YS-915 (ys915-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: YS-915 (ys915-il) Reynolds number: 500,000 Max Cl/Cd: 73.7 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ys915-il-500000-n5.txt Download as CSV file: xf-ys915-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: YS-915
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4454 0.04171 0.03853 -0.0979 0.9423 0.0063
-7.750 -0.4454 0.03813 0.03469 -0.0962 0.9371 0.0059
-7.500 -0.4433 0.03127 0.02725 -0.0924 0.9327 0.0033
-7.000 -0.4157 0.02713 0.02265 -0.0896 0.9278 0.0028
-6.750 -0.4046 0.02422 0.01939 -0.0874 0.9249 0.0027
-6.500 -0.3898 0.02147 0.01627 -0.0854 0.9227 0.0026
-6.250 -0.3712 0.01928 0.01376 -0.0838 0.9209 0.0025
-6.000 -0.3506 0.01737 0.01157 -0.0825 0.9193 0.0024
-5.750 -0.3289 0.01580 0.00978 -0.0814 0.9180 0.0023
-5.500 -0.3079 0.01447 0.00828 -0.0801 0.9167 0.0023
-5.250 -0.2884 0.01334 0.00701 -0.0785 0.9151 0.0023
-5.000 -0.2683 0.01245 0.00593 -0.0771 0.9135 0.0024
-4.750 -0.2470 0.01172 0.00506 -0.0758 0.9121 0.0024
-4.500 -0.2239 0.01117 0.00435 -0.0750 0.9108 0.0026
-4.250 -0.1995 0.01076 0.00381 -0.0744 0.9096 0.0029
-4.000 -0.1743 0.01041 0.00332 -0.0738 0.9083 0.0050
-3.750 -0.1526 0.00965 0.00293 -0.0730 0.9072 0.0871
-3.500 -0.1354 0.00845 0.00262 -0.0718 0.9060 0.3142
-3.250 -0.1093 0.00827 0.00253 -0.0717 0.9051 0.3542
-3.000 -0.0831 0.00812 0.00242 -0.0716 0.9043 0.3903
-2.750 -0.0577 0.00805 0.00237 -0.0713 0.9031 0.4075
-2.500 -0.0322 0.00800 0.00233 -0.0710 0.9018 0.4202
-2.250 -0.0065 0.00796 0.00230 -0.0707 0.9005 0.4313
-2.000 0.0195 0.00792 0.00228 -0.0705 0.8992 0.4425
-1.750 0.0457 0.00788 0.00226 -0.0703 0.8979 0.4539
-1.500 0.0722 0.00784 0.00222 -0.0702 0.8967 0.4667
-1.250 0.0988 0.00779 0.00221 -0.0701 0.8954 0.4818
-1.000 0.1258 0.00773 0.00220 -0.0701 0.8942 0.4983
-0.500 0.1806 0.00760 0.00221 -0.0702 0.8919 0.5363
-0.250 0.2066 0.00755 0.00224 -0.0700 0.8903 0.5585
0.000 0.2299 0.00750 0.00232 -0.0692 0.8875 0.5840
0.250 0.2545 0.00741 0.00236 -0.0686 0.8848 0.6134
0.500 0.2805 0.00728 0.00236 -0.0683 0.8819 0.6467
0.750 0.3084 0.00710 0.00233 -0.0683 0.8791 0.6825
1.000 0.3312 0.00696 0.00237 -0.0672 0.8741 0.7208
1.250 0.3558 0.00676 0.00235 -0.0663 0.8687 0.7636
1.500 0.3816 0.00653 0.00238 -0.0657 0.8630 0.8110
1.750 0.4079 0.00630 0.00236 -0.0650 0.8542 0.8645
2.000 0.4459 0.00605 0.00226 -0.0668 0.8319 0.9126
2.250 0.4670 0.00681 0.00199 -0.0647 0.5801 0.9432
2.500 0.4784 0.00827 0.00251 -0.0620 0.3637 0.9667
3.000 0.5201 0.01011 0.00334 -0.0604 0.0986 0.9898
3.250 0.5485 0.01086 0.00376 -0.0610 0.0255 0.9957
3.500 0.5829 0.01129 0.00419 -0.0628 0.0145 0.9998
3.750 0.6034 0.01159 0.00454 -0.0613 0.0095 1.0000
4.000 0.6170 0.01248 0.00556 -0.0582 0.0055 1.0000
4.250 0.6315 0.01334 0.00651 -0.0553 0.0052 1.0000
4.500 0.6490 0.01398 0.00723 -0.0532 0.0049 1.0000
4.750 0.6692 0.01435 0.00763 -0.0518 0.0041 1.0000
5.000 0.6902 0.01459 0.00788 -0.0506 0.0031 1.0000
5.250 0.7103 0.01498 0.00829 -0.0492 0.0026 1.0000
5.500 0.7276 0.01619 0.00969 -0.0472 0.0020 1.0000
5.750 0.7483 0.01760 0.01127 -0.0457 0.0018 1.0000
6.000 0.7706 0.01878 0.01262 -0.0445 0.0016 1.0000
6.250 0.7942 0.02117 0.01534 -0.0433 0.0014 1.0000
6.500 0.8144 0.02433 0.01893 -0.0412 0.0014 1.0000
6.750 0.8276 0.02865 0.02376 -0.0374 0.0014 1.0000
7.000 0.8361 0.03268 0.02819 -0.0333 0.0014 1.0000
7.250 0.8408 0.03678 0.03265 -0.0287 0.0014 1.0000
7.500 0.8421 0.04105 0.03725 -0.0240 0.0015 1.0000
7.750 0.8439 0.04457 0.04102 -0.0200 0.0015 1.0000
8.000 0.8403 0.04875 0.04546 -0.0155 0.0015 1.0000
8.250 0.8363 0.05241 0.04932 -0.0115 0.0015 1.0000
8.500 0.8281 0.05626 0.05336 -0.0074 0.0016 1.0000
8.750 0.8170 0.05982 0.05707 -0.0034 0.0016 1.0000
9.000 0.8006 0.06290 0.06028 0.0011 0.0016 1.0000
9.250 0.7863 0.06599 0.06347 0.0043 0.0016 1.0000
9.500 0.7673 0.06985 0.06743 0.0064 0.0016 1.0000
9.750 0.7473 0.07443 0.07210 0.0070 0.0017 1.0000
10.000 0.7319 0.07925 0.07700 0.0058 0.0017 1.0000
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Polar data table (+)
Polar graphs
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