NACA M18 (nacam18-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M18 (nacam18-il) Reynolds number: 1,000,000 Max Cl/Cd: 114 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacam18-il-1000000-n5.txt Download as CSV file: xf-nacam18-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M18
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5098 0.10352 0.10114 -0.0047 0.7580 0.0162
-10.250 -0.5051 0.10046 0.09804 -0.0063 0.7457 0.0163
-9.750 -0.7955 0.02931 0.02551 -0.0380 0.7533 0.0197
-9.500 -0.7820 0.02704 0.02298 -0.0367 0.7421 0.0199
-9.250 -0.7631 0.02568 0.02142 -0.0357 0.7305 0.0201
-9.000 -0.7418 0.02471 0.02030 -0.0348 0.7184 0.0202
-8.750 -0.7190 0.02395 0.01942 -0.0342 0.7067 0.0203
-8.500 -0.6958 0.02325 0.01859 -0.0335 0.6961 0.0205
-8.000 -0.6506 0.02137 0.01638 -0.0320 0.6759 0.0208
-7.750 -0.6273 0.02047 0.01530 -0.0313 0.6668 0.0209
-7.500 -0.6037 0.01957 0.01424 -0.0307 0.6583 0.0211
-7.250 -0.5795 0.01874 0.01325 -0.0301 0.6507 0.0212
-7.000 -0.5549 0.01795 0.01230 -0.0295 0.6435 0.0214
-6.750 -0.5298 0.01722 0.01142 -0.0290 0.6369 0.0216
-6.500 -0.5043 0.01652 0.01058 -0.0285 0.6313 0.0217
-6.250 -0.4784 0.01588 0.00982 -0.0281 0.6253 0.0219
-5.750 -0.4257 0.01475 0.00846 -0.0274 0.6151 0.0223
-5.500 -0.3990 0.01424 0.00786 -0.0271 0.6098 0.0225
-5.250 -0.3721 0.01379 0.00731 -0.0268 0.6047 0.0227
-5.000 -0.3448 0.01340 0.00685 -0.0266 0.6005 0.0229
-4.750 -0.3173 0.01308 0.00646 -0.0264 0.5959 0.0232
-4.500 -0.2898 0.01274 0.00606 -0.0262 0.5908 0.0233
-4.250 -0.2623 0.01243 0.00568 -0.0261 0.5863 0.0235
-4.000 -0.2346 0.01213 0.00533 -0.0259 0.5822 0.0236
-3.750 -0.2068 0.01186 0.00501 -0.0258 0.5775 0.0237
-3.500 -0.1797 0.01144 0.00452 -0.0256 0.5726 0.0239
-3.250 -0.1525 0.01104 0.00408 -0.0254 0.5684 0.0243
-3.000 -0.1250 0.01074 0.00377 -0.0253 0.5640 0.0246
-2.750 -0.0972 0.01051 0.00350 -0.0252 0.5592 0.0249
-2.500 -0.0694 0.01033 0.00329 -0.0251 0.5544 0.0252
-2.250 -0.0414 0.01014 0.00308 -0.0250 0.5497 0.0254
-2.000 -0.0134 0.00997 0.00290 -0.0250 0.5446 0.0257
-1.750 0.0145 0.00983 0.00272 -0.0250 0.5397 0.0261
-1.500 0.0426 0.00968 0.00256 -0.0250 0.5350 0.0264
-1.250 0.0707 0.00955 0.00241 -0.0250 0.5292 0.0268
-1.000 0.0988 0.00944 0.00228 -0.0250 0.5236 0.0272
-0.750 0.1270 0.00933 0.00216 -0.0250 0.5187 0.0277
-0.500 0.1553 0.00925 0.00206 -0.0251 0.5125 0.0283
-0.250 0.1835 0.00920 0.00198 -0.0252 0.5065 0.0286
0.000 0.2116 0.00909 0.00186 -0.0252 0.5007 0.0293
0.250 0.2397 0.00902 0.00177 -0.0253 0.4942 0.0303
0.500 0.2679 0.00896 0.00170 -0.0254 0.4882 0.0313
0.750 0.2962 0.00892 0.00165 -0.0255 0.4816 0.0325
1.000 0.3244 0.00890 0.00162 -0.0257 0.4752 0.0338
1.250 0.3527 0.00887 0.00159 -0.0258 0.4690 0.0366
1.500 0.3807 0.00883 0.00157 -0.0259 0.4620 0.0478
1.750 0.4084 0.00874 0.00158 -0.0261 0.4558 0.0799
2.000 0.4361 0.00868 0.00160 -0.0262 0.4483 0.1159
2.250 0.4637 0.00862 0.00163 -0.0263 0.4415 0.1556
2.500 0.4912 0.00854 0.00167 -0.0264 0.4343 0.2109
2.750 0.5097 0.00750 0.00169 -0.0252 0.4284 0.6262
3.000 0.5244 0.00666 0.00180 -0.0221 0.4238 0.9198
3.250 0.5535 0.00676 0.00192 -0.0223 0.4183 0.9452
3.500 0.5853 0.00692 0.00207 -0.0232 0.4130 0.9630
3.750 0.6167 0.00707 0.00221 -0.0240 0.4079 0.9739
4.000 0.6578 0.00729 0.00239 -0.0271 0.4012 0.9801
