0000 0.1726
-10.750 -0.4837 0.10959 0.10486 -0.0242 1.0000 0.1784
-10.500 -0.5043 0.10441 0.09978 -0.0277 1.0000 0.1898
-8.500 -0.7734 0.04857 0.04123 -0.0347 0.9897 0.0608
-8.250 -0.7442 0.04366 0.03620 -0.0365 0.9854 0.0577
-8.000 -0.7177 0.04034 0.03243 -0.0375 0.9791 0.0558
-7.750 -0.6857 0.03760 0.02930 -0.0391 0.9742 0.0557
-7.500 -0.6557 0.03529 0.02668 -0.0399 0.9686 0.0556
-7.250 -0.6213 0.03309 0.02419 -0.0410 0.9644 0.0550
-7.000 -0.5832 0.03115 0.02209 -0.0425 0.9616 0.0552
-6.750 -0.5510 0.02968 0.02056 -0.0430 0.9574 0.0563
-6.500 -0.5177 0.02836 0.01924 -0.0437 0.9534 0.0582
-6.250 -0.4826 0.02711 0.01798 -0.0450 0.9500 0.0621
-6.000 -0.4515 0.02571 0.01675 -0.0464 0.9467 0.0683
-5.750 -0.4331 0.02480 0.01581 -0.0455 0.9405 0.0735
-5.500 -0.4081 0.02355 0.01459 -0.0462 0.9362 0.0864
-5.250 -0.3917 0.02071 0.01286 -0.0470 0.9321 0.2230
-5.000 -0.3924 0.02210 0.01625 -0.0390 0.9247 0.6091
-4.750 -0.3628 0.02560 0.01964 -0.0343 0.9211 0.6536
-4.500 -0.3238 0.03023 0.02425 -0.0272 0.9196 0.6874
-4.250 -0.2720 0.03253 0.02641 -0.0253 0.9187 0.7068
-4.000 -0.2519 0.03238 0.02609 -0.0246 0.9138 0.7203
-3.750 -0.2184 0.03263 0.02621 -0.0243 0.9100 0.7286
-3.500 -0.1915 0.03242 0.02586 -0.0245 0.9058 0.7397
-3.250 -0.1660 0.03202 0.02531 -0.0252 0.9018 0.7523
-3.000 -0.1214 0.03197 0.02513 -0.0270 0.8994 0.7588
-2.750 -0.1273 0.03184 0.02497 -0.0228 0.8916 0.7698
-2.500 -0.0868 0.03168 0.02469 -0.0246 0.8883 0.7766
-2.250 -0.0646 0.03125 0.02416 -0.0250 0.8842 0.7859
-2.000 -0.0467 0.03131 0.02417 -0.0234 0.8784 0.7920
-1.750 -0.0484 0.03111 0.02392 -0.0203 0.8714 0.8011
-1.500 -0.0013 0.03081 0.02353 -0.0232 0.8684 0.8055
-1.250 0.0073 0.03085 0.02354 -0.0209 0.8620 0.8119
-1.000 0.0099 0.03072 0.02337 -0.0181 0.8546 0.8184
-0.750 0.0541 0.03044 0.02302 -0.0209 0.8509 0.8224
-0.500 0.0551 0.03060 0.02317 -0.0175 0.8428 0.8280
-0.250 0.0693 0.03041 0.02294 -0.0167 0.8358 0.8335
0.000 0.1167 0.03009 0.02256 -0.0196 0.8323 0.8367
0.250 0.1128 0.03041 0.02290 -0.0154 0.8218 0.8413
0.500 0.1502 0.03012 0.02257 -0.0173 0.8166 0.8453
0.750 0.1486 0.03037 0.02282 -0.0143 0.8059 0.8499
1.000 0.1886 0.03006 0.02249 -0.0160 0.8004 0.8526
1.250 0.1989 0.03031 0.02276 -0.0139 0.7900 0.8561
1.500 0.2363 0.03002 0.02246 -0.0155 0.7838 0.8589
1.750 0.2471 0.03028 0.02274 -0.0138 0.7728 0.8628
2.000 0.2857 0.02994 0.02238 -0.0156 0.7667 0.8655
2.250 0.2995 0.03016 0.02264 -0.0141 0.7549 0.8681
2.500 0.3409 0.02968 0.02216 -0.0155 0.7494 0.8706
2.750 0.3557 0.02988 0.02241 -0.0140 0.7365 0.8739
3.000 0.3809 0.02979 0.02236 -0.0138 0.7259 0.8766
3.250 0.4178 0.02922 0.02180 -0.0146 0.7176 0.8791
3.500 0.4404 0.02914 0.02176 -0.0142 0.7046 0.8824
