NACA M18 AIRFOIL (m18-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M18 AIRFOIL (m18-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.23 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m18-il-1000000.txt Download as CSV file: xf-m18-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3435 0.08385 0.08164 -0.0215 0.7524 0.0239
-9.000 -0.3407 0.08069 0.07844 -0.0223 0.7417 0.0240
-8.750 -0.4632 0.08156 0.07936 -0.0226 0.7723 0.0237
-8.500 -0.4642 0.07811 0.07585 -0.0247 0.7590 0.0239
-8.250 -0.4613 0.07512 0.07280 -0.0261 0.7462 0.0240
-8.000 -0.4545 0.07205 0.06966 -0.0278 0.7344 0.0242
-7.750 -0.4462 0.06897 0.06651 -0.0293 0.7237 0.0244
-7.500 -0.4364 0.06595 0.06340 -0.0308 0.7132 0.0247
-7.250 -0.4256 0.06271 0.06008 -0.0322 0.7038 0.0253
-7.000 -0.4148 0.05878 0.05602 -0.0337 0.6950 0.0262
-6.750 -0.4308 0.04096 0.03763 -0.0364 0.6922 0.0284
-6.500 -0.4127 0.03959 0.03616 -0.0360 0.6833 0.0286
-6.250 -0.3937 0.03810 0.03457 -0.0356 0.6755 0.0288
-6.000 -0.3741 0.03652 0.03287 -0.0352 0.6679 0.0292
-5.750 -0.3534 0.03508 0.03132 -0.0348 0.6612 0.0297
-5.500 -0.3334 0.03291 0.02899 -0.0343 0.6552 0.0306
-5.250 -0.3302 0.02406 0.01916 -0.0305 0.6511 0.0339
-5.000 -0.3070 0.02273 0.01773 -0.0300 0.6454 0.0343
-4.750 -0.2917 0.01672 0.01073 -0.0269 0.6412 0.0281
-4.500 -0.2663 0.01537 0.00918 -0.0265 0.6356 0.0282
-4.250 -0.2401 0.01434 0.00799 -0.0262 0.6298 0.0284
-4.000 -0.2130 0.01351 0.00708 -0.0260 0.6248 0.0286
-3.750 -0.1858 0.01288 0.00638 -0.0258 0.6191 0.0289
-3.500 -0.1584 0.01239 0.00582 -0.0257 0.6137 0.0291
-3.250 -0.1307 0.01193 0.00533 -0.0256 0.6091 0.0294
-3.000 -0.1030 0.01153 0.00490 -0.0255 0.6038 0.0297
-2.750 -0.0754 0.01120 0.00450 -0.0254 0.5985 0.0301
-2.500 -0.0476 0.01088 0.00417 -0.0254 0.5936 0.0305
-2.250 -0.0198 0.01062 0.00389 -0.0253 0.5880 0.0312
-2.000 0.0079 0.01038 0.00360 -0.0252 0.5822 0.0318
-1.750 0.0357 0.01013 0.00333 -0.0251 0.5767 0.0323
-1.500 0.0636 0.00992 0.00309 -0.0251 0.5705 0.0327
-1.250 0.0914 0.00978 0.00290 -0.0250 0.5644 0.0330
-1.000 0.1190 0.00951 0.00261 -0.0249 0.5587 0.0335
-0.750 0.1464 0.00926 0.00233 -0.0248 0.5521 0.0345
-0.500 0.1742 0.00911 0.00217 -0.0247 0.5457 0.0356
-0.250 0.2023 0.00899 0.00204 -0.0247 0.5384 0.0368
0.000 0.2304 0.00892 0.00193 -0.0247 0.5310 0.0382
0.250 0.2586 0.00882 0.00183 -0.0248 0.5230 0.0402
0.500 0.2865 0.00875 0.00174 -0.0248 0.5152 0.0443
0.750 0.3143 0.00862 0.00168 -0.0248 0.5074 0.0624
1.000 0.3414 0.00846 0.00167 -0.0247 0.4998 0.1174
1.500 0.3952 0.00813 0.00170 -0.0246 0.4848 0.2666
1.750 0.4004 0.00623 0.00169 -0.0201 0.4794 0.8907
2.000 0.4301 0.00635 0.00189 -0.0201 0.4722 0.9504
2.250 0.4602 0.00654 0.00205 -0.0203 0.4654 0.9683
2.500 0.4989 0.00676 0.00221 -0.0226 0.4578 0.9748
2.750 0.5423 0.00699 0.00239 -0.0260 0.4511 0.9799
3.000 0.5916 0.00724 0.00259 -0.0307 0.4445 0.9847
3.250 0.6421 0.00748 0.00275 -0.0357 0.4382 0.9879
3.500 0.6847 0.00760 0.00287 -0.0390 0.4341 0.9913
3.750 0.7239 0.00773 0.00298 -0.0415 0.4298 0.9942
4.000 0.7608 0.00782 0.00303 -0.0437 0.4247 0.9953