4.250 0.6911 0.00744 0.00252 -0.0285 0.3952 0.9840
4.500 0.7265 0.00757 0.00261 -0.0304 0.3871 0.9848
4.750 0.7576 0.00770 0.00270 -0.0315 0.3794 0.9854
5.000 0.7887 0.00780 0.00278 -0.0325 0.3725 0.9860
5.250 0.8195 0.00794 0.00289 -0.0335 0.3664 0.9867
5.500 0.8501 0.00803 0.00298 -0.0344 0.3611 0.9875
5.750 0.8801 0.00816 0.00309 -0.0353 0.3544 0.9883
6.000 0.9099 0.00829 0.00321 -0.0361 0.3480 0.9892
6.250 0.9396 0.00842 0.00334 -0.0369 0.3411 0.9902
6.500 0.9688 0.00859 0.00349 -0.0376 0.3335 0.9913
6.750 0.9972 0.00879 0.00365 -0.0382 0.3220 0.9924
7.000 1.0249 0.00899 0.00382 -0.0387 0.3107 0.9935
7.250 1.0537 0.00925 0.00402 -0.0395 0.2960 0.9941
7.500 1.0822 0.00961 0.00429 -0.0403 0.2754 0.9946
7.750 1.1096 0.01013 0.00464 -0.0411 0.2447 0.9953
8.000 1.1363 0.01071 0.00505 -0.0418 0.2135 0.9962
8.250 1.1627 0.01128 0.00548 -0.0424 0.1864 0.9971
8.500 1.1844 0.01236 0.00624 -0.0426 0.1323 0.9983
8.750 1.2079 0.01315 0.00688 -0.0428 0.1053 0.9992
9.000 1.2328 0.01374 0.00739 -0.0432 0.0877 1.0000
9.250 1.2424 0.01466 0.00811 -0.0407 0.0570 1.0000
9.500 1.2542 0.01533 0.00871 -0.0384 0.0425 1.0000
9.750 1.2655 0.01594 0.00928 -0.0360 0.0328 1.0000
10.000 1.2763 0.01652 0.00983 -0.0335 0.0259 1.0000
10.250 1.2866 0.01707 0.01038 -0.0310 0.0215 1.0000
10.500 1.2956 0.01764 0.01094 -0.0283 0.0188 1.0000
10.750 1.2988 0.01816 0.01149 -0.0244 0.0174 1.0000
11.000 1.3045 0.01881 0.01217 -0.0215 0.0163 1.0000
11.250 1.3130 0.01963 0.01302 -0.0195 0.0152 1.0000
11.500 1.3232 0.02054 0.01396 -0.0180 0.0143 1.0000
11.750 1.3349 0.02148 0.01496 -0.0170 0.0137 1.0000
12.000 1.3460 0.02256 0.01608 -0.0161 0.0130 1.0000
12.250 1.3564 0.02378 0.01734 -0.0154 0.0124 1.0000
12.500 1.3656 0.02517 0.01876 -0.0147 0.0118 1.0000
12.750 1.3741 0.02669 0.02034 -0.0142 0.0113 1.0000
13.000 1.3839 0.02814 0.02185 -0.0138 0.0110 1.0000
13.250 1.3927 0.02973 0.02350 -0.0135 0.0107 1.0000
13.500 1.4007 0.03143 0.02526 -0.0132 0.0104 1.0000
13.750 1.4074 0.03328 0.02716 -0.0130 0.0101 1.0000
14.000 1.4131 0.03526 0.02921 -0.0127 0.0098 1.0000
14.250 1.4175 0.03739 0.03140 -0.0126 0.0095 1.0000
14.500 1.4206 0.03968 0.03375 -0.0124 0.0093 1.0000
14.750 1.4221 0.04214 0.03627 -0.0122 0.0090 1.0000
15.000 1.4217 0.04484 0.03904 -0.0121 0.0087 1.0000
15.250 1.4227 0.04743 0.04170 -0.0121 0.0086 1.0000
15.500 1.4247 0.04999 0.04433 -0.0122 0.0084 1.0000
15.750 1.4259 0.05270 0.04712 -0.0124 0.0083 1.0000
16.000 1.4267 0.05551 0.05000 -0.0126 0.0081 1.0000
16.250 1.4263 0.05850 0.05306 -0.0129 0.0080 1.0000
16.500 1.4253 0.06162 0.05626 -0.0133 0.0078 1.0000
16.750 1.4242 0.06482 0.05954 -0.0138 0.0077 1.0000
17.000 1.4223 0.06813 0.06292 -0.0143 0.0075 1.0000
17.250 1.4202 0.07151 0.06638 -0.0149 0.0074 1.0000
17.500 1.4172 0.07506 0.07000 -0.0156 0.0073 1.0000
17.750 1.4136 0.07876 0.07377 -0.0164 0.0072 1.0000
18.000 1.4094 0.08255 0.07763 -0.0172 0.0071 1.0000
18.250 1.4047 0.08643 0.08159 -0.0181 0.0069 1.0000
18.500 1.3996 0.09043 0.08566 -0.0190 0.0068 1.0000
18.750 1.3932 0.09469 0.09000 -0.0201 0.0067 1.0000
19.000 1.3855 0.09915 0.09455 -0.0213 0.0066 1.0000
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Polar data table (+)
Polar graphs
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