NACA M18 (nacam18-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M18 (nacam18-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.09 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacam18-il-1000000.txt Download as CSV file: xf-nacam18-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4460 0.09200 0.08988 -0.0149 0.7976 0.0234
-8.750 -0.4485 0.08689 0.08472 -0.0189 0.7843 0.0234
-8.500 -0.4650 0.08013 0.07793 -0.0239 0.7720 0.0238
-8.250 -0.4661 0.07695 0.07468 -0.0253 0.7586 0.0239
-8.000 -0.4606 0.07390 0.07156 -0.0269 0.7456 0.0240
-7.750 -0.4532 0.07085 0.06845 -0.0285 0.7335 0.0242
-7.500 -0.4443 0.06783 0.06534 -0.0300 0.7224 0.0245
-7.250 -0.3634 0.05561 0.05315 -0.0338 0.6888 0.0256
-7.000 -0.3641 0.05067 0.04812 -0.0356 0.6820 0.0264
-6.750 -0.4127 0.05592 0.05309 -0.0351 0.6938 0.0273
-6.500 -0.4268 0.04004 0.03666 -0.0367 0.6900 0.0285
-6.250 -0.4083 0.03871 0.03523 -0.0362 0.6812 0.0287
-6.000 -0.3890 0.03725 0.03367 -0.0358 0.6736 0.0289
-5.750 -0.3689 0.03578 0.03209 -0.0353 0.6662 0.0293
-5.500 -0.3481 0.03435 0.03053 -0.0349 0.6596 0.0298
-5.250 -0.3581 0.02006 0.01478 -0.0292 0.6567 0.0274
-5.000 -0.3352 0.01836 0.01277 -0.0283 0.6504 0.0274
-4.750 -0.3092 0.01769 0.01192 -0.0279 0.6447 0.0277
-4.500 -0.2839 0.01667 0.01066 -0.0273 0.6392 0.0281
-4.250 -0.2584 0.01537 0.00916 -0.0268 0.6336 0.0282
-4.000 -0.2322 0.01426 0.00790 -0.0265 0.6284 0.0284
-3.750 -0.2052 0.01342 0.00697 -0.0263 0.6234 0.0286
-3.500 -0.1779 0.01278 0.00626 -0.0261 0.6183 0.0288
-3.250 -0.1505 0.01229 0.00569 -0.0259 0.6131 0.0291
-3.000 -0.1228 0.01182 0.00520 -0.0258 0.6086 0.0294
-2.750 -0.0952 0.01144 0.00478 -0.0257 0.6036 0.0297
-2.500 -0.0676 0.01112 0.00441 -0.0255 0.5988 0.0301
-2.250 -0.0398 0.01081 0.00408 -0.0254 0.5943 0.0305
-2.000 -0.0120 0.01055 0.00381 -0.0254 0.5893 0.0312
-1.750 0.0157 0.01031 0.00352 -0.0252 0.5843 0.0318
-1.500 0.0434 0.01009 0.00327 -0.0251 0.5796 0.0323
-1.250 0.0714 0.00987 0.00304 -0.0251 0.5749 0.0327
-1.000 0.0994 0.00970 0.00285 -0.0251 0.5696 0.0331
-0.750 0.1267 0.00949 0.00258 -0.0249 0.5644 0.0336
-0.500 0.1543 0.00922 0.00231 -0.0248 0.5598 0.0346
-0.250 0.1823 0.00907 0.00215 -0.0248 0.5543 0.0357
0.000 0.2102 0.00898 0.00203 -0.0248 0.5486 0.0370
0.250 0.2386 0.00887 0.00193 -0.0249 0.5436 0.0385
0.500 0.2667 0.00877 0.00182 -0.0250 0.5378 0.0409
0.750 0.2947 0.00870 0.00174 -0.0250 0.5319 0.0456
1.000 0.3224 0.00851 0.00169 -0.0250 0.5261 0.0784
1.250 0.3497 0.00835 0.00168 -0.0250 0.5199 0.1324
1.500 0.3771 0.00820 0.00168 -0.0251 0.5138 0.1903
1.750 0.4027 0.00784 0.00169 -0.0249 0.5074 0.3343
2.000 0.4087 0.00612 0.00173 -0.0203 0.5016 0.9185
2.250 0.4386 0.00625 0.00190 -0.0205 0.4949 0.9573
2.500 0.4696 0.00644 0.00204 -0.0210 0.4875 0.9710
2.750 0.5141 0.00665 0.00222 -0.0247 0.4803 0.9763
3.000 0.5515 0.00686 0.00237 -0.0268 0.4730 0.9822
3.250 0.6098 0.00712 0.00258 -0.0337 0.4654 0.9858
3.500 0.6553 0.00729 0.00270 -0.0377 0.4584 0.9887
3.750 0.6967 0.00746 0.00283 -0.0409 0.4519 0.9926
4.000 0.7373 0.00755 0.00290 -0.0439 0.4450 0.9947
4.250 0.7708 0.00764 0.00295 -0.0455 0.4376 0.9955
4.500 0.8024 0.00769 0.00298 -0.0466 0.4306 0.9962
