M6 (85%) (m685-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: M6 (85%) (m685-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.1 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m685-il-1000000-n5.txt Download as CSV file: xf-m685-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -1.1623 0.04407 0.04131 -0.0578 1.0000 0.0058
-15.250 -1.1860 0.03952 0.03655 -0.0575 1.0000 0.0058
-15.000 -1.2039 0.03614 0.03295 -0.0553 1.0000 0.0058
-14.750 -1.2047 0.03447 0.03118 -0.0530 1.0000 0.0057
-14.500 -1.2127 0.03229 0.02882 -0.0497 1.0000 0.0058
-14.250 -1.2169 0.03051 0.02688 -0.0461 1.0000 0.0058
-14.000 -1.2164 0.02919 0.02543 -0.0426 1.0000 0.0058
-13.750 -1.2154 0.02781 0.02390 -0.0389 1.0000 0.0058
-13.500 -1.2074 0.02663 0.02260 -0.0363 1.0000 0.0058
-13.250 -1.1983 0.02548 0.02132 -0.0338 1.0000 0.0059
-13.000 -1.1879 0.02438 0.02008 -0.0314 1.0000 0.0059
-12.750 -1.1757 0.02339 0.01895 -0.0291 1.0000 0.0059
-12.500 -1.1618 0.02252 0.01799 -0.0270 1.0000 0.0060
-12.250 -1.1469 0.02170 0.01708 -0.0251 1.0000 0.0060
-12.000 -1.1313 0.02093 0.01622 -0.0231 1.0000 0.0062
-11.750 -1.1146 0.02025 0.01547 -0.0213 1.0000 0.0062
-11.500 -1.0977 0.01958 0.01473 -0.0196 1.0000 0.0064
-11.250 -1.0803 0.01896 0.01403 -0.0178 1.0000 0.0064
-11.000 -1.0624 0.01839 0.01339 -0.0161 1.0000 0.0065
-10.750 -1.0441 0.01786 0.01282 -0.0144 1.0000 0.0067
-10.500 -1.0257 0.01735 0.01225 -0.0127 1.0000 0.0067
-10.250 -1.0061 0.01698 0.01188 -0.0112 1.0000 0.0069
-10.000 -0.9869 0.01657 0.01143 -0.0096 1.0000 0.0070
-9.750 -0.9644 0.01620 0.01104 -0.0087 0.9997 0.0071
-9.500 -0.9328 0.01591 0.01076 -0.0098 0.9978 0.0073
-9.250 -0.9028 0.01547 0.01029 -0.0105 0.9942 0.0074
-9.000 -0.8759 0.01475 0.00942 -0.0106 0.9897 0.0081
-8.500 -0.8177 0.01382 0.00833 -0.0115 0.9781 0.0088
-8.250 -0.7856 0.01340 0.00786 -0.0126 0.9715 0.0090
-8.000 -0.7485 0.01306 0.00748 -0.0147 0.9640 0.0094
-7.750 -0.7078 0.01269 0.00706 -0.0177 0.9536 0.0095
-7.500 -0.6647 0.01227 0.00658 -0.0213 0.9378 0.0096
-7.250 -0.6265 0.01193 0.00614 -0.0237 0.9106 0.0097
-7.000 -0.5999 0.01165 0.00572 -0.0235 0.8803 0.0100
-6.500 -0.5534 0.01123 0.00508 -0.0215 0.8297 0.0106
-6.250 -0.5302 0.01103 0.00478 -0.0205 0.8094 0.0107
-6.000 -0.5065 0.01088 0.00454 -0.0195 0.7905 0.0110
-5.750 -0.4825 0.01071 0.00428 -0.0187 0.7738 0.0112
-5.500 -0.4583 0.01053 0.00403 -0.0179 0.7585 0.0113
-5.250 -0.4338 0.01037 0.00380 -0.0171 0.7441 0.0116
-5.000 -0.4091 0.01021 0.00358 -0.0164 0.7309 0.0117
