NACA M25 AIRFOIL (m25-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M25 AIRFOIL (m25-il) Reynolds number: 200,000 Max Cl/Cd: 78.46 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m25-il-200000-n5.txt Download as CSV file: xf-m25-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M25 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3955 0.14486 0.14097 0.0320 0.6703 0.0111
-10.500 -0.3887 0.14139 0.13748 0.0310 0.6652 0.0113
-10.250 -0.3815 0.13823 0.13428 0.0298 0.6608 0.0115
-10.000 -0.3740 0.13513 0.13118 0.0285 0.6562 0.0117
-9.750 -0.3664 0.13208 0.12811 0.0272 0.6515 0.0120
-9.500 -0.3587 0.12905 0.12505 0.0258 0.6474 0.0122
-9.250 -0.3510 0.12604 0.12202 0.0244 0.6432 0.0125
-9.000 -0.3431 0.12302 0.11900 0.0229 0.6385 0.0128
-8.750 -0.3352 0.12003 0.11598 0.0214 0.6343 0.0132
-8.250 -0.3188 0.11409 0.11001 0.0183 0.6263 0.0139
-8.000 -0.3101 0.11118 0.10710 0.0165 0.6222 0.0143
-7.750 -0.3012 0.10838 0.10428 0.0145 0.6185 0.0145
-7.500 -0.2922 0.10572 0.10160 0.0122 0.6150 0.0147
-7.250 -0.2829 0.10321 0.09909 0.0096 0.6108 0.0148
-7.000 -0.2694 0.10049 0.09634 0.0062 0.6068 0.0149
-6.750 -0.2543 0.09772 0.09350 0.0027 0.6033 0.0150
-6.500 -0.2362 0.09517 0.09090 -0.0016 0.5998 0.0151
-6.250 -0.2144 0.09282 0.08852 -0.0068 0.5958 0.0151
-6.000 -0.2066 0.08736 0.08306 -0.0063 0.5923 0.0154
-5.750 -0.1944 0.08345 0.07911 -0.0073 0.5889 0.0157
-5.500 -0.1771 0.08020 0.07580 -0.0096 0.5856 0.0161
-5.250 -0.1573 0.07707 0.07263 -0.0124 0.5815 0.0165
-5.000 -0.1357 0.07400 0.06951 -0.0154 0.5777 0.0171
-4.750 -0.1127 0.07098 0.06641 -0.0183 0.5745 0.0178
-4.500 -0.0876 0.06805 0.06337 -0.0214 0.5714 0.0190
-4.250 -0.0569 0.06543 0.06066 -0.0252 0.5674 0.0201
-4.000 -0.0234 0.06305 0.05816 -0.0292 0.5635 0.0205
-3.750 0.0140 0.06111 0.05602 -0.0335 0.5601 0.0207
-3.500 0.0437 0.05826 0.05301 -0.0360 0.5573 0.0208
-3.250 0.0738 0.05534 0.04998 -0.0384 0.5535 0.0208
-3.000 0.1037 0.05245 0.04696 -0.0404 0.5498 0.0209
-2.500 0.1377 0.04559 0.03999 -0.0413 0.5436 0.0246
-2.250 0.1769 0.04443 0.03863 -0.0436 0.5400 0.0280
-2.000 0.2131 0.04276 0.03675 -0.0453 0.5363 0.0284
-1.750 0.2470 0.04102 0.03479 -0.0465 0.5328 0.0287
-1.500 0.2741 0.03779 0.03138 -0.0474 0.5299 0.0291
-1.250 0.2943 0.03489 0.02839 -0.0479 0.5269 0.0302
-1.000 0.3207 0.03315 0.02657 -0.0486 0.5231 0.0321
-0.750 0.3604 0.03332 0.02644 -0.0493 0.5193 0.0387
-0.500 0.3912 0.03200 0.02488 -0.0496 0.5161 0.0389
0.000 0.4396 0.02751 0.02022 -0.0507 0.5097 0.0428
0.250 0.4769 0.02814 0.02052 -0.0507 0.5059 0.0507
0.500 0.4999 0.02547 0.01782 -0.0514 0.5026 0.0526
0.750 0.5267 0.02441 0.01662 -0.0516 0.4997 0.0549
1.000 0.5556 0.02359 0.01568 -0.0519 0.4963 0.0586
1.250 0.5882 0.02313 0.01494 -0.0518 0.4927 0.0637
1.500 0.6147 0.02188 0.01365 -0.0522 0.4893 0.0653
1.750 0.6432 0.02103 0.01262 -0.0523 0.4862 0.0659
2.000 0.6738 0.01952 0.01081 -0.0519 0.4833 0.0444
2.250 0.7027 0.01895 0.01014 -0.0520 0.4795 0.0475