4.750 0.8336 0.00779 0.00304 -0.0477 0.4235 0.9970
5.000 0.8649 0.00784 0.00309 -0.0488 0.4175 0.9977
5.250 0.8962 0.00793 0.00316 -0.0499 0.4109 0.9985
5.500 0.9276 0.00802 0.00324 -0.0510 0.4051 0.9993
5.750 0.9592 0.00810 0.00333 -0.0522 0.3989 0.9999
6.000 0.9854 0.00823 0.00343 -0.0523 0.3916 1.0000
6.250 1.0112 0.00829 0.00350 -0.0522 0.3852 1.0000
6.500 1.0365 0.00845 0.00362 -0.0521 0.3761 1.0000
6.750 1.0621 0.00854 0.00372 -0.0521 0.3675 1.0000
7.000 1.0870 0.00869 0.00385 -0.0519 0.3580 1.0000
7.250 1.1113 0.00889 0.00400 -0.0517 0.3431 1.0000
7.500 1.1351 0.00910 0.00416 -0.0513 0.3285 1.0000
7.750 1.1585 0.00935 0.00435 -0.0510 0.3130 1.0000
8.000 1.1814 0.00962 0.00457 -0.0505 0.2962 1.0000
8.250 1.2035 0.00994 0.00483 -0.0499 0.2780 1.0000
8.500 1.2244 0.01036 0.00514 -0.0492 0.2570 1.0000
8.750 1.2448 0.01078 0.00548 -0.0484 0.2365 1.0000
9.000 1.2629 0.01136 0.00592 -0.0472 0.2101 1.0000
9.250 1.2765 0.01222 0.00653 -0.0454 0.1679 1.0000
9.500 1.2830 0.01347 0.00746 -0.0424 0.1172 1.0000
9.750 1.2938 0.01429 0.00814 -0.0400 0.0928 1.0000
10.000 1.2957 0.01550 0.00910 -0.0362 0.0546 1.0000
10.250 1.2991 0.01647 0.00996 -0.0326 0.0360 1.0000
10.500 1.3046 0.01723 0.01069 -0.0293 0.0280 1.0000
10.750 1.3087 0.01788 0.01134 -0.0257 0.0248 1.0000
11.000 1.3096 0.01857 0.01206 -0.0217 0.0228 1.0000
11.250 1.3166 0.01939 0.01291 -0.0193 0.0213 1.0000
11.500 1.3233 0.02047 0.01402 -0.0174 0.0198 1.0000
11.750 1.3324 0.02158 0.01519 -0.0161 0.0188 1.0000
12.000 1.3429 0.02271 0.01637 -0.0152 0.0180 1.0000
12.250 1.3524 0.02401 0.01773 -0.0144 0.0173 1.0000
12.500 1.3599 0.02555 0.01931 -0.0136 0.0166 1.0000
12.750 1.3632 0.02757 0.02139 -0.0129 0.0159 1.0000
13.000 1.3688 0.02944 0.02335 -0.0123 0.0155 1.0000
13.250 1.3764 0.03119 0.02516 -0.0120 0.0152 1.0000
13.500 1.3824 0.03313 0.02717 -0.0118 0.0148 1.0000
13.750 1.3873 0.03520 0.02930 -0.0115 0.0144 1.0000
14.000 1.3913 0.03739 0.03156 -0.0113 0.0140 1.0000
14.250 1.3939 0.03975 0.03398 -0.0112 0.0137 1.0000
14.500 1.3935 0.04243 0.03673 -0.0110 0.0134 1.0000
14.750 1.3892 0.04558 0.03996 -0.0108 0.0130 1.0000
15.000 1.3802 0.04932 0.04379 -0.0107 0.0127 1.0000
15.250 1.3761 0.05266 0.04722 -0.0108 0.0126 1.0000
15.500 1.3769 0.05551 0.05015 -0.0111 0.0124 1.0000
15.750 1.3767 0.05850 0.05322 -0.0114 0.0123 1.0000
16.000 1.3755 0.06167 0.05647 -0.0118 0.0121 1.0000
16.250 1.3740 0.06494 0.05981 -0.0123 0.0119 1.0000
16.500 1.3717 0.06834 0.06330 -0.0128 0.0117 1.0000
16.750 1.3691 0.07183 0.06687 -0.0134 0.0115 1.0000
17.000 1.3659 0.07546 0.07057 -0.0141 0.0114 1.0000
17.250 1.3625 0.07916 0.07434 -0.0148 0.0112 1.0000
17.500 1.3592 0.08286 0.07811 -0.0156 0.0110 1.0000
17.750 1.3555 0.08662 0.08194 -0.0165 0.0109 1.0000
18.000 1.3510 0.09058 0.08597 -0.0174 0.0108 1.0000
18.250 1.3460 0.09464 0.09010 -0.0185 0.0106 1.0000
18.500 1.3405 0.09875 0.09427 -0.0195 0.0105 1.0000
18.750 1.3334 0.10312 0.09871 -0.0207 0.0103 1.0000
19.000 1.3247 0.10769 0.10335 -0.0219 0.0101 1.0000
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Polar data table (+)
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