NACA M17 AIRFOIL (m17-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M17 AIRFOIL (m17-il) Reynolds number: 500,000 Max Cl/Cd: 98.27 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m17-il-500000-n5.txt Download as CSV file: xf-m17-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M17 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4895 0.09685 0.09435 0.0099 0.7980 0.0090
-8.250 -0.4880 0.09281 0.09027 0.0075 0.7841 0.0092
-8.000 -0.4878 0.08856 0.08598 0.0042 0.7713 0.0093
-7.750 -0.4853 0.08380 0.08117 0.0001 0.7598 0.0096
-7.500 -0.4801 0.07789 0.07519 -0.0051 0.7494 0.0101
-7.250 -0.4736 0.07076 0.06797 -0.0109 0.7405 0.0108
-7.000 -0.4569 0.06837 0.06549 -0.0129 0.7296 0.0111
-6.750 -0.4396 0.06569 0.06273 -0.0150 0.7191 0.0116
-6.500 -0.4222 0.06199 0.05891 -0.0176 0.7098 0.0122
-6.250 -0.4047 0.05662 0.05338 -0.0208 0.7015 0.0131
-6.000 -0.3878 0.04746 0.04392 -0.0248 0.6950 0.0148
-5.500 -0.3420 0.04439 0.04063 -0.0261 0.6771 0.0160
-5.250 -0.3193 0.04074 0.03675 -0.0269 0.6698 0.0171
-5.000 -0.2998 0.02937 0.02469 -0.0272 0.6652 0.0204
-4.750 -0.2751 0.02851 0.02368 -0.0273 0.6574 0.0209
-4.500 -0.2502 0.02728 0.02230 -0.0273 0.6501 0.0215
-4.250 -0.2250 0.02603 0.02087 -0.0272 0.6429 0.0223
-4.000 -0.1998 0.02394 0.01854 -0.0269 0.6364 0.0236
-3.750 -0.1751 0.02074 0.01489 -0.0263 0.6304 0.0246
-3.500 -0.1492 0.01875 0.01254 -0.0259 0.6245 0.0256
-3.250 -0.1222 0.01770 0.01125 -0.0256 0.6179 0.0265
-2.750 -0.0677 0.01599 0.00912 -0.0253 0.6062 0.0273
-2.500 -0.0401 0.01542 0.00838 -0.0253 0.6002 0.0276
-2.250 -0.0124 0.01494 0.00776 -0.0252 0.5946 0.0277
-2.000 0.0150 0.01388 0.00651 -0.0251 0.5887 0.0280
-1.750 0.0425 0.01306 0.00553 -0.0250 0.5834 0.0283
-1.500 0.0700 0.01226 0.00463 -0.0249 0.5781 0.0291
-1.250 0.0976 0.01178 0.00408 -0.0249 0.5723 0.0294
-1.000 0.1252 0.01141 0.00362 -0.0248 0.5670 0.0295
-0.750 0.1528 0.01105 0.00323 -0.0247 0.5616 0.0297
-0.500 0.1804 0.01074 0.00288 -0.0246 0.5564 0.0300
-0.250 0.2079 0.01048 0.00259 -0.0245 0.5513 0.0306
0.000 0.2356 0.01026 0.00235 -0.0245 0.5457 0.0313
0.250 0.2634 0.01011 0.00217 -0.0245 0.5403 0.0323
0.500 0.2913 0.00998 0.00203 -0.0245 0.5355 0.0334
0.750 0.3192 0.00988 0.00191 -0.0246 0.5302 0.0345
1.000 0.3472 0.00981 0.00182 -0.0246 0.5249 0.0355
1.250 0.3753 0.00975 0.00175 -0.0247 0.5197 0.0365
1.500 0.4034 0.00971 0.00170 -0.0247 0.5145 0.0374
1.750 0.4315 0.00971 0.00167 -0.0248 0.5095 0.0387
2.000 0.4596 0.00967 0.00166 -0.0249 0.5043 0.0431
2.250 0.4875 0.00960 0.00169 -0.0250 0.4989 0.0721
2.500 0.5151 0.00952 0.00175 -0.0251 0.4941 0.1313
2.750 0.5398 0.00875 0.00185 -0.0250 0.4889 0.5046
3.250 0.6351 0.00786 0.00219 -0.0336 0.4725 0.9977
3.500 0.6703 0.00798 0.00227 -0.0354 0.4630 1.0000
3.750 0.6964 0.00807 0.00233 -0.0352 0.4529 1.0000
4.000 0.7226 0.00815 0.00241 -0.0349 0.4455 1.0000
4.250 0.7487 0.00825 0.00252 -0.0346 0.4394 1.0000
4.500 0.7748 0.00836 0.00262 -0.0344 0.4329 1.0000
