YS-900 (ys900-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: YS-900 (ys900-il) Reynolds number: 1,000,000 Max Cl/Cd: 48.95 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ys900-il-1000000-n5.txt Download as CSV file: xf-ys900-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: YS-900
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4855 0.04559 0.04314 -0.0725 0.9618 0.0021
-7.500 -0.4950 0.04175 0.03909 -0.0677 0.9598 0.0022
-7.250 -0.4958 0.03878 0.03595 -0.0638 0.9583 0.0024
-7.000 -0.4893 0.03617 0.03315 -0.0604 0.9572 0.0024
-6.750 -0.4844 0.03368 0.03046 -0.0568 0.9561 0.0025
-6.500 -0.4781 0.03157 0.02818 -0.0531 0.9550 0.0026
-6.250 -0.4711 0.02977 0.02620 -0.0495 0.9537 0.0028
-6.000 -0.4619 0.02784 0.02405 -0.0459 0.9525 0.0029
-5.750 -0.4516 0.02611 0.02214 -0.0425 0.9512 0.0031
-5.500 -0.4390 0.02438 0.02021 -0.0394 0.9500 0.0034
-2.250 -0.1302 0.00939 0.00339 -0.0264 0.9437 0.0046
-2.000 -0.1049 0.00920 0.00310 -0.0260 0.9432 0.0037
-1.750 -0.1036 0.00934 0.00320 -0.0200 0.9393 0.0034
-1.500 -0.0856 0.00930 0.00313 -0.0180 0.9372 0.0032
-1.250 -0.0623 0.00921 0.00298 -0.0171 0.9359 0.0033
-1.000 -0.0368 0.00912 0.00294 -0.0169 0.9349 0.0069
-0.750 -0.0467 0.00695 0.00258 -0.0095 0.9322 0.5682
-0.500 -0.0776 0.00617 0.00246 0.0040 0.9244 0.7420
-0.250 -0.0396 0.00692 0.00387 0.0029 0.9246 0.9223
0.000 0.0000 0.00697 0.00392 0.0000 0.9237 0.9237
0.250 0.0396 0.00691 0.00386 -0.0029 0.9223 0.9246
0.500 0.0802 0.00613 0.00245 -0.0046 0.7504 0.9241
0.750 0.0484 0.00690 0.00257 0.0091 0.5804 0.9321
1.000 0.0400 0.00888 0.00292 0.0162 0.0934 0.9347
1.250 0.0624 0.00921 0.00298 0.0171 0.0033 0.9359
1.500 0.0856 0.00929 0.00312 0.0180 0.0031 0.9372
1.750 0.1035 0.00934 0.00320 0.0201 0.0034 0.9393
2.000 0.1049 0.00920 0.00310 0.0259 0.0036 0.9432
2.250 0.1302 0.00939 0.00338 0.0264 0.0045 0.9437
4.500 0.3500 0.00715 0.00250 0.0313 0.0057 0.9464
4.750 0.3726 0.00770 0.00318 0.0325 0.0049 0.9470
5.000 0.3933 0.00865 0.00431 0.0341 0.0041 0.9477
5.250 0.4101 0.00996 0.00583 0.0364 0.0038 0.9486
5.500 0.4241 0.01141 0.00749 0.0392 0.0034 0.9495
5.750 0.4361 0.01305 0.00933 0.0423 0.0033 0.9506
6.000 0.4459 0.01481 0.01129 0.0456 0.0030 0.9521
6.250 0.4539 0.01678 0.01345 0.0491 0.0029 0.9534
6.500 0.4611 0.01881 0.01569 0.0525 0.0028 0.9546
6.750 0.4661 0.02101 0.01805 0.0560 0.0026 0.9557
7.000 0.4708 0.02350 0.02072 0.0594 0.0026 0.9567
7.250 0.4735 0.02619 0.02358 0.0628 0.0025 0.9577
7.500 0.4728 0.02910 0.02664 0.0664 0.0024 0.9590
7.750 0.4712 0.03210 0.02979 0.0700 0.0023 0.9606
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Polar data table (+)
Polar graphs
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