MB253515 15.0% smoothed (mb253515sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MB253515 15.0% smoothed (mb253515sm-il) Reynolds number: 50,000 Max Cl/Cd: 7.54 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mb253515sm-il-50000.txt Download as CSV file: xf-mb253515sm-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MB253515 15.0% smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3355 0.10977 0.10310 -0.0276 1.0000 0.3539
-9.500 -0.3174 0.10514 0.09846 -0.0273 1.0000 0.3597
-9.250 -0.3345 0.10370 0.09718 -0.0263 1.0000 0.3706
-9.000 -0.3253 0.09970 0.09321 -0.0261 1.0000 0.3726
-8.750 -0.3277 0.09661 0.09021 -0.0257 1.0000 0.3733
-8.500 -0.4835 0.08070 0.07492 -0.0430 1.0000 0.1944
-8.250 -0.5297 0.07940 0.07381 -0.0378 1.0000 0.1935
-8.000 -0.5770 0.07768 0.07220 -0.0330 1.0000 0.1920
-7.750 -0.6079 0.07436 0.06887 -0.0300 1.0000 0.1812
-7.500 -0.6662 0.07102 0.06531 -0.0258 1.0000 0.1752
-7.250 -0.6760 0.06654 0.06069 -0.0236 1.0000 0.1632
-7.000 -0.6890 0.06263 0.05649 -0.0209 1.0000 0.1538
-6.750 -0.7076 0.05842 0.05159 -0.0176 1.0000 0.1437
-6.500 -0.7035 0.05495 0.04796 -0.0154 1.0000 0.1390
-6.250 -0.7116 0.05163 0.04354 -0.0115 1.0000 0.1309
-6.000 -0.7000 0.04864 0.04035 -0.0098 1.0000 0.1293
-5.750 -0.6902 0.04618 0.03749 -0.0077 1.0000 0.1291
-5.500 -0.6779 0.04394 0.03484 -0.0057 1.0000 0.1293
-5.250 -0.6630 0.04184 0.03237 -0.0040 1.0000 0.1291
-5.000 -0.6459 0.03985 0.02999 -0.0024 1.0000 0.1289
-4.750 -0.6280 0.03823 0.02800 -0.0008 1.0000 0.1297
-4.500 -0.6093 0.03664 0.02624 0.0003 1.0000 0.1329
-4.250 -0.5895 0.03537 0.02490 0.0013 1.0000 0.1370
-4.000 -0.5683 0.03429 0.02367 0.0024 1.0000 0.1404
-3.750 -0.5467 0.03345 0.02263 0.0035 1.0000 0.1442
-3.500 -0.5269 0.03258 0.02188 0.0046 1.0000 0.1515
-3.250 -0.5082 0.03194 0.02120 0.0059 1.0000 0.1616
-3.000 -0.4902 0.03133 0.02057 0.0072 1.0000 0.1734
-2.750 -0.4728 0.03059 0.01997 0.0083 1.0000 0.1918
-2.500 -0.4493 0.02860 0.01972 0.0080 0.9943 0.3959
-2.250 -0.0897 0.03751 0.02903 -0.0342 0.9845 1.0000
-2.000 -0.0700 0.03719 0.02850 -0.0364 0.9753 1.0000
-1.750 -0.0489 0.03707 0.02817 -0.0386 0.9661 1.0000
-1.500 -0.0266 0.03709 0.02797 -0.0407 0.9568 1.0000
-1.250 -0.0152 0.03705 0.02779 -0.0406 0.9472 1.0000
-1.000 0.0050 0.03725 0.02782 -0.0418 0.9377 1.0000
-0.750 0.0232 0.03747 0.02786 -0.0424 0.9276 1.0000
-0.500 0.0321 0.03765 0.02792 -0.0413 0.9172 1.0000
-0.250 0.0513 0.03803 0.02815 -0.0417 0.9069 1.0000
0.000 0.0739 0.03847 0.02846 -0.0425 0.8960 1.0000
0.250 0.0776 0.03877 0.02866 -0.0400 0.8848 1.0000
0.500 0.0918 0.03926 0.02902 -0.0391 0.8737 1.0000
0.750 0.1168 0.03989 0.02952 -0.0399 0.8623 1.0000
1.000 0.1380 0.04048 0.03000 -0.0399 0.8504 1.0000
1.250 0.1452 0.04105 0.03048 -0.0377 0.8383 1.0000
1.500 0.1607 0.04175 0.03107 -0.0367 0.8262 1.0000
1.750 0.1831 0.04251 0.03174 -0.0367 0.8140 1.0000
2.000 0.2130 0.04329 0.03244 -0.0378 0.8017 1.0000
2.250 0.2322 0.04407 0.03315 -0.0372 0.7892 1.0000
2.500 0.2438 0.04489 0.03391 -0.0356 0.7759 1.0000
2.750 0.2574 0.04581 0.03477 -0.0342 0.7632 1.0000
3.000 0.2755 0.04673 0.03565 -0.0335 0.7505 1.0000
3.250 0.2985 0.04765 0.03654 -0.0334 0.7383 1.0000
3.500 0.3345 0.04842 0.03730 -0.0348 0.7270 1.0000
3.750 0.3369 0.04961 0.03845 -0.0323 0.7142 1.0000
4.000 0.3453 0.05082 0.03964 -0.0305 0.7018 1.0000
4.250 0.3599 0.05203 0.04085 -0.0295 0.6905 1.0000
4.500 0.3906 0.05294 0.04177 -0.0302 0.6801 1.0000
4.750 0.3974 0.05436 0.04318 -0.0286 0.6689 1.0000
5.000 0.4004 0.05602 0.04484 -0.0268 0.6586 1.0000
5.250 0.4257 0.05715 0.04602 -0.0270 0.6491 1.0000
5.500 0.4315 0.05884 0.04771 -0.0256 0.6395 1.0000
5.750 0.4371 0.06067 0.04955 -0.0244 0.6309 1.0000
6.000 0.4658 0.06180 0.05074 -0.0248 0.6221 1.0000
6.250 0.4546 0.06435 0.05329 -0.0228 0.6151 1.0000
6.500 0.4826 0.06565 0.05467 -0.0233 0.6072 1.0000
6.750 0.4727 0.06831 0.05734 -0.0216 0.6014 1.0000
7.000 0.4778 0.07056 0.05964 -0.0210 0.5961 1.0000
7.250 0.4983 0.07242 0.06156 -0.0212 0.5896 1.0000
7.500 0.4905 0.07531 0.06448 -0.0203 0.5874 1.0000
7.750 0.4899 0.07821 0.06742 -0.0200 0.5872 1.0000
8.000 0.4962 0.08123 0.07054 -0.0203 0.5894 1.0000
8.250 0.4268 0.08958 0.07884 -0.0218 0.6808 1.0000
8.500 0.4227 0.09069 0.07999 -0.0202 0.6726 1.0000
8.750 0.4543 0.09444 0.08384 -0.0225 0.6662 1.0000
9.000 0.4458 0.09520 0.08465 -0.0205 0.6569 1.0000
9.250 0.4756 0.09901 0.08860 -0.0225 0.6510 1.0000
9.500 0.4667 0.09983 0.08946 -0.0207 0.6424 1.0000
9.750 0.4980 0.10390 0.09366 -0.0228 0.6361 1.0000
10.000 0.4900 0.10463 0.09444 -0.0211 0.6260 1.0000
10.250 0.5169 0.10865 0.09862 -0.0229 0.6209 1.0000
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Polar data table (+)
Polar graphs
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