M6 (85%) (m685-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: M6 (85%) (m685-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.44 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m685-il-1000000.txt Download as CSV file: xf-m685-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: M6 (85%)
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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.9523 0.04872 0.04659 -0.0521 1.0000 0.0091
-13.250 -0.9923 0.04148 0.03907 -0.0536 1.0000 0.0091
-13.000 -1.0155 0.03754 0.03489 -0.0511 1.0000 0.0091
-12.750 -1.0329 0.03460 0.03173 -0.0470 1.0000 0.0092
-12.500 -1.0429 0.03252 0.02946 -0.0425 1.0000 0.0092
-12.250 -1.0486 0.03053 0.02726 -0.0383 1.0000 0.0093
-12.000 -1.0430 0.02908 0.02564 -0.0354 1.0000 0.0094
-11.750 -1.0372 0.02759 0.02397 -0.0325 1.0000 0.0095
-11.500 -1.0246 0.02664 0.02288 -0.0303 1.0000 0.0096
-11.250 -1.0156 0.02533 0.02140 -0.0276 1.0000 0.0096
-11.000 -1.0173 0.02294 0.01874 -0.0234 1.0000 0.0099
-10.750 -1.0054 0.02187 0.01757 -0.0209 1.0000 0.0102
-10.500 -0.9922 0.02089 0.01647 -0.0185 1.0000 0.0103
-10.250 -0.9750 0.02034 0.01588 -0.0167 1.0000 0.0106
-10.000 -0.9601 0.01951 0.01494 -0.0145 1.0000 0.0108
-9.750 -0.9440 0.01881 0.01414 -0.0124 1.0000 0.0110
-9.500 -0.9275 0.01813 0.01335 -0.0103 1.0000 0.0113
-9.250 -0.9118 0.01739 0.01250 -0.0081 1.0000 0.0116
-9.000 -0.8943 0.01688 0.01189 -0.0061 1.0000 0.0118
-8.750 -0.8785 0.01623 0.01114 -0.0038 1.0000 0.0120
-8.500 -0.8648 0.01543 0.01025 -0.0012 1.0000 0.0124
-8.250 -0.8332 0.01480 0.00956 -0.0023 0.9984 0.0127
-8.000 -0.7985 0.01437 0.00910 -0.0040 0.9962 0.0132
-7.750 -0.7648 0.01388 0.00855 -0.0055 0.9935 0.0134
-7.500 -0.7324 0.01337 0.00799 -0.0066 0.9899 0.0137
-7.250 -0.6981 0.01292 0.00748 -0.0082 0.9866 0.0139
-7.000 -0.6657 0.01253 0.00704 -0.0092 0.9816 0.0142
-6.750 -0.6325 0.01214 0.00660 -0.0105 0.9762 0.0144
-6.500 -0.6001 0.01168 0.00610 -0.0115 0.9685 0.0147
-6.250 -0.5616 0.01119 0.00557 -0.0140 0.9625 0.0150
-6.000 -0.5224 0.01085 0.00522 -0.0166 0.9510 0.0154
-5.750 -0.4815 0.01055 0.00489 -0.0196 0.9353 0.0159
-5.500 -0.4467 0.01027 0.00453 -0.0211 0.9115 0.0162
-5.000 -0.3948 0.00997 0.00402 -0.0201 0.8597 0.0170
-4.500 -0.3475 0.00965 0.00349 -0.0181 0.8179 0.0173
-4.250 -0.3236 0.00949 0.00325 -0.0171 0.7995 0.0174
-4.000 -0.2993 0.00935 0.00303 -0.0163 0.7830 0.0175
-3.750 -0.2751 0.00919 0.00280 -0.0154 0.7677 0.0178
-3.500 -0.2507 0.00905 0.00261 -0.0146 0.7535 0.0184
-3.250 -0.2260 0.00893 0.00243 -0.0138 0.7401 0.0190
-3.000 -0.2009 0.00881 0.00228 -0.0131 0.7273 0.0201
-2.750 -0.1757 0.00870 0.00212 -0.0125 0.7155 0.0208
-2.500 -0.1505 0.00860 0.00199 -0.0118 0.7044 0.0224
-2.250 -0.1253 0.00851 0.00187 -0.0112 0.6933 0.0263
-2.000 -0.0999 0.00839 0.00174 -0.0106 0.6829 0.0302
-1.750 -0.0746 0.00830 0.00163 -0.0100 0.6731 0.0356
-1.500 -0.0499 0.00813 0.00153 -0.0092 0.6637 0.0548
-1.250 -0.0251 0.00798 0.00145 -0.0086 0.6547 0.0797
-0.750 0.0245 0.00769 0.00132 -0.0072 0.6369 0.1426
-0.500 0.0488 0.00756 0.00127 -0.0064 0.6284 0.1795
-0.250 0.0729 0.00734 0.00123 -0.0057 0.6202 0.2382
0.000 0.0936 0.00697 0.00118 -0.0043 0.6119 0.3480
0.250 0.0940 0.00567 0.00103 0.0014 0.6048 0.6944
0.500 0.1056 0.00513 0.00108 0.0053 0.5972 0.8664
0.750 0.1653 0.00513 0.00122 -0.0017 0.5873 0.9206
1.000 0.2162 0.00529 0.00134 -0.0067 0.5775 0.9360
1.500 0.2868 0.00580 0.00175 -0.0095 0.5520 0.9548
1.750 0.3270 0.00607 0.00198 -0.0120 0.5408 0.9593
2.000 0.3574 0.00629 0.00215 -0.0123 0.5314 0.9653
