YS-915 (ys915-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: YS-915 (ys915-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.13 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ys915-il-1000000-n5.txt Download as CSV file: xf-ys915-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4006 0.04795 0.04578 -0.1053 0.9274 0.0032
-8.500 -0.4130 0.04579 0.04346 -0.1026 0.9183 0.0032
-8.250 -0.4245 0.04279 0.04030 -0.1001 0.9124 0.0032
-8.000 -0.4284 0.03985 0.03718 -0.0980 0.9080 0.0032
-7.750 -0.4287 0.03684 0.03396 -0.0959 0.9047 0.0032
-7.500 -0.4255 0.03389 0.03080 -0.0938 0.9021 0.0032
-7.250 -0.4395 0.02764 0.02409 -0.0896 0.8985 0.0026
-7.000 -0.4320 0.02405 0.02013 -0.0868 0.8963 0.0023
-6.750 -0.4180 0.02126 0.01702 -0.0847 0.8946 0.0022
-6.500 -0.4029 0.01808 0.01346 -0.0823 0.8932 0.0019
-6.250 -0.3833 0.01589 0.01099 -0.0807 0.8920 0.0017
-6.000 -0.3641 0.01363 0.00846 -0.0788 0.8908 0.0016
-5.750 -0.3448 0.01212 0.00676 -0.0771 0.8897 0.0015
-5.500 -0.3245 0.01106 0.00554 -0.0756 0.8884 0.0014
-5.250 -0.3028 0.01026 0.00460 -0.0745 0.8874 0.0014
-5.000 -0.2797 0.00962 0.00378 -0.0736 0.8864 0.0014
-4.750 -0.2550 0.00918 0.00323 -0.0730 0.8855 0.0015
-4.500 -0.2295 0.00885 0.00281 -0.0727 0.8847 0.0017
-4.250 -0.2032 0.00861 0.00251 -0.0725 0.8840 0.0021
-4.000 -0.1766 0.00842 0.00229 -0.0724 0.8832 0.0030
-3.750 -0.1501 0.00824 0.00211 -0.0723 0.8825 0.0079
-3.500 -0.1265 0.00768 0.00184 -0.0718 0.8816 0.0796
-3.250 -0.1072 0.00668 0.00151 -0.0707 0.8805 0.2606
-3.000 -0.0810 0.00648 0.00139 -0.0707 0.8798 0.3065
-2.750 -0.0546 0.00630 0.00134 -0.0706 0.8792 0.3473
-2.500 -0.0274 0.00621 0.00129 -0.0707 0.8784 0.3677
-2.250 -0.0001 0.00614 0.00125 -0.0707 0.8776 0.3814
-2.000 0.0271 0.00608 0.00122 -0.0708 0.8768 0.3928
-1.750 0.0544 0.00603 0.00119 -0.0708 0.8759 0.4027
-1.500 0.0818 0.00598 0.00116 -0.0709 0.8750 0.4122
-1.250 0.1092 0.00594 0.00114 -0.0710 0.8739 0.4217
-1.000 0.1365 0.00589 0.00113 -0.0710 0.8726 0.4317
-0.750 0.1638 0.00584 0.00112 -0.0711 0.8710 0.4435
-0.500 0.1912 0.00578 0.00111 -0.0711 0.8691 0.4574
-0.250 0.2186 0.00571 0.00109 -0.0711 0.8666 0.4717
0.000 0.2455 0.00565 0.00108 -0.0710 0.8633 0.4869
0.500 0.2984 0.00547 0.00103 -0.0706 0.8539 0.5223
0.750 0.3246 0.00539 0.00104 -0.0703 0.8487 0.5432
1.000 0.3504 0.00528 0.00103 -0.0699 0.8419 0.5673
1.250 0.3758 0.00518 0.00107 -0.0694 0.8334 0.5950
1.500 0.4004 0.00506 0.00105 -0.0687 0.8183 0.6239
1.750 0.4089 0.00539 0.00095 -0.0643 0.6854 0.6524
2.000 0.4061 0.00646 0.00131 -0.0579 0.4931 0.6801
2.250 0.4148 0.00722 0.00159 -0.0543 0.3460 0.7143
2.500 0.4293 0.00771 0.00182 -0.0518 0.2433 0.7545
2.750 0.4430 0.00823 0.00209 -0.0492 0.1317 0.8022
3.000 0.4592 0.00855 0.00234 -0.0469 0.0605 0.8620
3.250 0.4950 0.00885 0.00275 -0.0488 0.0245 0.9386
3.500 0.5458 0.00924 0.00313 -0.0543 0.0131 0.9677
3.750 0.5710 0.00959 0.00347 -0.0539 0.0051 0.9806
4.000 0.6008 0.00999 0.00394 -0.0545 0.0039 0.9862
4.250 0.6285 0.01042 0.00443 -0.0546 0.0032 0.9910
4.500 0.6556 0.01102 0.00508 -0.0547 0.0021 0.9945
4.750 0.6851 0.01180 0.00597 -0.0554 0.0019 0.9973
5.000 0.7160 0.01229 0.00650 -0.0564 0.0018 0.9994
5.250 0.7411 0.01255 0.00682 -0.0561 0.0016 1.0000
5.500 0.7615 0.01282 0.00712 -0.0547 0.0013 1.0000
5.750 0.7795 0.01344 0.00782 -0.0528 0.0012 1.0000
6.000 0.7975 0.01424 0.00872 -0.0508 0.0010 1.0000
6.250 0.8166 0.01506 0.00964 -0.0491 0.0009 1.0000
6.500 0.8361 0.01633 0.01108 -0.0474 0.0007 1.0000
6.750 0.8565 0.01821 0.01321 -0.0458 0.0007 1.0000
7.000 0.8733 0.02268 0.01825 -0.0429 0.0007 1.0000
7.250 0.8664 0.03259 0.02903 -0.0339 0.0008 1.0000
7.500 0.8623 0.03826 0.03510 -0.0274 0.0009 1.0000
7.750 0.8596 0.04277 0.03990 -0.0221 0.0010 1.0000
8.000 0.8555 0.04706 0.04443 -0.0171 0.0010 1.0000
8.250 0.8508 0.05101 0.04858 -0.0127 0.0010 1.0000
8.500 0.8429 0.05494 0.05269 -0.0084 0.0011 1.0000
8.750 0.8328 0.05872 0.05662 -0.0043 0.0011 1.0000
9.000 0.8189 0.06187 0.05989 0.0001 0.0011 1.0000
9.250 0.7997 0.06506 0.06317 0.0045 0.0012 1.0000
9.500 0.7845 0.06817 0.06637 0.0071 0.0012 1.0000
9.750 0.7658 0.07211 0.07039 0.0086 0.0012 1.0000
10.000 0.7451 0.07701 0.07538 0.0083 0.0012 1.0000
10.250 0.7279 0.08274 0.08117 0.0055 0.0012 1.0000
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Polar data table (+)
Polar graphs
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