NACA M18 (nacam18-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M18 (nacam18-il) Reynolds number: 500,000 Max Cl/Cd: 99.25 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacam18-il-500000-n5.txt Download as CSV file: xf-nacam18-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4439 0.08810 0.08515 -0.0156 0.7531 0.0212
-8.500 -0.4470 0.08335 0.08038 -0.0194 0.7421 0.0213
-8.250 -0.4545 0.07808 0.07505 -0.0243 0.7317 0.0214
-7.750 -0.4606 0.06767 0.06446 -0.0310 0.7128 0.0220
-7.250 -0.5279 0.03108 0.02632 -0.0362 0.7062 0.0241
-7.000 -0.5120 0.02860 0.02354 -0.0351 0.6972 0.0243
-6.750 -0.4936 0.02658 0.02123 -0.0341 0.6882 0.0245
-6.500 -0.4735 0.02483 0.01921 -0.0332 0.6801 0.0247
-6.250 -0.4519 0.02334 0.01745 -0.0324 0.6719 0.0250
-6.000 -0.4293 0.02198 0.01584 -0.0316 0.6650 0.0252
-5.750 -0.4056 0.02080 0.01443 -0.0310 0.6578 0.0254
-5.500 -0.3812 0.01975 0.01315 -0.0304 0.6515 0.0257
-5.250 -0.3561 0.01879 0.01200 -0.0299 0.6452 0.0259
-5.000 -0.3304 0.01794 0.01096 -0.0295 0.6391 0.0262
-4.750 -0.3041 0.01725 0.01012 -0.0291 0.6337 0.0266
-4.500 -0.2775 0.01661 0.00934 -0.0289 0.6279 0.0270
-4.250 -0.2507 0.01598 0.00855 -0.0286 0.6224 0.0273
-4.000 -0.2236 0.01539 0.00783 -0.0283 0.6176 0.0276
-3.750 -0.1963 0.01485 0.00720 -0.0281 0.6124 0.0278
-3.500 -0.1690 0.01440 0.00664 -0.0279 0.6071 0.0281
-3.250 -0.1416 0.01400 0.00615 -0.0278 0.6023 0.0283
-3.000 -0.1139 0.01363 0.00572 -0.0277 0.5975 0.0285
-2.750 -0.0863 0.01330 0.00533 -0.0275 0.5924 0.0287
-2.500 -0.0596 0.01280 0.00476 -0.0273 0.5875 0.0291
-2.250 -0.0324 0.01240 0.00435 -0.0271 0.5827 0.0296
-2.000 -0.0050 0.01210 0.00404 -0.0270 0.5778 0.0300
-1.750 0.0223 0.01186 0.00377 -0.0268 0.5729 0.0305
-1.500 0.0499 0.01165 0.00354 -0.0267 0.5681 0.0311
-1.250 0.0775 0.01146 0.00334 -0.0267 0.5627 0.0319
-1.000 0.1052 0.01130 0.00316 -0.0266 0.5577 0.0327
-0.750 0.1328 0.01114 0.00297 -0.0265 0.5530 0.0334
-0.500 0.1606 0.01099 0.00281 -0.0265 0.5474 0.0340
-0.250 0.1884 0.01088 0.00267 -0.0265 0.5417 0.0346
0.000 0.2159 0.01074 0.00251 -0.0264 0.5367 0.0359
0.250 0.2438 0.01062 0.00241 -0.0264 0.5311 0.0375
0.500 0.2716 0.01055 0.00231 -0.0264 0.5251 0.0396
0.750 0.2995 0.01048 0.00224 -0.0265 0.5195 0.0431
1.000 0.3270 0.01036 0.00220 -0.0265 0.5134 0.0595
1.250 0.3542 0.01025 0.00218 -0.0265 0.5075 0.0917
1.500 0.3816 0.01013 0.00218 -0.0265 0.5013 0.1294
1.750 0.4088 0.01002 0.00219 -0.0265 0.4950 0.1768
2.000 0.4350 0.00981 0.00221 -0.0264 0.4890 0.2660
2.250 0.4446 0.00798 0.00232 -0.0227 0.4833 0.9041
2.500 0.4845 0.00819 0.00253 -0.0251 0.4763 0.9473
2.750 0.5233 0.00841 0.00272 -0.0274 0.4688 0.9656
3.250 0.6143 0.00891 0.00310 -0.0352 0.4531 0.9842
3.500 0.6606 0.00908 0.00321 -0.0394 0.4455 0.9878
3.750 0.6951 0.00917 0.00328 -0.0412 0.4391 0.9900
4.000 0.7250 0.00926 0.00335 -0.0419 0.4331 0.9913
