NACA M5 AIRFOIL (m5-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M5 AIRFOIL (m5-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.66 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m5-il-1000000-n5.txt Download as CSV file: xf-m5-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.8351 0.09630 0.09476 0.0239 1.0000 0.0062
-11.250 -1.1203 0.02968 0.02645 -0.0019 1.0000 0.0047
-11.000 -1.1094 0.02581 0.02223 -0.0007 1.0000 0.0049
-10.750 -1.0914 0.02368 0.01986 0.0000 1.0000 0.0051
-10.500 -1.0707 0.02210 0.01807 0.0007 1.0000 0.0053
-10.250 -1.0487 0.02079 0.01659 0.0012 1.0000 0.0055
-10.000 -1.0255 0.01971 0.01535 0.0017 1.0000 0.0057
-9.750 -1.0024 0.01850 0.01398 0.0021 1.0000 0.0061
-9.500 -0.9786 0.01742 0.01276 0.0025 1.0000 0.0065
-9.250 -0.9540 0.01651 0.01173 0.0028 1.0000 0.0070
-9.000 -0.9288 0.01574 0.01084 0.0031 1.0000 0.0075
-8.750 -0.9030 0.01508 0.01008 0.0033 1.0000 0.0080
-8.500 -0.8769 0.01445 0.00936 0.0035 1.0000 0.0086
-8.250 -0.8510 0.01376 0.00860 0.0037 1.0000 0.0098
-8.000 -0.8246 0.01319 0.00797 0.0038 1.0000 0.0112
-7.750 -0.7965 0.01276 0.00752 0.0036 0.9701 0.0135
-7.500 -0.7723 0.01255 0.00727 0.0045 0.9372 0.0159
-7.250 -0.7482 0.01240 0.00706 0.0054 0.9111 0.0177
-7.000 -0.7227 0.01240 0.00700 0.0060 0.8859 0.0195
-6.750 -0.6965 0.01234 0.00686 0.0064 0.8631 0.0210
-6.500 -0.6696 0.01228 0.00669 0.0066 0.8421 0.0222
-6.250 -0.6423 0.01225 0.00658 0.0068 0.8230 0.0230
-6.000 -0.6148 0.01221 0.00645 0.0068 0.8055 0.0234
-5.750 -0.5871 0.01214 0.00629 0.0069 0.7893 0.0236
-5.500 -0.5607 0.01157 0.00559 0.0071 0.7743 0.0248
-5.250 -0.5334 0.01131 0.00525 0.0072 0.7601 0.0258
-4.750 -0.4775 0.01113 0.00499 0.0071 0.7336 0.0278
-4.500 -0.4499 0.01086 0.00464 0.0072 0.7212 0.0282
-4.250 -0.4223 0.01057 0.00426 0.0073 0.7097 0.0285
-4.000 -0.3946 0.01031 0.00392 0.0073 0.6984 0.0288
-3.500 -0.3390 0.00984 0.00329 0.0074 0.6766 0.0295
-3.250 -0.3110 0.00964 0.00303 0.0074 0.6664 0.0300
-3.000 -0.2829 0.00949 0.00282 0.0073 0.6562 0.0306
-2.750 -0.2548 0.00932 0.00259 0.0073 0.6457 0.0310
-2.500 -0.2266 0.00917 0.00239 0.0072 0.6359 0.0314
-2.250 -0.1983 0.00906 0.00223 0.0072 0.6260 0.0319
-2.000 -0.1699 0.00896 0.00209 0.0071 0.6159 0.0322
-1.750 -0.1417 0.00878 0.00186 0.0070 0.6067 0.0345
-1.500 -0.1133 0.00867 0.00173 0.0069 0.5976 0.0366
-1.250 -0.0849 0.00858 0.00164 0.0068 0.5885 0.0386
-1.000 -0.0563 0.00851 0.00154 0.0067 0.5803 0.0405
-0.750 -0.0278 0.00845 0.00146 0.0065 0.5714 0.0423
-0.500 0.0008 0.00838 0.00138 0.0064 0.5631 0.0470
-0.250 0.0293 0.00832 0.00133 0.0062 0.5545 0.0527
0.000 0.0579 0.00826 0.00128 0.0061 0.5460 0.0600
0.500 0.1149 0.00811 0.00121 0.0057 0.5288 0.0947
0.750 0.1433 0.00800 0.00120 0.0055 0.5203 0.1310
1.000 0.1715 0.00784 0.00119 0.0054 0.5113 0.1920
1.250 0.1992 0.00753 0.00120 0.0052 0.5027 0.3094
1.500 0.2136 0.00562 0.00118 0.0077 0.4949 0.9053
1.750 0.2381 0.00562 0.00125 0.0088 0.4858 0.9494
2.000 0.2656 0.00567 0.00130 0.0091 0.4768 0.9726
2.250 0.2985 0.00578 0.00137 0.0081 0.4660 0.9848
2.500 0.3404 0.00594 0.00148 0.0049 0.4526 0.9896
2.750 0.3751 0.00609 0.00155 0.0033 0.4295 0.9916
