NACA M5 AIRFOIL (m5-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M5 AIRFOIL (m5-il) Reynolds number: 500,000 Max Cl/Cd: 70.12 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m5-il-500000-n5.txt Download as CSV file: xf-m5-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M5 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6945 0.10515 0.10310 0.0278 1.0000 0.0092
-9.750 -0.9679 0.02701 0.02296 -0.0024 1.0000 0.0086
-9.500 -0.9503 0.02428 0.01991 -0.0017 1.0000 0.0092
-9.250 -0.9294 0.02238 0.01776 -0.0011 1.0000 0.0100
-9.000 -0.9069 0.02088 0.01599 -0.0007 1.0000 0.0108
-8.750 -0.8834 0.01956 0.01442 -0.0003 1.0000 0.0116
-8.500 -0.8581 0.01877 0.01357 0.0000 1.0000 0.0131
-8.250 -0.8318 0.01831 0.01307 0.0000 1.0000 0.0146
-8.000 -0.8057 0.01766 0.01229 0.0002 1.0000 0.0162
-7.750 -0.7786 0.01739 0.01199 0.0002 1.0000 0.0176
-7.500 -0.7503 0.01762 0.01226 0.0000 1.0000 0.0191
-7.250 -0.7227 0.01751 0.01209 0.0000 1.0000 0.0209
-7.000 -0.6956 0.01712 0.01158 0.0000 1.0000 0.0224
-6.750 -0.6681 0.01680 0.01115 0.0000 1.0000 0.0233
-6.500 -0.6411 0.01613 0.01037 -0.0001 0.9868 0.0245
-6.250 -0.6118 0.01602 0.01023 -0.0005 0.9475 0.0257
-6.000 -0.5876 0.01602 0.01017 0.0004 0.9193 0.0267
-5.750 -0.5638 0.01590 0.00992 0.0014 0.8941 0.0279
-5.500 -0.5392 0.01567 0.00954 0.0021 0.8715 0.0292
-5.250 -0.5139 0.01534 0.00905 0.0028 0.8510 0.0303
-5.000 -0.4880 0.01500 0.00855 0.0033 0.8324 0.0311
-4.750 -0.4615 0.01468 0.00808 0.0036 0.8151 0.0317
-4.500 -0.4349 0.01422 0.00745 0.0039 0.7990 0.0319
-4.250 -0.4081 0.01377 0.00687 0.0042 0.7839 0.0321
-4.000 -0.3818 0.01305 0.00601 0.0045 0.7700 0.0326
-3.750 -0.3553 0.01241 0.00525 0.0048 0.7565 0.0332
-3.500 -0.3285 0.01195 0.00468 0.0050 0.7437 0.0340
-3.000 -0.2739 0.01133 0.00393 0.0052 0.7193 0.0358
-2.750 -0.2463 0.01106 0.00359 0.0053 0.7077 0.0366
-2.500 -0.2187 0.01083 0.00330 0.0054 0.6966 0.0376
-2.250 -0.1909 0.01064 0.00303 0.0054 0.6858 0.0390
-2.000 -0.1630 0.01046 0.00280 0.0055 0.6748 0.0403
-1.750 -0.1350 0.01031 0.00259 0.0055 0.6641 0.0416
-1.500 -0.1069 0.01019 0.00241 0.0054 0.6538 0.0426
-1.250 -0.0790 0.01000 0.00218 0.0054 0.6435 0.0461
-1.000 -0.0509 0.00987 0.00204 0.0054 0.6334 0.0497
-0.750 -0.0226 0.00978 0.00192 0.0053 0.6239 0.0539
-0.500 0.0056 0.00968 0.00181 0.0052 0.6145 0.0606
-0.250 0.0339 0.00958 0.00173 0.0051 0.6052 0.0707
0.000 0.0619 0.00944 0.00167 0.0050 0.5963 0.0980
0.250 0.0898 0.00925 0.00163 0.0049 0.5871 0.1469
0.500 0.1173 0.00897 0.00159 0.0048 0.5783 0.2323
0.750 0.1381 0.00745 0.00145 0.0055 0.5701 0.6699
1.000 0.1562 0.00675 0.00163 0.0086 0.5618 0.9382
1.250 0.1904 0.00686 0.00171 0.0075 0.5525 0.9677
1.500 0.2385 0.00708 0.00188 0.0032 0.5418 0.9865
1.750 0.2963 0.00733 0.00208 -0.0034 0.5302 0.9958
2.000 0.3366 0.00743 0.00214 -0.0062 0.5196 0.9990
2.250 0.3675 0.00750 0.00217 -0.0070 0.5096 1.0000
