M6 (85%) (m685-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: M6 (85%) (m685-il) Reynolds number: 500,000 Max Cl/Cd: 70.74 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m685-il-500000-n5.txt Download as CSV file: xf-m685-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.8861 0.05210 0.04945 -0.0501 1.0000 0.0093
-12.500 -0.9387 0.04256 0.03951 -0.0506 1.0000 0.0092
-12.250 -0.9701 0.03798 0.03460 -0.0462 1.0000 0.0092
-12.000 -0.9902 0.03472 0.03103 -0.0410 1.0000 0.0094
-11.750 -0.9961 0.03221 0.02821 -0.0372 1.0000 0.0095
-11.500 -0.9951 0.03007 0.02578 -0.0339 1.0000 0.0096
-11.250 -0.9897 0.02849 0.02404 -0.0310 1.0000 0.0098
-11.000 -0.9802 0.02726 0.02268 -0.0285 1.0000 0.0099
-10.750 -0.9687 0.02616 0.02145 -0.0262 1.0000 0.0101
-10.500 -0.9564 0.02506 0.02022 -0.0239 1.0000 0.0102
-10.250 -0.9418 0.02419 0.01923 -0.0218 1.0000 0.0105
-10.000 -0.9278 0.02317 0.01807 -0.0197 1.0000 0.0107
-9.750 -0.9131 0.02222 0.01696 -0.0175 1.0000 0.0109
-9.500 -0.8978 0.02131 0.01589 -0.0154 1.0000 0.0112
-9.250 -0.8822 0.02043 0.01486 -0.0133 1.0000 0.0115
-9.000 -0.8659 0.01963 0.01392 -0.0113 1.0000 0.0117
-8.750 -0.8489 0.01895 0.01311 -0.0093 1.0000 0.0118
-8.500 -0.8324 0.01827 0.01233 -0.0073 1.0000 0.0121
-8.250 -0.8027 0.01753 0.01150 -0.0081 0.9970 0.0123
-8.000 -0.7718 0.01702 0.01094 -0.0091 0.9919 0.0128
-7.750 -0.7408 0.01645 0.01030 -0.0100 0.9862 0.0131
-7.500 -0.7113 0.01590 0.00967 -0.0106 0.9786 0.0135
-7.250 -0.6799 0.01536 0.00905 -0.0115 0.9712 0.0138
-7.000 -0.6462 0.01483 0.00843 -0.0130 0.9632 0.0142
-6.750 -0.6112 0.01429 0.00780 -0.0147 0.9530 0.0144
-6.500 -0.5735 0.01377 0.00723 -0.0170 0.9411 0.0148
-6.250 -0.5339 0.01328 0.00668 -0.0197 0.9256 0.0152
-6.000 -0.4967 0.01292 0.00625 -0.0219 0.9056 0.0157
-5.750 -0.4660 0.01259 0.00581 -0.0225 0.8823 0.0160
-5.500 -0.4398 0.01231 0.00540 -0.0221 0.8586 0.0162
-5.000 -0.3911 0.01185 0.00471 -0.0205 0.8183 0.0170
-4.750 -0.3672 0.01163 0.00440 -0.0196 0.8004 0.0173
-4.500 -0.3432 0.01144 0.00412 -0.0187 0.7840 0.0177
-4.250 -0.3190 0.01125 0.00387 -0.0179 0.7693 0.0184
-4.000 -0.2947 0.01109 0.00363 -0.0170 0.7551 0.0189
-3.750 -0.2701 0.01093 0.00341 -0.0163 0.7418 0.0200
-3.500 -0.2453 0.01079 0.00321 -0.0156 0.7291 0.0217
-3.250 -0.2206 0.01064 0.00302 -0.0149 0.7175 0.0238
-3.000 -0.1958 0.01051 0.00283 -0.0141 0.7064 0.0268
-2.750 -0.1709 0.01036 0.00265 -0.0134 0.6955 0.0289
-2.500 -0.1458 0.01025 0.00249 -0.0128 0.6851 0.0311
-2.250 -0.1209 0.01012 0.00233 -0.0121 0.6754 0.0348
-2.000 -0.0957 0.01000 0.00219 -0.0115 0.6653 0.0390
-1.750 -0.0708 0.00987 0.00206 -0.0108 0.6559 0.0474
-1.500 -0.0462 0.00972 0.00195 -0.0101 0.6463 0.0662
-1.250 -0.0209 0.00961 0.00186 -0.0095 0.6374 0.0801
-0.750 0.0279 0.00928 0.00171 -0.0080 0.6198 0.1452
-0.500 0.0513 0.00907 0.00165 -0.0071 0.6117 0.1977
-0.250 0.0751 0.00885 0.00160 -0.0063 0.6032 0.2552
0.000 0.0966 0.00852 0.00153 -0.0051 0.5954 0.3482
0.250 0.0906 0.00696 0.00139 0.0020 0.5883 0.7382
0.500 0.1522 0.00672 0.00164 -0.0051 0.5789 0.8973
0.750 0.2218 0.00710 0.00201 -0.0138 0.5679 0.9306
1.000 0.2584 0.00744 0.00231 -0.0153 0.5590 0.9442
1.250 0.2853 0.00761 0.00243 -0.0149 0.5500 0.9524
1.500 0.3238 0.00778 0.00255 -0.0171 0.5388 0.9553
1.750 0.3580 0.00795 0.00265 -0.0184 0.5245 0.9590
2.000 0.3833 0.00805 0.00269 -0.0178 0.5103 0.9629
2.250 0.4108 0.00814 0.00273 -0.0177 0.4967 0.9652