3.750 0.4829 0.02817 0.02080 -0.0149 0.6989 0.8846
4.000 0.5028 0.02801 0.02072 -0.0137 0.6848 0.8873
4.250 0.5265 0.02775 0.02053 -0.0130 0.6718 0.8900
4.500 0.5674 0.02673 0.01952 -0.0138 0.6655 0.8928
4.750 0.5906 0.02637 0.01925 -0.0132 0.6512 0.8964
5.000 0.6166 0.02588 0.01884 -0.0127 0.6376 0.8995
5.250 0.6445 0.02518 0.01823 -0.0121 0.6246 0.9022
5.500 0.6755 0.02428 0.01741 -0.0119 0.6119 0.9052
5.750 0.7061 0.02333 0.01652 -0.0116 0.5979 0.9089
6.000 0.7341 0.02251 0.01579 -0.0111 0.5803 0.9130
6.250 0.7627 0.02167 0.01499 -0.0106 0.5603 0.9165
6.500 0.7928 0.02080 0.01409 -0.0101 0.5372 0.9200
6.750 0.8192 0.02032 0.01354 -0.0094 0.5073 0.9241
7.000 0.8428 0.02022 0.01328 -0.0085 0.4731 0.9289
7.250 0.8632 0.02045 0.01333 -0.0073 0.4375 0.9341
7.500 0.8829 0.02090 0.01360 -0.0061 0.4042 0.9400
7.750 0.9029 0.02150 0.01401 -0.0053 0.3747 0.9462
8.000 0.9234 0.02216 0.01456 -0.0047 0.3474 0.9526
8.250 0.9449 0.02291 0.01521 -0.0045 0.3238 0.9604
8.500 0.9682 0.02368 0.01593 -0.0047 0.3014 0.9694
8.750 0.9943 0.02453 0.01669 -0.0055 0.2811 0.9802
9.000 1.0206 0.02542 0.01751 -0.0066 0.2621 0.9969
9.250 1.0401 0.02631 0.01838 -0.0066 0.2458 1.0000
9.500 1.0620 0.02733 0.01938 -0.0071 0.2299 1.0000
9.750 1.0845 0.02845 0.02046 -0.0077 0.2146 1.0000
10.000 1.1083 0.02967 0.02161 -0.0085 0.1999 1.0000
10.250 1.1280 0.03085 0.02287 -0.0088 0.1864 1.0000
10.500 1.1473 0.03219 0.02429 -0.0091 0.1738 1.0000
10.750 1.1661 0.03362 0.02579 -0.0091 0.1624 1.0000
11.000 1.1876 0.03511 0.02721 -0.0095 0.1520 1.0000
11.250 1.2034 0.03645 0.02860 -0.0091 0.1428 1.0000
11.500 1.2180 0.03817 0.03045 -0.0086 0.1346 1.0000
11.750 1.2421 0.03966 0.03177 -0.0092 0.1265 1.0000
12.000 1.2473 0.04155 0.03399 -0.0076 0.1208 1.0000
12.250 1.2619 0.04305 0.03549 -0.0070 0.1149 1.0000
12.500 1.2754 0.04523 0.03778 -0.0065 0.1098 1.0000
12.750 1.2768 0.04731 0.04012 -0.0049 0.1056 1.0000
13.000 1.2948 0.04890 0.04163 -0.0047 0.1009 1.0000
13.250 1.2984 0.05169 0.04463 -0.0036 0.0978 1.0000
13.500 1.2900 0.05456 0.04784 -0.0020 0.0953 1.0000
13.750 1.2861 0.05732 0.05083 -0.0010 0.0927 1.0000
14.000 1.2898 0.05963 0.05322 -0.0005 0.0899 1.0000
14.250 1.3028 0.06258 0.05615 -0.0002 0.0869 1.0000
14.500 1.2802 0.06674 0.06066 0.0006 0.0862 1.0000
14.750 1.2553 0.07154 0.06580 0.0008 0.0856 1.0000
15.000 1.2270 0.07707 0.07164 0.0002 0.0853 1.0000
15.250 1.1949 0.08350 0.07835 -0.0012 0.0852 1.0000
15.500 1.1579 0.09113 0.08624 -0.0038 0.0855 1.0000
15.750 1.1165 0.10029 0.09563 -0.0079 0.0861 1.0000
16.000 1.0716 0.11139 0.10690 -0.0138 0.0869 1.0000
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Polar data table (+)
Polar graphs
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