YS-915 (ys915-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: YS-915 (ys915-il) Reynolds number: 500,000 Max Cl/Cd: 91.86 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ys915-il-500000.txt Download as CSV file: xf-ys915-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4690 0.08618 0.08399 -0.0516 0.9935 0.0122
-9.250 -0.4657 0.07931 0.07713 -0.0572 0.9911 0.0122
-9.000 -0.4644 0.07139 0.06915 -0.0656 0.9883 0.0122
-8.750 -0.4671 0.06369 0.06135 -0.0766 0.9852 0.0121
-8.500 -0.4697 0.05880 0.05630 -0.0830 0.9821 0.0121
-8.250 -0.4784 0.05564 0.05300 -0.0826 0.9758 0.0122
-8.000 -0.4755 0.05150 0.04864 -0.0846 0.9727 0.0122
-7.750 -0.4671 0.04751 0.04437 -0.0862 0.9708 0.0122
-7.500 -0.4659 0.04486 0.04151 -0.0844 0.9671 0.0123
-7.250 -0.4654 0.04217 0.03860 -0.0817 0.9631 0.0123
-7.000 -0.4639 0.03716 0.03321 -0.0803 0.9604 0.0125
-5.750 -0.4128 0.02151 0.01606 -0.0677 0.9490 0.0094
-5.500 -0.3912 0.01870 0.01289 -0.0659 0.9479 0.0082
-5.250 -0.3669 0.01702 0.01103 -0.0650 0.9469 0.0082
-5.000 -0.3429 0.01601 0.00991 -0.0643 0.9461 0.0093
-4.750 -0.3162 0.01568 0.00953 -0.0643 0.9454 0.0114
-4.500 -0.2891 0.01509 0.00885 -0.0643 0.9447 0.0121
-4.250 -0.2796 0.01439 0.00806 -0.0606 0.9420 0.0121
-4.000 -0.2737 0.01389 0.00741 -0.0561 0.9383 0.0122
-3.750 -0.2546 0.01308 0.00639 -0.0543 0.9365 0.0139
-3.500 -0.2360 0.01157 0.00549 -0.0528 0.9349 0.1843
-3.250 -0.2127 0.01087 0.00542 -0.0526 0.9338 0.3547
-3.000 -0.1842 0.01070 0.00541 -0.0531 0.9329 0.4121
-2.750 -0.1534 0.01061 0.00536 -0.0539 0.9322 0.4404
-2.500 -0.1224 0.01053 0.00533 -0.0548 0.9316 0.4680
-2.250 -0.1108 0.01063 0.00542 -0.0516 0.9279 0.4843
-2.000 -0.0926 0.01064 0.00547 -0.0497 0.9247 0.5017
-1.750 -0.0658 0.01057 0.00545 -0.0497 0.9229 0.5234
-1.500 -0.0365 0.01047 0.00543 -0.0502 0.9215 0.5489
-1.250 -0.0058 0.01034 0.00540 -0.0511 0.9204 0.5807
-1.000 0.0263 0.01018 0.00535 -0.0521 0.9195 0.6193
-0.750 0.0590 0.00999 0.00534 -0.0533 0.9188 0.6640
-0.500 0.0707 0.01001 0.00552 -0.0499 0.9140 0.7097
-0.250 0.0908 0.00986 0.00561 -0.0483 0.9104 0.7694
0.000 0.1211 0.00959 0.00563 -0.0486 0.9088 0.8470
0.500 0.2755 0.00911 0.00544 -0.0702 0.9177 0.9434
0.750 0.3102 0.00927 0.00564 -0.0718 0.9132 0.9651
1.000 0.3542 0.00908 0.00552 -0.0752 0.9109 0.9764
1.250 0.4009 0.00872 0.00520 -0.0789 0.9084 0.9826
1.500 0.4537 0.00803 0.00456 -0.0835 0.9047 0.9834
1.750 0.4963 0.00724 0.00379 -0.0856 0.8894 0.9865
2.000 0.5323 0.00651 0.00305 -0.0861 0.8584 0.9921
2.250 0.5705 0.00625 0.00283 -0.0880 0.8299 0.9974
2.500 0.5879 0.00640 0.00241 -0.0852 0.6780 1.0000
2.750 0.5769 0.00768 0.00278 -0.0772 0.4854 1.0000
3.000 0.5625 0.00956 0.00331 -0.0692 0.1951 1.0000
3.250 0.5659 0.01090 0.00386 -0.0647 0.0292 1.0000
3.500 0.5816 0.01154 0.00454 -0.0620 0.0131 1.0000
3.750 0.5966 0.01228 0.00537 -0.0591 0.0108 1.0000
4.000 0.6061 0.01369 0.00692 -0.0551 0.0097 1.0000
4.250 0.6236 0.01471 0.00801 -0.0528 0.0097 1.0000
4.500 0.6452 0.01587 0.00928 -0.0513 0.0100 1.0000
4.750 0.6693 0.01676 0.01026 -0.0503 0.0107 1.0000
5.750 0.7703 0.02732 0.02197 -0.0445 0.0153 1.0000
6.000 0.7864 0.02909 0.02398 -0.0418 0.0133 1.0000
6.250 0.7997 0.03092 0.02601 -0.0391 0.0120 1.0000
|
Polar data table (+)
Polar graphs
<< Back to YS-915 (ys915-il)