2.500 0.4422 0.00823 0.00277 -0.0185 0.4858 0.9665
2.750 0.4730 0.00831 0.00283 -0.0192 0.4750 0.9679
3.000 0.5025 0.00841 0.00289 -0.0196 0.4604 0.9697
3.250 0.5303 0.00854 0.00296 -0.0197 0.4434 0.9722
3.500 0.5537 0.00867 0.00306 -0.0188 0.4302 0.9756
3.750 0.5847 0.00880 0.00314 -0.0196 0.4135 0.9766
4.000 0.6148 0.00898 0.00324 -0.0202 0.3918 0.9779
4.250 0.6440 0.00915 0.00335 -0.0207 0.3701 0.9795
4.500 0.6706 0.00948 0.00350 -0.0207 0.3301 0.9814
4.750 0.6947 0.00995 0.00372 -0.0203 0.2752 0.9841
5.000 0.7193 0.01046 0.00399 -0.0200 0.2236 0.9861
5.250 0.7460 0.01104 0.00430 -0.0203 0.1706 0.9875
5.500 0.7722 0.01160 0.00463 -0.0205 0.1235 0.9891
5.750 0.7979 0.01220 0.00502 -0.0207 0.0835 0.9911
6.000 0.8250 0.01258 0.00534 -0.0208 0.0684 0.9929
6.250 0.8511 0.01299 0.00570 -0.0209 0.0530 0.9946
6.500 0.8788 0.01342 0.00604 -0.0213 0.0389 0.9958
6.750 0.9064 0.01382 0.00641 -0.0217 0.0303 0.9972
7.000 0.9339 0.01423 0.00681 -0.0220 0.0249 0.9986
7.250 0.9621 0.01461 0.00721 -0.0225 0.0220 0.9998
7.500 0.9813 0.01503 0.00764 -0.0211 0.0198 1.0000
7.750 0.9996 0.01541 0.00806 -0.0194 0.0187 1.0000
8.000 1.0167 0.01586 0.00854 -0.0176 0.0172 1.0000
8.250 1.0335 0.01632 0.00903 -0.0157 0.0165 1.0000
8.500 1.0491 0.01685 0.00960 -0.0136 0.0159 1.0000
8.750 1.0653 0.01731 0.01012 -0.0117 0.0156 1.0000
9.000 1.0810 0.01780 0.01066 -0.0097 0.0153 1.0000
9.250 1.0951 0.01836 0.01128 -0.0074 0.0149 1.0000
9.500 1.1089 0.01891 0.01189 -0.0051 0.0146 1.0000
9.750 1.1213 0.01952 0.01256 -0.0026 0.0144 1.0000
10.000 1.1328 0.02015 0.01324 0.0000 0.0142 1.0000
10.250 1.1430 0.02081 0.01396 0.0027 0.0141 1.0000
10.500 1.1513 0.02149 0.01471 0.0058 0.0139 1.0000
10.750 1.1546 0.02212 0.01540 0.0098 0.0136 1.0000
11.000 1.1565 0.02283 0.01617 0.0138 0.0136 1.0000
11.250 1.1594 0.02364 0.01705 0.0173 0.0135 1.0000
11.500 1.1630 0.02457 0.01805 0.0204 0.0133 1.0000
11.750 1.1666 0.02563 0.01918 0.0230 0.0132 1.0000
12.000 1.1707 0.02680 0.02043 0.0253 0.0131 1.0000
12.250 1.1734 0.02821 0.02191 0.0274 0.0129 1.0000
12.500 1.1766 0.02971 0.02350 0.0291 0.0129 1.0000
12.750 1.1789 0.03143 0.02529 0.0306 0.0128 1.0000
13.000 1.1807 0.03329 0.02724 0.0318 0.0127 1.0000
13.250 1.1816 0.03535 0.02938 0.0329 0.0126 1.0000
13.500 1.1833 0.03742 0.03154 0.0337 0.0125 1.0000
13.750 1.1840 0.03968 0.03390 0.0344 0.0125 1.0000
14.000 1.1858 0.04190 0.03623 0.0349 0.0124 1.0000
14.250 1.1873 0.04423 0.03867 0.0352 0.0123 1.0000
14.500 1.1882 0.04669 0.04123 0.0354 0.0123 1.0000
14.750 1.1876 0.04934 0.04400 0.0355 0.0123 1.0000
15.000 1.1867 0.05213 0.04690 0.0353 0.0123 1.0000
15.250 1.1852 0.05507 0.04997 0.0350 0.0122 1.0000
15.500 1.1829 0.05816 0.05317 0.0345 0.0122 1.0000
15.750 1.1789 0.06166 0.05680 0.0337 0.0120 1.0000
16.000 1.1775 0.06493 0.06019 0.0327 0.0119 1.0000
16.250 1.1682 0.06924 0.06464 0.0317 0.0120 1.0000
16.500 1.1630 0.07324 0.06876 0.0304 0.0120 1.0000
16.750 1.1563 0.07761 0.07326 0.0287 0.0119 1.0000
17.000 1.1482 0.08239 0.07818 0.0266 0.0117 1.0000
17.250 1.1384 0.08748 0.08340 0.0245 0.0117 1.0000
17.500 1.1244 0.09340 0.08947 0.0220 0.0118 1.0000
17.750 1.1156 0.09879 0.09498 0.0193 0.0116 1.0000
18.000 1.1026 0.10490 0.10123 0.0164 0.0116 1.0000
18.250 1.0900 0.11129 0.10775 0.0131 0.0114 1.0000
18.500 1.0711 0.11895 0.11557 0.0093 0.0116 1.0000
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Polar data table (+)
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