NACA M18 AIRFOIL (m18-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: NACA M18 AIRFOIL (m18-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.83 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m18-il-1000000-n5.txt Download as CSV file: xf-m18-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M18 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5068 0.10128 0.09883 -0.0058 0.7378 0.0163
-10.250 -0.5023 0.09814 0.09563 -0.0076 0.7233 0.0164
-10.000 -0.8019 0.02946 0.02572 -0.0355 0.7642 0.0198
-9.750 -0.7876 0.02736 0.02337 -0.0343 0.7517 0.0200
-9.500 -0.7687 0.02602 0.02184 -0.0334 0.7380 0.0201
-9.250 -0.7479 0.02498 0.02063 -0.0327 0.7221 0.0202
-9.000 -0.7256 0.02419 0.01968 -0.0321 0.7053 0.0204
-8.750 -0.7027 0.02345 0.01880 -0.0315 0.6908 0.0205
-8.500 -0.6795 0.02269 0.01790 -0.0310 0.6797 0.0207
-8.250 -0.6570 0.02171 0.01674 -0.0303 0.6706 0.0208
-8.000 -0.6341 0.02074 0.01560 -0.0297 0.6628 0.0210
-7.750 -0.6107 0.01981 0.01450 -0.0291 0.6547 0.0211
-7.500 -0.5866 0.01896 0.01348 -0.0286 0.6478 0.0213
-7.250 -0.5622 0.01813 0.01250 -0.0281 0.6413 0.0214
-7.000 -0.5372 0.01739 0.01161 -0.0277 0.6356 0.0216
-6.750 -0.5118 0.01667 0.01076 -0.0273 0.6301 0.0218
-6.500 -0.4860 0.01602 0.00998 -0.0270 0.6240 0.0220
-6.250 -0.4599 0.01543 0.00926 -0.0267 0.6185 0.0221
-6.000 -0.4334 0.01486 0.00859 -0.0265 0.6135 0.0223
-5.750 -0.4067 0.01435 0.00799 -0.0263 0.6086 0.0225
-5.500 -0.3798 0.01390 0.00743 -0.0261 0.6038 0.0227
-5.250 -0.3525 0.01351 0.00696 -0.0259 0.5996 0.0229
-5.000 -0.3251 0.01317 0.00657 -0.0258 0.5945 0.0232
-4.750 -0.2976 0.01285 0.00617 -0.0257 0.5891 0.0234
-4.500 -0.2701 0.01253 0.00578 -0.0256 0.5843 0.0235
-4.250 -0.2424 0.01222 0.00542 -0.0255 0.5794 0.0236
-4.000 -0.2146 0.01196 0.00511 -0.0255 0.5743 0.0237
-3.750 -0.1878 0.01146 0.00454 -0.0253 0.5696 0.0240
-3.500 -0.1605 0.01108 0.00413 -0.0251 0.5648 0.0243
-3.250 -0.1330 0.01080 0.00382 -0.0250 0.5593 0.0246
-3.000 -0.1052 0.01059 0.00356 -0.0250 0.5538 0.0249
-2.750 -0.0773 0.01038 0.00334 -0.0250 0.5477 0.0252
-2.500 -0.0495 0.01021 0.00313 -0.0249 0.5408 0.0255
-2.250 -0.0215 0.01005 0.00294 -0.0249 0.5347 0.0257
-2.000 0.0065 0.00990 0.00276 -0.0249 0.5278 0.0261
-1.750 0.0344 0.00976 0.00260 -0.0249 0.5213 0.0264
-1.500 0.0625 0.00963 0.00245 -0.0249 0.5141 0.0268
-1.250 0.0905 0.00953 0.00231 -0.0249 0.5068 0.0272
-1.000 0.1186 0.00943 0.00219 -0.0249 0.4994 0.0277
-0.750 0.1467 0.00938 0.00209 -0.0250 0.4914 0.0282
-0.500 0.1750 0.00931 0.00201 -0.0250 0.4835 0.0286
-0.250 0.2029 0.00924 0.00190 -0.0251 0.4757 0.0293
0.000 0.2310 0.00916 0.00180 -0.0251 0.4692 0.0302
0.250 0.2591 0.00912 0.00174 -0.0252 0.4628 0.0312
0.500 0.2873 0.00908 0.00170 -0.0252 0.4574 0.0322
0.750 0.3156 0.00905 0.00166 -0.0253 0.4520 0.0335
1.250 0.3719 0.00901 0.00162 -0.0255 0.4416 0.0416
1.500 0.3996 0.00891 0.00163 -0.0256 0.4366 0.0737
1.750 0.4273 0.00886 0.00165 -0.0256 0.4315 0.1030
2.250 0.4827 0.00872 0.00172 -0.0257 0.4214 0.1880
2.500 0.5085 0.00846 0.00179 -0.0256 0.4161 0.3272
2.750 0.5154 0.00681 0.00183 -0.0213 0.4121 0.9058
3.000 0.5446 0.00687 0.00196 -0.0214 0.4072 0.9401
3.250 0.5737 0.00700 0.00208 -0.0216 0.4024 0.9593
3.500 0.6051 0.00717 0.00224 -0.0223 0.3989 0.9727