2.500 0.7314 0.01818 0.00924 -0.0521 0.4760 0.0445
2.750 0.7605 0.01733 0.00815 -0.0520 0.4730 0.0410
3.000 0.7886 0.01697 0.00763 -0.0519 0.4702 0.0395
3.250 0.8164 0.01676 0.00739 -0.0521 0.4665 0.0389
3.500 0.8439 0.01636 0.00698 -0.0522 0.4626 0.0385
3.750 0.8708 0.01606 0.00666 -0.0522 0.4592 0.0383
4.000 0.8975 0.01586 0.00641 -0.0521 0.4564 0.0383
4.250 0.9242 0.01574 0.00631 -0.0522 0.4533 0.0384
4.500 0.9507 0.01568 0.00632 -0.0522 0.4495 0.0388
4.750 0.9770 0.01561 0.00626 -0.0521 0.4459 0.0399
5.000 1.0039 0.01564 0.00624 -0.0522 0.4427 0.0425
5.250 1.0311 0.01575 0.00633 -0.0524 0.4396 0.0466
5.750 1.0852 0.01601 0.00692 -0.0528 0.4321 0.1353
6.750 1.2216 0.01557 0.00767 -0.0607 0.3662 1.0000
7.000 1.2421 0.01645 0.00824 -0.0607 0.3088 1.0000
7.250 1.2310 0.02157 0.01202 -0.0599 0.0901 1.0000
7.500 1.2324 0.02409 0.01436 -0.0585 0.0252 1.0000
7.750 1.2433 0.02545 0.01585 -0.0576 0.0214 1.0000
8.000 1.2483 0.02732 0.01788 -0.0569 0.0193 1.0000
8.250 1.2450 0.02963 0.02037 -0.0553 0.0177 1.0000
8.500 1.2488 0.03161 0.02247 -0.0544 0.0167 1.0000
8.750 1.2506 0.03393 0.02494 -0.0537 0.0156 1.0000
9.000 1.2499 0.03661 0.02777 -0.0531 0.0150 1.0000
9.250 1.2474 0.03956 0.03086 -0.0526 0.0144 1.0000
9.500 1.2433 0.04273 0.03418 -0.0521 0.0140 1.0000
9.750 1.2378 0.04612 0.03770 -0.0517 0.0136 1.0000
10.000 1.2314 0.04963 0.04137 -0.0513 0.0133 1.0000
10.250 1.2247 0.05322 0.04507 -0.0510 0.0128 1.0000
10.500 1.2181 0.05683 0.04877 -0.0507 0.0123 1.0000
10.750 1.2118 0.06054 0.05256 -0.0505 0.0117 1.0000
11.000 1.2048 0.06437 0.05646 -0.0504 0.0111 1.0000
11.250 1.1976 0.06817 0.06031 -0.0501 0.0106 1.0000
11.500 1.1927 0.07143 0.06359 -0.0493 0.0103 1.0000
11.750 1.1942 0.07346 0.06559 -0.0477 0.0100 1.0000
12.000 1.2021 0.07511 0.06729 -0.0466 0.0097 1.0000
12.250 1.2122 0.07631 0.06852 -0.0452 0.0095 1.0000
12.500 1.2255 0.07692 0.06916 -0.0431 0.0093 1.0000
12.750 1.2397 0.07756 0.06990 -0.0412 0.0090 1.0000
13.000 1.2512 0.07890 0.07134 -0.0400 0.0083 1.0000
13.250 1.2613 0.08045 0.07297 -0.0391 0.0076 1.0000
13.500 1.2737 0.08160 0.07419 -0.0377 0.0072 1.0000
13.750 1.2885 0.08248 0.07515 -0.0357 0.0070 1.0000
14.000 1.3033 0.08358 0.07634 -0.0338 0.0068 1.0000
14.250 1.3162 0.08519 0.07809 -0.0321 0.0067 1.0000
14.500 1.3267 0.08735 0.08041 -0.0307 0.0066 1.0000
14.750 1.3335 0.09012 0.08337 -0.0298 0.0066 1.0000
15.000 1.3360 0.09343 0.08694 -0.0293 0.0066 1.0000
15.250 1.3337 0.09734 0.09109 -0.0293 0.0067 1.0000
15.500 1.3257 0.10211 0.09615 -0.0300 0.0069 1.0000
15.750 1.3163 0.10724 0.10157 -0.0309 0.0070 1.0000
16.000 1.3055 0.11265 0.10724 -0.0322 0.0072 1.0000
16.250 1.2938 0.11829 0.11312 -0.0340 0.0074 1.0000
16.500 1.2816 0.12418 0.11924 -0.0361 0.0076 1.0000
16.750 1.2692 0.13030 0.12555 -0.0386 0.0078 1.0000
17.000 1.2564 0.13664 0.13209 -0.0416 0.0079 1.0000
17.250 1.2435 0.14323 0.13886 -0.0449 0.0080 1.0000
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