3.000 0.4087 0.00628 0.00164 0.0019 0.4035 0.9937
3.250 0.4399 0.00651 0.00173 0.0010 0.3685 0.9948
3.500 0.4710 0.00667 0.00181 0.0001 0.3493 0.9953
3.750 0.5019 0.00686 0.00192 -0.0008 0.3243 0.9959
4.000 0.5323 0.00711 0.00204 -0.0016 0.2930 0.9965
4.250 0.5627 0.00734 0.00218 -0.0024 0.2659 0.9972
4.500 0.5921 0.00784 0.00241 -0.0032 0.2050 0.9978
4.750 0.6212 0.00843 0.00272 -0.0040 0.1417 0.9985
5.000 0.6504 0.00898 0.00304 -0.0047 0.0902 0.9991
5.250 0.6796 0.00948 0.00336 -0.0055 0.0529 0.9997
5.500 0.7067 0.00975 0.00360 -0.0056 0.0424 1.0000
5.750 0.7312 0.01002 0.00383 -0.0051 0.0348 1.0000
6.000 0.7557 0.01027 0.00407 -0.0046 0.0281 1.0000
6.250 0.7801 0.01055 0.00432 -0.0041 0.0217 1.0000
6.500 0.8046 0.01086 0.00461 -0.0036 0.0162 1.0000
6.750 0.8291 0.01115 0.00490 -0.0032 0.0138 1.0000
7.000 0.8536 0.01151 0.00526 -0.0027 0.0112 1.0000
7.250 0.8784 0.01180 0.00557 -0.0023 0.0104 1.0000
7.500 0.9032 0.01212 0.00592 -0.0020 0.0096 1.0000
7.750 0.9279 0.01250 0.00633 -0.0016 0.0087 1.0000
8.000 0.9523 0.01296 0.00683 -0.0013 0.0078 1.0000
8.250 0.9771 0.01337 0.00728 -0.0010 0.0074 1.0000
8.500 1.0020 0.01377 0.00771 -0.0008 0.0069 1.0000
8.750 1.0267 0.01419 0.00817 -0.0006 0.0064 1.0000
9.000 1.0513 0.01464 0.00866 -0.0004 0.0060 1.0000
9.250 1.0753 0.01517 0.00923 -0.0001 0.0057 1.0000
9.500 1.0981 0.01589 0.01001 0.0003 0.0053 1.0000
9.750 1.1214 0.01648 0.01067 0.0006 0.0051 1.0000
10.000 1.1444 0.01707 0.01132 0.0010 0.0049 1.0000
10.250 1.1669 0.01771 0.01203 0.0014 0.0047 1.0000
10.500 1.1888 0.01839 0.01279 0.0018 0.0046 1.0000
10.750 1.2101 0.01910 0.01357 0.0023 0.0044 1.0000
11.000 1.2308 0.01983 0.01440 0.0029 0.0042 1.0000
11.250 1.2511 0.02057 0.01520 0.0034 0.0041 1.0000
11.500 1.2708 0.02132 0.01601 0.0041 0.0039 1.0000
11.750 1.2891 0.02216 0.01692 0.0048 0.0037 1.0000
12.000 1.3043 0.02327 0.01811 0.0058 0.0036 1.0000
12.250 1.3152 0.02468 0.01965 0.0072 0.0034 1.0000
12.500 1.3284 0.02572 0.02079 0.0084 0.0034 1.0000
12.750 1.3361 0.02691 0.02209 0.0102 0.0033 1.0000
13.000 1.3408 0.02835 0.02365 0.0119 0.0033 1.0000
13.250 1.3453 0.03010 0.02553 0.0129 0.0032 1.0000
13.500 1.3494 0.03211 0.02767 0.0134 0.0032 1.0000
13.750 1.3523 0.03445 0.03013 0.0135 0.0031 1.0000
14.000 1.3542 0.03705 0.03287 0.0132 0.0031 1.0000
14.250 1.3545 0.04000 0.03594 0.0126 0.0030 1.0000
14.500 1.3528 0.04329 0.03937 0.0118 0.0030 1.0000
14.750 1.3494 0.04692 0.04314 0.0106 0.0030 1.0000
15.000 1.3433 0.05100 0.04735 0.0092 0.0029 1.0000
15.250 1.3362 0.05535 0.05184 0.0076 0.0029 1.0000
15.500 1.3259 0.06027 0.05689 0.0056 0.0029 1.0000
15.750 1.3139 0.06560 0.06236 0.0033 0.0029 1.0000
16.000 1.2992 0.07150 0.06840 0.0007 0.0028 1.0000
16.250 1.2828 0.07800 0.07503 -0.0024 0.0028 1.0000
16.500 1.2648 0.08511 0.08228 -0.0059 0.0028 1.0000
16.750 1.2444 0.09290 0.09022 -0.0098 0.0028 1.0000
17.000 1.2217 0.10144 0.09889 -0.0140 0.0028 1.0000
17.250 1.1964 0.11071 0.10830 -0.0187 0.0029 1.0000
17.500 1.1694 0.12075 0.11848 -0.0237 0.0029 1.0000
17.750 1.1388 0.13193 0.12980 -0.0293 0.0029 1.0000
18.000 1.1049 0.14455 0.14256 -0.0357 0.0030 1.0000
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