3.750 0.6459 0.00736 0.00241 -0.0252 0.3957 0.9787
4.000 0.6792 0.00749 0.00254 -0.0264 0.3925 0.9837
4.250 0.7164 0.00761 0.00264 -0.0286 0.3870 0.9846
4.500 0.7483 0.00774 0.00273 -0.0297 0.3812 0.9852
4.750 0.7797 0.00781 0.00280 -0.0306 0.3773 0.9859
5.000 0.8108 0.00790 0.00288 -0.0315 0.3728 0.9865
5.250 0.8414 0.00801 0.00298 -0.0323 0.3682 0.9873
5.500 0.8717 0.00812 0.00307 -0.0330 0.3644 0.9880
5.750 0.9018 0.00820 0.00317 -0.0337 0.3607 0.9889
6.000 0.9318 0.00830 0.00328 -0.0344 0.3561 0.9898
6.250 0.9612 0.00845 0.00341 -0.0350 0.3506 0.9909
6.500 0.9906 0.00856 0.00354 -0.0355 0.3435 0.9919
6.750 1.0187 0.00875 0.00369 -0.0359 0.3338 0.9930
7.000 1.0468 0.00896 0.00386 -0.0363 0.3198 0.9939
7.250 1.0756 0.00930 0.00409 -0.0370 0.2936 0.9944
7.500 1.1020 0.00995 0.00450 -0.0375 0.2516 0.9951
7.750 1.1280 0.01065 0.00499 -0.0379 0.2156 0.9960
8.000 1.1550 0.01116 0.00538 -0.0384 0.1913 0.9968
8.250 1.1800 0.01186 0.00590 -0.0387 0.1573 0.9978
8.500 1.2016 0.01290 0.00667 -0.0386 0.1127 0.9989
8.750 1.2262 0.01354 0.00722 -0.0388 0.0942 0.9997
9.000 1.2417 0.01434 0.00786 -0.0372 0.0676 1.0000
9.250 1.2524 0.01511 0.00851 -0.0346 0.0476 1.0000
9.500 1.2643 0.01572 0.00908 -0.0322 0.0368 1.0000
9.750 1.2752 0.01632 0.00964 -0.0296 0.0289 1.0000
10.250 1.2952 0.01744 0.01075 -0.0241 0.0201 1.0000
10.500 1.2999 0.01800 0.01133 -0.0205 0.0181 1.0000
10.750 1.3041 0.01859 0.01195 -0.0169 0.0169 1.0000
11.000 1.3118 0.01936 0.01275 -0.0145 0.0158 1.0000
11.250 1.3210 0.02027 0.01369 -0.0127 0.0147 1.0000
11.500 1.3323 0.02121 0.01468 -0.0114 0.0140 1.0000
11.750 1.3435 0.02225 0.01576 -0.0103 0.0134 1.0000
12.000 1.3541 0.02344 0.01699 -0.0094 0.0127 1.0000
12.250 1.3637 0.02477 0.01836 -0.0085 0.0121 1.0000
12.500 1.3720 0.02630 0.01993 -0.0078 0.0115 1.0000
12.750 1.3809 0.02783 0.02153 -0.0072 0.0111 1.0000
13.000 1.3898 0.02940 0.02316 -0.0067 0.0109 1.0000
13.250 1.3978 0.03111 0.02493 -0.0063 0.0106 1.0000
13.500 1.4048 0.03294 0.02682 -0.0059 0.0103 1.0000
13.750 1.4106 0.03491 0.02885 -0.0056 0.0100 1.0000
14.000 1.4152 0.03703 0.03103 -0.0053 0.0097 1.0000
14.250 1.4186 0.03929 0.03335 -0.0050 0.0094 1.0000
14.500 1.4205 0.04172 0.03584 -0.0047 0.0092 1.0000
14.750 1.4208 0.04434 0.03853 -0.0045 0.0089 1.0000
15.000 1.4192 0.04721 0.04147 -0.0044 0.0087 1.0000
15.250 1.4214 0.04975 0.04408 -0.0044 0.0085 1.0000
15.500 1.4229 0.05242 0.04682 -0.0044 0.0084 1.0000
15.750 1.4236 0.05524 0.04972 -0.0046 0.0082 1.0000
16.000 1.4235 0.05819 0.05274 -0.0048 0.0081 1.0000
16.250 1.4228 0.06129 0.05591 -0.0051 0.0079 1.0000
16.500 1.4217 0.06447 0.05917 -0.0055 0.0078 1.0000
16.750 1.4202 0.06774 0.06252 -0.0060 0.0076 1.0000
17.000 1.4183 0.07109 0.06594 -0.0065 0.0075 1.0000
17.250 1.4160 0.07454 0.06946 -0.0071 0.0074 1.0000
17.500 1.4129 0.07815 0.07314 -0.0078 0.0072 1.0000
17.750 1.4092 0.08185 0.07692 -0.0085 0.0071 1.0000
18.000 1.4054 0.08559 0.08072 -0.0093 0.0070 1.0000
18.250 1.4010 0.08945 0.08466 -0.0102 0.0069 1.0000
18.500 1.3952 0.09359 0.08887 -0.0112 0.0068 1.0000
18.750 1.3889 0.09781 0.09317 -0.0124 0.0067 1.0000
19.000 1.3818 0.10215 0.09759 -0.0135 0.0066 1.0000
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Polar data table (+)
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