NACA M18 AIRFOIL (m18-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M18 AIRFOIL (m18-il) Reynolds number: 500,000 Max Cl/Cd: 100.71 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m18-il-500000-n5.txt Download as CSV file: xf-m18-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4463 0.08469 0.08168 -0.0183 0.7374 0.0213
-8.500 -0.4530 0.07939 0.07635 -0.0233 0.7276 0.0214
-8.000 -0.4615 0.06905 0.06585 -0.0300 0.7097 0.0219
-7.500 -0.5320 0.03197 0.02730 -0.0354 0.7038 0.0241
-7.250 -0.5159 0.02958 0.02464 -0.0344 0.6953 0.0243
-7.000 -0.4985 0.02734 0.02209 -0.0334 0.6869 0.0245
-6.750 -0.4791 0.02544 0.01990 -0.0325 0.6790 0.0248
-6.500 -0.4581 0.02382 0.01800 -0.0316 0.6711 0.0250
-6.250 -0.4358 0.02239 0.01631 -0.0309 0.6642 0.0252
-6.000 -0.4125 0.02114 0.01483 -0.0303 0.6574 0.0254
-5.750 -0.3883 0.02004 0.01350 -0.0298 0.6513 0.0257
-5.500 -0.3633 0.01905 0.01231 -0.0294 0.6449 0.0259
-5.250 -0.3379 0.01815 0.01121 -0.0290 0.6386 0.0262
-5.000 -0.3117 0.01742 0.01032 -0.0287 0.6327 0.0266
-4.750 -0.2851 0.01677 0.00953 -0.0284 0.6269 0.0270
-4.500 -0.2584 0.01614 0.00874 -0.0282 0.6215 0.0273
-4.250 -0.2314 0.01552 0.00799 -0.0280 0.6166 0.0276
-4.000 -0.2041 0.01498 0.00735 -0.0279 0.6111 0.0279
-3.750 -0.1768 0.01453 0.00678 -0.0277 0.6054 0.0281
-3.500 -0.1493 0.01411 0.00628 -0.0276 0.6001 0.0283
-3.250 -0.1217 0.01373 0.00583 -0.0275 0.5942 0.0285
-3.000 -0.0942 0.01341 0.00543 -0.0274 0.5888 0.0287
-2.750 -0.0674 0.01285 0.00483 -0.0272 0.5839 0.0292
-2.500 -0.0402 0.01246 0.00442 -0.0270 0.5783 0.0296
-2.250 -0.0130 0.01217 0.00409 -0.0269 0.5727 0.0300
-2.000 0.0145 0.01192 0.00383 -0.0268 0.5672 0.0305
-1.750 0.0420 0.01170 0.00359 -0.0267 0.5607 0.0311
-1.500 0.0695 0.01153 0.00338 -0.0266 0.5545 0.0318
-1.250 0.0972 0.01135 0.00319 -0.0265 0.5479 0.0326
-1.000 0.1248 0.01119 0.00300 -0.0265 0.5414 0.0333
-0.750 0.1525 0.01105 0.00283 -0.0264 0.5353 0.0339
-0.500 0.1802 0.01093 0.00268 -0.0264 0.5283 0.0345
-0.250 0.2077 0.01080 0.00252 -0.0263 0.5219 0.0357
0.000 0.2355 0.01068 0.00241 -0.0262 0.5148 0.0372
0.500 0.2910 0.01056 0.00224 -0.0262 0.5003 0.0417
0.750 0.3184 0.01048 0.00219 -0.0262 0.4931 0.0518
1.000 0.3458 0.01036 0.00217 -0.0261 0.4870 0.0829
1.250 0.3730 0.01026 0.00217 -0.0261 0.4807 0.1169
1.500 0.4001 0.01018 0.00219 -0.0260 0.4751 0.1603
1.750 0.4268 0.01001 0.00222 -0.0259 0.4693 0.2318
2.000 0.4364 0.00839 0.00214 -0.0227 0.4643 0.7605
2.250 0.4735 0.00828 0.00252 -0.0240 0.4588 0.9413
2.500 0.5088 0.00848 0.00270 -0.0254 0.4538 0.9612
2.750 0.5557 0.00878 0.00294 -0.0295 0.4472 0.9747
3.000 0.6002 0.00902 0.00312 -0.0331 0.4405 0.9824
3.250 0.6476 0.00921 0.00325 -0.0374 0.4330 0.9868
3.500 0.6847 0.00934 0.00334 -0.0396 0.4273 0.9895
3.750 0.7155 0.00942 0.00341 -0.0404 0.4227 0.9909
4.000 0.7453 0.00951 0.00348 -0.0410 0.4182 0.9923
4.250 0.7745 0.00964 0.00358 -0.0415 0.4142 0.9935