4.250 0.7546 0.00938 0.00343 -0.0426 0.4278 0.9926
4.500 0.7841 0.00947 0.00351 -0.0432 0.4221 0.9938
4.750 0.8148 0.00957 0.00360 -0.0442 0.4157 0.9945
5.000 0.8453 0.00968 0.00369 -0.0451 0.4086 0.9953
5.250 0.8755 0.00980 0.00379 -0.0460 0.4008 0.9961
5.500 0.9057 0.00993 0.00391 -0.0470 0.3942 0.9970
5.750 0.9361 0.01005 0.00404 -0.0479 0.3871 0.9980
6.000 0.9663 0.01021 0.00419 -0.0489 0.3806 0.9989
6.250 0.9964 0.01034 0.00434 -0.0498 0.3743 0.9998
6.500 1.0221 0.01051 0.00451 -0.0498 0.3677 1.0000
6.750 1.0464 0.01065 0.00467 -0.0495 0.3605 1.0000
7.000 1.0700 0.01085 0.00485 -0.0490 0.3524 1.0000
7.250 1.0937 0.01102 0.00505 -0.0486 0.3438 1.0000
7.500 1.1165 0.01126 0.00527 -0.0481 0.3327 1.0000
7.750 1.1387 0.01154 0.00551 -0.0475 0.3193 1.0000
8.000 1.1595 0.01191 0.00581 -0.0467 0.2969 1.0000
8.250 1.1782 0.01243 0.00619 -0.0456 0.2699 1.0000
8.500 1.1968 0.01293 0.00659 -0.0445 0.2480 1.0000
8.750 1.2143 0.01347 0.00703 -0.0432 0.2265 1.0000
9.000 1.2293 0.01415 0.00758 -0.0416 0.1997 1.0000
9.250 1.2404 0.01503 0.00826 -0.0394 0.1617 1.0000
9.500 1.2456 0.01617 0.00916 -0.0363 0.1229 1.0000
9.750 1.2539 0.01702 0.00992 -0.0335 0.1047 1.0000
10.000 1.2619 0.01780 0.01064 -0.0308 0.0867 1.0000
10.250 1.2586 0.01900 0.01166 -0.0264 0.0594 1.0000
10.500 1.2542 0.01999 0.01262 -0.0218 0.0474 1.0000
10.750 1.2561 0.02111 0.01372 -0.0189 0.0385 1.0000
11.000 1.2609 0.02235 0.01496 -0.0169 0.0319 1.0000
11.250 1.2671 0.02368 0.01631 -0.0154 0.0271 1.0000
11.500 1.2744 0.02508 0.01774 -0.0143 0.0237 1.0000
11.750 1.2820 0.02656 0.01926 -0.0134 0.0214 1.0000
12.000 1.2893 0.02815 0.02091 -0.0127 0.0197 1.0000
12.250 1.2949 0.02996 0.02277 -0.0121 0.0183 1.0000
12.500 1.3021 0.03170 0.02458 -0.0116 0.0175 1.0000
12.750 1.3083 0.03358 0.02654 -0.0113 0.0167 1.0000
13.000 1.3130 0.03563 0.02865 -0.0109 0.0160 1.0000
13.250 1.3163 0.03788 0.03097 -0.0107 0.0154 1.0000
13.500 1.3178 0.04034 0.03350 -0.0104 0.0149 1.0000
13.750 1.3179 0.04297 0.03620 -0.0102 0.0144 1.0000
14.000 1.3204 0.04539 0.03872 -0.0101 0.0140 1.0000
14.250 1.3215 0.04796 0.04137 -0.0100 0.0136 1.0000
14.500 1.3222 0.05066 0.04416 -0.0100 0.0132 1.0000
14.750 1.3223 0.05351 0.04708 -0.0102 0.0129 1.0000
15.000 1.3218 0.05648 0.05014 -0.0104 0.0125 1.0000
15.250 1.3203 0.05964 0.05338 -0.0107 0.0122 1.0000
15.500 1.3179 0.06298 0.05681 -0.0111 0.0120 1.0000
15.750 1.3144 0.06653 0.06043 -0.0116 0.0117 1.0000
16.000 1.3093 0.07033 0.06432 -0.0122 0.0115 1.0000
16.250 1.3031 0.07437 0.06844 -0.0129 0.0113 1.0000
16.500 1.3012 0.07789 0.07205 -0.0136 0.0111 1.0000
16.750 1.2988 0.08149 0.07575 -0.0144 0.0110 1.0000
17.000 1.2961 0.08517 0.07951 -0.0152 0.0108 1.0000
17.250 1.2929 0.08896 0.08340 -0.0161 0.0106 1.0000
17.500 1.2894 0.09284 0.08737 -0.0170 0.0105 1.0000
17.750 1.2863 0.09668 0.09129 -0.0180 0.0103 1.0000
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