4.750 0.8008 0.00846 0.00274 -0.0341 0.4256 1.0000
5.000 0.8268 0.00859 0.00288 -0.0339 0.4168 1.0000
5.250 0.8524 0.00875 0.00302 -0.0336 0.4018 1.0000
5.500 0.8779 0.00894 0.00318 -0.0333 0.3843 1.0000
5.750 0.9031 0.00919 0.00337 -0.0330 0.3624 1.0000
6.000 0.9266 0.00973 0.00368 -0.0326 0.3069 1.0000
6.250 0.9474 0.01075 0.00427 -0.0321 0.2236 1.0000
6.750 0.9841 0.01335 0.00595 -0.0306 0.0575 1.0000
7.000 1.0039 0.01426 0.00670 -0.0298 0.0241 1.0000
7.250 1.0263 0.01477 0.00722 -0.0291 0.0181 1.0000
7.500 1.0487 0.01526 0.00774 -0.0285 0.0156 1.0000
7.750 1.0700 0.01588 0.00841 -0.0277 0.0130 1.0000
8.000 1.0915 0.01644 0.00904 -0.0270 0.0119 1.0000
8.250 1.1128 0.01701 0.00970 -0.0263 0.0111 1.0000
8.500 1.1332 0.01765 0.01041 -0.0255 0.0103 1.0000
8.750 1.1529 0.01834 0.01116 -0.0246 0.0096 1.0000
9.000 1.1700 0.01925 0.01212 -0.0235 0.0088 1.0000
9.250 1.1864 0.02018 0.01313 -0.0224 0.0082 1.0000
9.500 1.2033 0.02099 0.01403 -0.0213 0.0078 1.0000
9.750 1.2180 0.02193 0.01508 -0.0200 0.0074 1.0000
10.000 1.2308 0.02296 0.01619 -0.0185 0.0071 1.0000
10.250 1.2405 0.02403 0.01735 -0.0167 0.0068 1.0000
10.500 1.2468 0.02527 0.01867 -0.0148 0.0066 1.0000
10.750 1.2533 0.02676 0.02023 -0.0135 0.0064 1.0000
11.000 1.2595 0.02846 0.02202 -0.0126 0.0062 1.0000
11.250 1.2639 0.03047 0.02411 -0.0119 0.0060 1.0000
11.500 1.2646 0.03294 0.02668 -0.0111 0.0058 1.0000
11.750 1.2672 0.03530 0.02914 -0.0105 0.0057 1.0000
12.000 1.2733 0.03733 0.03132 -0.0101 0.0056 1.0000
12.250 1.2785 0.03950 0.03359 -0.0098 0.0054 1.0000
12.500 1.2826 0.04178 0.03599 -0.0095 0.0052 1.0000
12.750 1.2862 0.04416 0.03849 -0.0092 0.0050 1.0000
13.000 1.2886 0.04668 0.04113 -0.0090 0.0049 1.0000
13.250 1.2898 0.04936 0.04392 -0.0088 0.0048 1.0000
13.500 1.2905 0.05215 0.04683 -0.0088 0.0046 1.0000
13.750 1.2904 0.05505 0.04984 -0.0088 0.0045 1.0000
14.000 1.2895 0.05810 0.05302 -0.0089 0.0045 1.0000
14.250 1.2879 0.06129 0.05632 -0.0092 0.0044 1.0000
14.500 1.2857 0.06467 0.05982 -0.0097 0.0043 1.0000
14.750 1.2830 0.06826 0.06353 -0.0104 0.0043 1.0000
15.000 1.2796 0.07206 0.06745 -0.0113 0.0042 1.0000
15.250 1.2752 0.07607 0.07158 -0.0123 0.0041 1.0000
15.500 1.2698 0.08037 0.07600 -0.0136 0.0041 1.0000
15.750 1.2636 0.08493 0.08072 -0.0150 0.0041 1.0000
16.000 1.2560 0.08978 0.08570 -0.0167 0.0040 1.0000
16.250 1.2471 0.09500 0.09105 -0.0186 0.0040 1.0000
16.500 1.2368 0.10062 0.09682 -0.0208 0.0039 1.0000
16.750 1.2251 0.10665 0.10299 -0.0232 0.0039 1.0000
17.000 1.2125 0.11302 0.10951 -0.0260 0.0039 1.0000
17.250 1.1989 0.11982 0.11646 -0.0292 0.0039 1.0000
17.500 1.1848 0.12699 0.12378 -0.0327 0.0039 1.0000
17.750 1.1702 0.13458 0.13153 -0.0366 0.0039 1.0000
18.000 1.1552 0.14254 0.13963 -0.0409 0.0039 1.0000
18.250 1.1398 0.15103 0.14827 -0.0456 0.0039 1.0000
18.500 1.1232 0.16033 0.15773 -0.0509 0.0039 1.0000
18.750 1.1014 0.17187 0.16942 -0.0574 0.0039 1.0000
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