2.250 0.4134 0.00669 0.00250 -0.0182 0.5187 0.9686
2.500 0.4493 0.00685 0.00261 -0.0199 0.5051 0.9712
2.750 0.4740 0.00695 0.00268 -0.0192 0.4928 0.9747
3.000 0.5039 0.00703 0.00272 -0.0197 0.4804 0.9762
3.250 0.5363 0.00713 0.00275 -0.0208 0.4603 0.9771
3.500 0.5681 0.00725 0.00280 -0.0218 0.4407 0.9780
3.750 0.5993 0.00737 0.00286 -0.0226 0.4209 0.9792
4.000 0.6288 0.00758 0.00293 -0.0231 0.3880 0.9807
4.250 0.6573 0.00776 0.00303 -0.0234 0.3652 0.9827
4.500 0.6811 0.00803 0.00319 -0.0227 0.3358 0.9857
4.750 0.7117 0.00833 0.00330 -0.0236 0.2919 0.9865
5.000 0.7416 0.00869 0.00346 -0.0244 0.2468 0.9875
5.250 0.7700 0.00914 0.00368 -0.0250 0.1989 0.9888
5.500 0.7980 0.00953 0.00391 -0.0254 0.1626 0.9903
5.750 0.8239 0.01011 0.00422 -0.0255 0.1120 0.9922
6.000 0.8494 0.01063 0.00457 -0.0254 0.0788 0.9943
6.250 0.8788 0.01104 0.00486 -0.0262 0.0564 0.9954
6.500 0.9074 0.01152 0.00520 -0.0268 0.0343 0.9966
6.750 0.9358 0.01198 0.00558 -0.0273 0.0227 0.9980
7.000 0.9649 0.01235 0.00596 -0.0279 0.0194 0.9992
7.250 0.9926 0.01265 0.00627 -0.0282 0.0185 1.0000
7.500 1.0113 0.01300 0.00664 -0.0266 0.0174 1.0000
7.750 1.0296 0.01337 0.00704 -0.0249 0.0169 1.0000
8.000 1.0447 0.01399 0.00773 -0.0226 0.0160 1.0000
8.250 1.0625 0.01437 0.00815 -0.0208 0.0159 1.0000
8.500 1.0797 0.01479 0.00862 -0.0190 0.0158 1.0000
8.750 1.0963 0.01524 0.00911 -0.0171 0.0157 1.0000
9.000 1.1128 0.01568 0.00960 -0.0151 0.0155 1.0000
9.250 1.1273 0.01625 0.01023 -0.0128 0.0154 1.0000
9.500 1.1428 0.01672 0.01075 -0.0107 0.0151 1.0000
9.750 1.1555 0.01734 0.01143 -0.0082 0.0150 1.0000
10.000 1.1682 0.01793 0.01207 -0.0057 0.0149 1.0000
10.250 1.1793 0.01859 0.01279 -0.0030 0.0148 1.0000
10.500 1.1895 0.01925 0.01351 -0.0001 0.0146 1.0000
10.750 1.1990 0.01989 0.01421 0.0028 0.0144 1.0000
11.000 1.2029 0.02060 0.01498 0.0068 0.0143 1.0000
11.250 1.2022 0.02125 0.01569 0.0115 0.0142 1.0000
11.500 1.2035 0.02199 0.01650 0.0155 0.0141 1.0000
11.750 1.2070 0.02282 0.01738 0.0189 0.0139 1.0000
12.000 1.2107 0.02379 0.01841 0.0218 0.0138 1.0000
12.250 1.2145 0.02488 0.01957 0.0244 0.0136 1.0000
12.500 1.2172 0.02620 0.02098 0.0268 0.0137 1.0000
12.750 1.2228 0.02741 0.02224 0.0286 0.0134 1.0000
13.000 1.2277 0.02876 0.02364 0.0301 0.0132 1.0000
13.250 1.2290 0.03059 0.02556 0.0318 0.0132 1.0000
13.500 1.2327 0.03226 0.02729 0.0329 0.0130 1.0000
13.750 1.2325 0.03442 0.02953 0.0341 0.0129 1.0000
14.000 1.2308 0.03682 0.03203 0.0353 0.0127 1.0000
14.250 1.2334 0.03889 0.03420 0.0361 0.0128 1.0000
14.500 1.2242 0.04228 0.03775 0.0374 0.0125 1.0000
14.750 1.2273 0.04437 0.03991 0.0376 0.0126 1.0000
15.000 1.2260 0.04702 0.04268 0.0380 0.0126 1.0000
15.250 1.2230 0.04994 0.04573 0.0376 0.0123 1.0000
15.500 1.2193 0.05302 0.04892 0.0375 0.0124 1.0000
15.750 1.2143 0.05638 0.05240 0.0369 0.0123 1.0000
16.000 1.2088 0.05986 0.05600 0.0365 0.0124 1.0000
16.250 1.1999 0.06401 0.06028 0.0354 0.0123 1.0000
16.500 1.1966 0.06754 0.06391 0.0341 0.0123 1.0000
16.750 1.1849 0.07235 0.06886 0.0326 0.0123 1.0000
17.000 1.1758 0.07712 0.07375 0.0305 0.0122 1.0000
17.250 1.1646 0.08226 0.07902 0.0283 0.0122 1.0000
17.500 1.1520 0.08791 0.08480 0.0257 0.0122 1.0000
17.750 1.1349 0.09442 0.09145 0.0227 0.0123 1.0000
18.000 1.1176 0.10119 0.09835 0.0194 0.0123 1.0000
18.250 1.1024 0.10800 0.10528 0.0157 0.0123 1.0000
18.500 1.0616 0.11967 0.11716 0.0100 0.0124 1.0000
18.750 1.0599 0.12461 0.12217 0.0068 0.0123 1.0000
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Polar data table (+)
Polar graphs
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