4.500 0.8050 0.00972 0.00366 -0.0422 0.4108 0.9943
4.750 0.8358 0.00980 0.00375 -0.0431 0.4062 0.9950
5.000 0.8662 0.00991 0.00385 -0.0438 0.4010 0.9958
5.250 0.8963 0.01004 0.00396 -0.0446 0.3963 0.9967
5.500 0.9270 0.01012 0.00408 -0.0454 0.3916 0.9977
5.750 0.9574 0.01024 0.00421 -0.0462 0.3863 0.9987
6.000 0.9873 0.01040 0.00436 -0.0470 0.3816 0.9995
6.250 1.0155 0.01050 0.00451 -0.0473 0.3775 1.0000
6.500 1.0400 0.01062 0.00466 -0.0468 0.3725 1.0000
6.750 1.0640 0.01078 0.00482 -0.0463 0.3670 1.0000
7.000 1.0882 0.01091 0.00500 -0.0458 0.3611 1.0000
7.250 1.1117 0.01109 0.00518 -0.0451 0.3522 1.0000
7.500 1.1350 0.01127 0.00536 -0.0445 0.3405 1.0000
7.750 1.1565 0.01158 0.00560 -0.0436 0.3197 1.0000
8.000 1.1753 0.01211 0.00595 -0.0424 0.2830 1.0000
8.250 1.1928 0.01272 0.00640 -0.0410 0.2531 1.0000
8.500 1.2095 0.01334 0.00690 -0.0395 0.2289 1.0000
8.750 1.2253 0.01398 0.00743 -0.0377 0.2048 1.0000
9.000 1.2386 0.01474 0.00805 -0.0357 0.1748 1.0000
9.250 1.2450 0.01587 0.00891 -0.0326 0.1319 1.0000
9.500 1.2537 0.01673 0.00967 -0.0299 0.1106 1.0000
9.750 1.2622 0.01752 0.01039 -0.0271 0.0942 1.0000
10.000 1.2638 0.01856 0.01130 -0.0233 0.0688 1.0000
10.250 1.2581 0.01963 0.01228 -0.0183 0.0518 1.0000
10.500 1.2574 0.02072 0.01334 -0.0147 0.0421 1.0000
10.750 1.2610 0.02193 0.01456 -0.0122 0.0347 1.0000
11.000 1.2669 0.02323 0.01587 -0.0105 0.0292 1.0000
11.250 1.2737 0.02463 0.01730 -0.0091 0.0254 1.0000
11.500 1.2800 0.02618 0.01888 -0.0080 0.0225 1.0000
11.750 1.2879 0.02771 0.02046 -0.0072 0.0206 1.0000
12.000 1.2942 0.02945 0.02225 -0.0064 0.0191 1.0000
12.250 1.2997 0.03133 0.02419 -0.0058 0.0180 1.0000
12.500 1.3062 0.03319 0.02613 -0.0053 0.0172 1.0000
12.750 1.3113 0.03521 0.02822 -0.0049 0.0165 1.0000
13.000 1.3150 0.03741 0.03049 -0.0045 0.0158 1.0000
13.250 1.3172 0.03981 0.03295 -0.0041 0.0152 1.0000
13.500 1.3173 0.04243 0.03565 -0.0038 0.0147 1.0000
13.750 1.3178 0.04507 0.03837 -0.0036 0.0143 1.0000
14.000 1.3193 0.04761 0.04100 -0.0035 0.0139 1.0000
14.250 1.3200 0.05029 0.04377 -0.0034 0.0135 1.0000
14.500 1.3202 0.05311 0.04667 -0.0034 0.0131 1.0000
14.750 1.3199 0.05607 0.04971 -0.0036 0.0128 1.0000
15.000 1.3190 0.05915 0.05287 -0.0038 0.0124 1.0000
15.250 1.3172 0.06241 0.05622 -0.0041 0.0122 1.0000
15.500 1.3145 0.06585 0.05973 -0.0046 0.0119 1.0000
15.750 1.3107 0.06947 0.06344 -0.0051 0.0117 1.0000
16.000 1.3054 0.07335 0.06740 -0.0057 0.0114 1.0000
16.250 1.3006 0.07724 0.07137 -0.0064 0.0112 1.0000
16.500 1.2989 0.08074 0.07496 -0.0071 0.0111 1.0000
16.750 1.2967 0.08430 0.07862 -0.0078 0.0109 1.0000
17.000 1.2938 0.08802 0.08243 -0.0086 0.0107 1.0000
17.250 1.2909 0.09179 0.08627 -0.0095 0.0106 1.0000
17.500 1.2883 0.09553 0.09010 -0.0104 0.0104 1.0000
17.750 1.2850 0.09940 0.09407 -0.0114 0.0102 1.0000
18.000 1.2821 0.10322 0.09797 -0.0125 0.0100 1.0000
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