-4.750 -0.3843 0.01005 0.00336 -0.0158 0.7189 0.0118
-4.500 -0.3594 0.00991 0.00316 -0.0151 0.7071 0.0119
-4.250 -0.3343 0.00977 0.00297 -0.0144 0.6953 0.0119
-4.000 -0.3090 0.00963 0.00278 -0.0139 0.6850 0.0120
-3.750 -0.2838 0.00950 0.00261 -0.0132 0.6747 0.0122
-3.500 -0.2584 0.00937 0.00244 -0.0127 0.6646 0.0125
-3.250 -0.2329 0.00925 0.00229 -0.0121 0.6555 0.0126
-3.000 -0.2075 0.00914 0.00214 -0.0115 0.6458 0.0129
-2.750 -0.1817 0.00904 0.00201 -0.0110 0.6369 0.0129
-2.500 -0.1561 0.00896 0.00190 -0.0105 0.6280 0.0131
-2.250 -0.1303 0.00885 0.00178 -0.0100 0.6192 0.0138
-2.000 -0.1045 0.00878 0.00168 -0.0095 0.6107 0.0139
-1.750 -0.0787 0.00868 0.00159 -0.0090 0.6020 0.0157
-1.500 -0.0531 0.00858 0.00150 -0.0084 0.5947 0.0222
-1.250 -0.0270 0.00851 0.00143 -0.0080 0.5865 0.0252
-1.000 -0.0011 0.00846 0.00136 -0.0075 0.5789 0.0283
-0.750 0.0251 0.00840 0.00130 -0.0071 0.5706 0.0306
-0.500 0.0509 0.00834 0.00125 -0.0066 0.5631 0.0359
-0.250 0.0762 0.00821 0.00120 -0.0060 0.5552 0.0599
0.000 0.1016 0.00813 0.00115 -0.0055 0.5471 0.0807
0.250 0.1266 0.00799 0.00113 -0.0049 0.5392 0.1161
0.500 0.1507 0.00782 0.00110 -0.0041 0.5312 0.1709
0.750 0.1751 0.00767 0.00109 -0.0034 0.5224 0.2239
1.000 0.1990 0.00751 0.00108 -0.0026 0.5141 0.2837
1.250 0.2066 0.00645 0.00099 0.0014 0.5039 0.6042
1.500 0.2081 0.00559 0.00099 0.0074 0.4934 0.8552
1.750 0.2816 0.00566 0.00120 -0.0028 0.4703 0.9263
2.000 0.3225 0.00581 0.00132 -0.0057 0.4585 0.9382
2.250 0.3551 0.00602 0.00151 -0.0066 0.4486 0.9519
2.500 0.3953 0.00634 0.00177 -0.0091 0.4340 0.9579
2.750 0.4226 0.00649 0.00186 -0.0090 0.4178 0.9612
3.000 0.4456 0.00661 0.00193 -0.0079 0.4051 0.9649
3.250 0.4766 0.00676 0.00202 -0.0086 0.3884 0.9657
3.500 0.5067 0.00695 0.00211 -0.0092 0.3651 0.9667
3.750 0.5362 0.00717 0.00223 -0.0097 0.3394 0.9679
4.000 0.5633 0.00753 0.00239 -0.0098 0.2943 0.9695
4.250 0.5895 0.00785 0.00256 -0.0096 0.2595 0.9716
4.500 0.6081 0.00829 0.00279 -0.0079 0.2147 0.9758
4.750 0.6369 0.00868 0.00301 -0.0084 0.1775 0.9766
5.000 0.6647 0.00913 0.00327 -0.0088 0.1374 0.9775
5.250 0.6907 0.00976 0.00363 -0.0089 0.0836 0.9789
5.500 0.7188 0.01005 0.00386 -0.0092 0.0699 0.9803
5.750 0.7458 0.01035 0.00410 -0.0092 0.0571 0.9821
6.000 0.7697 0.01066 0.00436 -0.0086 0.0460 0.9844
6.250 0.7949 0.01102 0.00464 -0.0083 0.0340 0.9860
6.500 0.8238 0.01134 0.00492 -0.0088 0.0260 0.9867
6.750 0.8525 0.01167 0.00521 -0.0094 0.0203 0.9876
7.000 0.8811 0.01198 0.00551 -0.0098 0.0168 0.9886
7.250 0.9092 0.01227 0.00580 -0.0102 0.0151 0.9897