2.500 0.3943 0.00753 0.00217 -0.0068 0.4991 1.0000
2.750 0.4210 0.00758 0.00219 -0.0067 0.4882 1.0000
3.000 0.4476 0.00764 0.00222 -0.0065 0.4735 1.0000
3.250 0.4741 0.00776 0.00226 -0.0063 0.4522 1.0000
3.500 0.5004 0.00791 0.00230 -0.0061 0.4240 1.0000
3.750 0.5266 0.00806 0.00239 -0.0059 0.3983 1.0000
4.000 0.5526 0.00823 0.00248 -0.0057 0.3765 1.0000
4.250 0.5785 0.00845 0.00260 -0.0055 0.3473 1.0000
4.500 0.6042 0.00869 0.00276 -0.0052 0.3198 1.0000
4.750 0.6297 0.00898 0.00294 -0.0050 0.2872 1.0000
5.000 0.6545 0.00952 0.00321 -0.0049 0.2247 1.0000
5.250 0.6785 0.01029 0.00362 -0.0048 0.1493 1.0000
5.500 0.7025 0.01099 0.00406 -0.0045 0.0922 1.0000
5.750 0.7264 0.01160 0.00449 -0.0042 0.0555 1.0000
6.000 0.7510 0.01200 0.00485 -0.0038 0.0433 1.0000
6.250 0.7756 0.01238 0.00521 -0.0034 0.0347 1.0000
6.500 0.8002 0.01275 0.00559 -0.0030 0.0275 1.0000
6.750 0.8246 0.01315 0.00600 -0.0026 0.0215 1.0000
7.000 0.8487 0.01366 0.00649 -0.0022 0.0167 1.0000
7.250 0.8732 0.01407 0.00697 -0.0018 0.0152 1.0000
7.500 0.8973 0.01455 0.00749 -0.0014 0.0136 1.0000
7.750 0.9210 0.01514 0.00813 -0.0010 0.0119 1.0000
8.000 0.9442 0.01582 0.00888 -0.0006 0.0108 1.0000
8.250 0.9676 0.01640 0.00955 -0.0001 0.0102 1.0000
8.500 0.9906 0.01706 0.01028 0.0003 0.0095 1.0000
8.750 1.0131 0.01775 0.01104 0.0008 0.0089 1.0000
9.000 1.0352 0.01847 0.01183 0.0013 0.0084 1.0000
9.250 1.0555 0.01941 0.01283 0.0019 0.0079 1.0000
9.500 1.0748 0.02044 0.01399 0.0027 0.0074 1.0000
9.750 1.0954 0.02125 0.01490 0.0033 0.0071 1.0000
10.000 1.1145 0.02221 0.01597 0.0041 0.0068 1.0000
10.250 1.1324 0.02325 0.01712 0.0050 0.0065 1.0000
10.500 1.1495 0.02432 0.01831 0.0059 0.0062 1.0000
10.750 1.1655 0.02543 0.01952 0.0069 0.0060 1.0000
11.000 1.1803 0.02658 0.02077 0.0079 0.0058 1.0000
11.250 1.1933 0.02781 0.02211 0.0091 0.0056 1.0000
11.500 1.2030 0.02922 0.02365 0.0105 0.0055 1.0000
11.750 1.2056 0.03089 0.02545 0.0127 0.0054 1.0000
12.000 1.2043 0.03319 0.02790 0.0143 0.0053 1.0000
12.250 1.2042 0.03567 0.03056 0.0153 0.0052 1.0000
12.500 1.2058 0.03816 0.03323 0.0156 0.0051 1.0000
12.750 1.2058 0.04099 0.03625 0.0156 0.0050 1.0000
13.000 1.2041 0.04418 0.03963 0.0151 0.0050 1.0000
13.250 1.2003 0.04778 0.04342 0.0143 0.0049 1.0000
13.500 1.1946 0.05177 0.04760 0.0131 0.0048 1.0000
13.750 1.1865 0.05627 0.05230 0.0114 0.0048 1.0000
14.000 1.1764 0.06123 0.05744 0.0093 0.0047 1.0000
14.250 1.1641 0.06674 0.06312 0.0067 0.0047 1.0000
14.500 1.1491 0.07291 0.06947 0.0037 0.0047 1.0000
14.750 1.1321 0.07972 0.07646 0.0002 0.0046 1.0000
15.000 1.1131 0.08731 0.08421 -0.0039 0.0047 1.0000
15.250 1.0929 0.09570 0.09276 -0.0086 0.0047 1.0000
15.500 1.0698 0.10514 0.10236 -0.0138 0.0047 1.0000
15.750 1.0446 0.11560 0.11296 -0.0194 0.0048 1.0000
16.000 1.0159 0.12751 0.12501 -0.0257 0.0049 1.0000
16.250 0.9795 0.14237 0.13999 -0.0332 0.0050 1.0000
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