YS-915 (ys915-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: YS-915 (ys915-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.2 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ys915-il-1000000.txt Download as CSV file: xf-ys915-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3330 0.08276 0.08118 -0.0635 0.9866 0.0056
-10.250 -0.3332 0.07715 0.07558 -0.0662 0.9855 0.0056
-10.000 -0.3331 0.07141 0.06984 -0.0691 0.9846 0.0056
-9.750 -0.3360 0.06423 0.06266 -0.0727 0.9837 0.0056
-9.500 -0.3386 0.05597 0.05438 -0.0778 0.9829 0.0056
-9.250 -0.3488 0.04798 0.04634 -0.0840 0.9785 0.0056
-9.000 -0.3587 0.04111 0.03936 -0.0918 0.9738 0.0056
-8.750 -0.3704 0.03583 0.03394 -0.0986 0.9672 0.0056
-8.500 -0.3832 0.03273 0.03068 -0.0997 0.9575 0.0056
-8.250 -0.3969 0.03036 0.02817 -0.0970 0.9489 0.0056
-8.000 -0.4036 0.02733 0.02494 -0.0952 0.9436 0.0056
-7.750 -0.4065 0.02424 0.02166 -0.0932 0.9393 0.0056
-7.500 -0.4046 0.02134 0.01855 -0.0912 0.9359 0.0056
-7.250 -0.4002 0.01841 0.01537 -0.0892 0.9328 0.0056
-6.250 -0.3702 0.01739 0.01279 -0.0848 0.9269 0.0047
-6.000 -0.3523 0.01432 0.00937 -0.0826 0.9252 0.0040
-5.750 -0.3319 0.01274 0.00762 -0.0810 0.9238 0.0040
-5.500 -0.3095 0.01191 0.00670 -0.0801 0.9226 0.0047
-5.250 -0.2861 0.01132 0.00603 -0.0793 0.9215 0.0052
-5.000 -0.2593 0.01121 0.00589 -0.0793 0.9207 0.0056
-4.750 -0.2410 0.01003 0.00453 -0.0775 0.9192 0.0062
-4.500 -0.2187 0.00936 0.00370 -0.0765 0.9180 0.0078
-4.250 -0.1937 0.00900 0.00323 -0.0760 0.9171 0.0081
-4.000 -0.1682 0.00872 0.00286 -0.0756 0.9163 0.0096
-3.750 -0.1510 0.00755 0.00233 -0.0740 0.9148 0.1791
-3.500 -0.1296 0.00694 0.00219 -0.0732 0.9136 0.3059
-3.250 -0.1041 0.00677 0.00214 -0.0730 0.9126 0.3515
-3.000 -0.0779 0.00665 0.00210 -0.0728 0.9115 0.3805
-2.500 -0.0247 0.00650 0.00202 -0.0727 0.9097 0.4228
-2.250 0.0023 0.00643 0.00199 -0.0727 0.9087 0.4392
-2.000 0.0295 0.00637 0.00197 -0.0728 0.9077 0.4562
-1.750 0.0567 0.00631 0.00195 -0.0728 0.9067 0.4733
-1.500 0.0840 0.00626 0.00193 -0.0729 0.9057 0.4917
-1.000 0.1369 0.00617 0.00198 -0.0726 0.9030 0.5360
-0.750 0.1623 0.00609 0.00199 -0.0723 0.9011 0.5623
-0.500 0.1880 0.00599 0.00200 -0.0719 0.8988 0.5912
-0.250 0.2140 0.00586 0.00198 -0.0716 0.8962 0.6233
0.000 0.2410 0.00569 0.00193 -0.0715 0.8935 0.6602
0.250 0.2672 0.00555 0.00192 -0.0711 0.8903 0.7013
0.500 0.2904 0.00536 0.00191 -0.0701 0.8859 0.7465
0.750 0.3154 0.00515 0.00186 -0.0694 0.8818 0.7951
1.000 0.3416 0.00495 0.00185 -0.0688 0.8776 0.8464
1.250 0.3672 0.00474 0.00185 -0.0681 0.8714 0.8995
1.500 0.4087 0.00459 0.00177 -0.0709 0.8634 0.9341
1.750 0.4464 0.00437 0.00151 -0.0726 0.8357 0.9514
2.000 0.4772 0.00437 0.00153 -0.0732 0.8124 0.9647
2.250 0.4941 0.00493 0.00157 -0.0706 0.6725 0.9771
2.500 0.5064 0.00632 0.00204 -0.0679 0.4536 0.9868
2.750 0.5210 0.00813 0.00259 -0.0662 0.1530 0.9943
3.000 0.5530 0.00904 0.00296 -0.0679 0.0271 0.9974
3.250 0.5883 0.00954 0.00344 -0.0697 0.0077 0.9998
3.500 0.6077 0.00997 0.00395 -0.0678 0.0061 1.0000
3.750 0.6251 0.01045 0.00452 -0.0655 0.0060 1.0000
4.000 0.6400 0.01118 0.00536 -0.0626 0.0059 1.0000
4.250 0.6540 0.01211 0.00644 -0.0595 0.0062 1.0000
4.500 0.6702 0.01363 0.00808 -0.0567 0.0068 1.0000
4.750 0.6935 0.01513 0.00969 -0.0555 0.0070 1.0000
5.000 0.7165 0.01606 0.01070 -0.0544 0.0064 1.0000
5.250 0.7412 0.01774 0.01253 -0.0534 0.0063 1.0000
5.500 0.7651 0.02064 0.01573 -0.0517 0.0070 1.0000
5.750 0.7843 0.02142 0.01661 -0.0501 0.0059 1.0000
6.000 0.8003 0.02092 0.01605 -0.0487 0.0048 1.0000
7.000 0.8095 0.03834 0.03503 -0.0288 0.0041 1.0000
7.250 0.8113 0.04154 0.03846 -0.0245 0.0041 1.0000
7.500 0.8114 0.04487 0.04201 -0.0202 0.0041 1.0000
7.750 0.8099 0.04829 0.04563 -0.0161 0.0041 1.0000
8.000 0.8069 0.05166 0.04917 -0.0121 0.0041 1.0000
8.250 0.8011 0.05517 0.05284 -0.0081 0.0041 1.0000
8.500 0.7934 0.05847 0.05629 -0.0043 0.0041 1.0000
8.750 0.7796 0.06127 0.05919 0.0003 0.0041 1.0000
9.000 0.7650 0.06424 0.06226 0.0041 0.0041 1.0000
9.250 0.7500 0.06747 0.06558 0.0067 0.0041 1.0000
9.500 0.7336 0.07134 0.06955 0.0082 0.0041 1.0000
9.750 0.7182 0.07564 0.07393 0.0082 0.0041 1.0000
10.000 0.7036 0.08084 0.07920 0.0064 0.0041 1.0000
|
Polar data table (+)
Polar graphs
<< Back to YS-915 (ys915-il)