7.500 0.9364 0.01259 0.00612 -0.0104 0.0136 0.9910
7.750 0.9628 0.01291 0.00645 -0.0104 0.0130 0.9923
8.000 0.9880 0.01328 0.00685 -0.0102 0.0122 0.9936
8.250 1.0139 0.01362 0.00720 -0.0101 0.0120 0.9947
8.500 1.0421 0.01396 0.00758 -0.0106 0.0118 0.9955
8.750 1.0695 0.01433 0.00798 -0.0110 0.0116 0.9964
9.000 1.0963 0.01471 0.00840 -0.0113 0.0114 0.9974
9.250 1.1222 0.01515 0.00887 -0.0114 0.0112 0.9983
9.500 1.1480 0.01558 0.00933 -0.0115 0.0109 0.9992
9.750 1.1734 0.01607 0.00986 -0.0116 0.0109 0.9999
10.000 1.1901 0.01652 0.01036 -0.0098 0.0107 1.0000
10.250 1.2052 0.01699 0.01087 -0.0077 0.0107 1.0000
10.500 1.2192 0.01750 0.01143 -0.0054 0.0106 1.0000
10.750 1.2324 0.01803 0.01200 -0.0031 0.0104 1.0000
11.000 1.2446 0.01857 0.01259 -0.0005 0.0104 1.0000
11.250 1.2550 0.01917 0.01324 0.0022 0.0103 1.0000
11.500 1.2624 0.01976 0.01389 0.0055 0.0102 1.0000
11.750 1.2631 0.02035 0.01453 0.0101 0.0100 1.0000
12.000 1.2655 0.02098 0.01522 0.0140 0.0100 1.0000
12.250 1.2675 0.02181 0.01612 0.0177 0.0098 1.0000
12.500 1.2716 0.02268 0.01705 0.0206 0.0099 1.0000
12.750 1.2729 0.02385 0.01830 0.0235 0.0097 1.0000
13.000 1.2740 0.02520 0.01973 0.0260 0.0095 1.0000
13.250 1.2769 0.02660 0.02121 0.0280 0.0095 1.0000
13.500 1.2846 0.02775 0.02243 0.0293 0.0095 1.0000
13.750 1.2904 0.02915 0.02391 0.0305 0.0094 1.0000
14.000 1.2971 0.03057 0.02541 0.0315 0.0093 1.0000
14.250 1.2931 0.03305 0.02800 0.0326 0.0094 1.0000
14.500 1.3044 0.03422 0.02923 0.0331 0.0092 1.0000
14.750 1.3048 0.03649 0.03158 0.0336 0.0092 1.0000
15.000 1.3037 0.03900 0.03420 0.0339 0.0092 1.0000
15.250 1.3074 0.04110 0.03638 0.0341 0.0091 1.0000
15.500 1.3080 0.04359 0.03895 0.0341 0.0090 1.0000
15.750 1.3048 0.04658 0.04205 0.0339 0.0089 1.0000
16.000 1.3044 0.04933 0.04488 0.0336 0.0089 1.0000
16.250 1.2962 0.05307 0.04874 0.0330 0.0089 1.0000
16.500 1.2974 0.05583 0.05158 0.0324 0.0088 1.0000
16.750 1.2877 0.06003 0.05589 0.0314 0.0089 1.0000
17.000 1.2827 0.06380 0.05976 0.0303 0.0087 1.0000
17.250 1.2794 0.06745 0.06350 0.0291 0.0086 1.0000
17.500 1.2737 0.07152 0.06766 0.0277 0.0085 1.0000
17.750 1.2624 0.07649 0.07275 0.0259 0.0085 1.0000
18.000 1.2537 0.08122 0.07758 0.0240 0.0086 1.0000
18.250 1.2460 0.08593 0.08238 0.0221 0.0084 1.0000
18.500 1.2289 0.09214 0.08872 0.0195 0.0086 1.0000
18.750 1.2235 0.09671 0.09337 0.0175 0.0084 1.0000
19.000 1.2068 0.10312 0.09990 0.0147 0.0085 1.0000
19.250 1.1946 0.10896 0.10584 0.0120 0.0084 1.0000
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