4.250 0.7925 0.00787 0.00307 -0.0447 0.4202 0.9960
4.500 0.8240 0.00791 0.00311 -0.0457 0.4160 0.9967
4.750 0.8552 0.00799 0.00317 -0.0466 0.4115 0.9974
5.000 0.8862 0.00811 0.00326 -0.0476 0.4066 0.9982
5.250 0.9180 0.00814 0.00332 -0.0486 0.4034 0.9990
5.500 0.9496 0.00820 0.00339 -0.0496 0.3992 0.9997
5.750 0.9780 0.00829 0.00348 -0.0500 0.3945 1.0000
6.000 1.0036 0.00840 0.00358 -0.0497 0.3901 1.0000
6.250 1.0295 0.00844 0.00365 -0.0495 0.3854 1.0000
6.500 1.0549 0.00854 0.00374 -0.0493 0.3786 1.0000
6.750 1.0803 0.00864 0.00384 -0.0490 0.3721 1.0000
7.000 1.1051 0.00877 0.00395 -0.0486 0.3610 1.0000
7.250 1.1299 0.00889 0.00406 -0.0482 0.3493 1.0000
7.500 1.1540 0.00907 0.00420 -0.0477 0.3356 1.0000
7.750 1.1773 0.00931 0.00438 -0.0472 0.3184 1.0000
8.000 1.1996 0.00963 0.00462 -0.0465 0.2968 1.0000
8.250 1.2200 0.01012 0.00496 -0.0455 0.2671 1.0000
8.500 1.2392 0.01068 0.00537 -0.0443 0.2396 1.0000
8.750 1.2578 0.01124 0.00581 -0.0431 0.2146 1.0000
9.000 1.2741 0.01192 0.00633 -0.0414 0.1842 1.0000
9.250 1.2823 0.01311 0.00718 -0.0386 0.1297 1.0000
9.500 1.2924 0.01401 0.00792 -0.0360 0.1024 1.0000
9.750 1.2995 0.01498 0.00870 -0.0329 0.0701 1.0000
10.000 1.3005 0.01614 0.00967 -0.0288 0.0424 1.0000
10.250 1.3058 0.01695 0.01043 -0.0254 0.0312 1.0000
10.500 1.3118 0.01765 0.01111 -0.0220 0.0262 1.0000
10.750 1.3099 0.01836 0.01184 -0.0173 0.0236 1.0000
11.000 1.3160 0.01910 0.01262 -0.0144 0.0221 1.0000
11.250 1.3234 0.02006 0.01361 -0.0123 0.0206 1.0000
11.500 1.3295 0.02132 0.01492 -0.0105 0.0191 1.0000
11.750 1.3406 0.02238 0.01603 -0.0094 0.0184 1.0000
12.000 1.3505 0.02363 0.01733 -0.0084 0.0177 1.0000
12.250 1.3589 0.02508 0.01883 -0.0075 0.0170 1.0000
12.500 1.3649 0.02682 0.02062 -0.0067 0.0163 1.0000
12.750 1.3656 0.02914 0.02303 -0.0058 0.0156 1.0000
13.000 1.3740 0.03081 0.02477 -0.0054 0.0153 1.0000
13.250 1.3804 0.03272 0.02674 -0.0050 0.0150 1.0000
13.500 1.3854 0.03478 0.02888 -0.0046 0.0146 1.0000
13.750 1.3895 0.03697 0.03113 -0.0043 0.0142 1.0000
14.000 1.3928 0.03926 0.03348 -0.0041 0.0139 1.0000
14.250 1.3936 0.04181 0.03610 -0.0038 0.0135 1.0000
14.500 1.3916 0.04471 0.03907 -0.0036 0.0132 1.0000
14.750 1.3854 0.04812 0.04255 -0.0035 0.0129 1.0000
15.000 1.3751 0.05213 0.04667 -0.0035 0.0126 1.0000
15.250 1.3742 0.05517 0.04979 -0.0037 0.0125 1.0000
15.500 1.3747 0.05808 0.05277 -0.0039 0.0124 1.0000
15.750 1.3740 0.06119 0.05597 -0.0042 0.0122 1.0000
16.000 1.3728 0.06442 0.05927 -0.0046 0.0120 1.0000
16.250 1.3711 0.06776 0.06269 -0.0051 0.0118 1.0000
16.500 1.3685 0.07122 0.06623 -0.0056 0.0117 1.0000
16.750 1.3657 0.07478 0.06986 -0.0062 0.0115 1.0000
17.000 1.3628 0.07839 0.07355 -0.0069 0.0113 1.0000
17.250 1.3598 0.08203 0.07726 -0.0076 0.0111 1.0000
17.500 1.3567 0.08570 0.08100 -0.0084 0.0110 1.0000
17.750 1.3525 0.08957 0.08493 -0.0093 0.0108 1.0000
18.000 1.3485 0.09345 0.08888 -0.0102 0.0107 1.0000
18.250 1.3438 0.09745 0.09294 -0.0112 0.0106 1.0000
18.500 1.3374 0.10170 0.09726 -0.0123 0.0104 1.0000
18.750 1.3305 0.10599 0.10162 -0.0134 0.0102 1.0000
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