S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Reynolds number: 50,000 Max Cl/Cd: 27.68 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4095-il-50000.txt Download as CSV file: xf-s4095-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S4095 (designed for the E-flite UMX ASK-21 scale
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.6145 0.11945 0.11308 0.0220 1.0007 0.2200
-7.750 -0.5761 0.11212 0.10569 0.0265 1.0007 0.2304
-7.500 -0.6095 0.11184 0.10552 0.0166 1.0007 0.2393
-7.250 -0.5733 0.10461 0.09830 0.0251 1.0007 0.2490
-7.000 -0.5825 0.10135 0.09511 0.0195 1.0007 0.2611
-6.750 -0.5663 0.09718 0.09094 0.0215 1.0007 0.2752
-6.500 -0.5567 0.09274 0.08653 0.0214 1.0007 0.2877
-6.250 -0.5505 0.08881 0.08264 0.0194 1.0007 0.3056
-6.000 -0.5408 0.08497 0.07882 0.0185 1.0007 0.3263
-5.750 -0.5280 0.08118 0.07507 0.0199 1.0007 0.3501
-5.500 -0.5151 0.07775 0.07166 0.0218 1.0007 0.3793
-5.250 -0.5053 0.07424 0.06820 0.0236 1.0007 0.4156
-5.000 -0.4952 0.07110 0.06512 0.0263 1.0007 0.4578
-4.750 -0.4797 0.06758 0.06165 0.0303 1.0007 0.4912
-4.500 -0.3052 0.04008 0.03038 -0.0416 1.0007 0.1273
-4.250 -0.2695 0.03659 0.02626 -0.0434 1.0007 0.1282
-4.000 -0.2369 0.03382 0.02321 -0.0444 1.0007 0.1337
-3.750 -0.2031 0.03128 0.02017 -0.0451 1.0007 0.1404
-3.500 -0.1711 0.02919 0.01781 -0.0455 1.0007 0.1551
-3.250 -0.1416 0.02715 0.01593 -0.0456 1.0007 0.1805
-3.000 -0.1124 0.02530 0.01429 -0.0455 1.0007 0.2336
-2.750 -0.0832 0.02341 0.01276 -0.0453 1.0007 0.3234
-2.500 -0.0583 0.02082 0.01151 -0.0441 1.0007 0.5139
-2.250 -0.0402 0.01768 0.00961 -0.0391 1.0007 0.9993
-2.000 -0.0098 0.01773 0.00909 -0.0398 1.0007 0.9993
-1.750 0.0194 0.01782 0.00878 -0.0405 1.0007 0.9993
-1.500 0.0479 0.01797 0.00864 -0.0410 1.0007 0.9993
-1.250 0.0756 0.01819 0.00863 -0.0415 1.0007 0.9993
-1.000 0.1023 0.01852 0.00876 -0.0420 1.0007 0.9993
-0.750 0.1273 0.01901 0.00911 -0.0424 1.0007 0.9993
-0.500 0.1502 0.01972 0.00970 -0.0426 1.0007 0.9993
-0.250 0.1713 0.02068 0.01056 -0.0428 1.0007 0.9993
0.000 0.1912 0.02186 0.01164 -0.0433 1.0007 0.9993
0.250 0.2106 0.02321 0.01290 -0.0440 1.0007 0.9993
0.500 0.2293 0.02469 0.01431 -0.0449 1.0007 0.9993
0.750 0.2742 0.02533 0.01486 -0.0504 0.9904 0.9993
1.000 0.3441 0.02491 0.01436 -0.0597 0.9691 0.9993
1.250 0.4138 0.02432 0.01373 -0.0685 0.9474 0.9993
1.500 0.4741 0.02391 0.01331 -0.0748 0.9232 0.9993
1.750 0.5191 0.02392 0.01331 -0.0776 0.8957 0.9993
2.000 0.5506 0.02431 0.01370 -0.0775 0.8661 0.9993
2.250 0.5769 0.02487 0.01423 -0.0764 0.8373 0.9993
2.500 0.6012 0.02544 0.01477 -0.0746 0.8105 0.9993
2.750 0.6244 0.02602 0.01530 -0.0724 0.7852 0.9993
3.000 0.6480 0.02669 0.01601 -0.0710 0.7578 0.9993
3.250 0.6716 0.02731 0.01662 -0.0693 0.7321 0.9993
3.500 0.6952 0.02791 0.01721 -0.0676 0.7072 0.9993
3.750 0.7191 0.02851 0.01778 -0.0659 0.6831 0.9993
4.000 0.7432 0.02910 0.01834 -0.0642 0.6594 0.9993
4.250 0.7676 0.02969 0.01894 -0.0626 0.6360 0.9993
4.500 0.7927 0.03035 0.01962 -0.0615 0.6116 0.9993
4.750 0.8183 0.03107 0.02039 -0.0607 0.5864 0.9993
5.000 0.8438 0.03175 0.02111 -0.0598 0.5619 0.9993
5.250 0.8693 0.03241 0.02184 -0.0588 0.5381 0.9993
5.500 0.8949 0.03306 0.02250 -0.0577 0.5148 0.9993
5.750 0.9205 0.03370 0.02314 -0.0567 0.4921 0.9993
6.000 0.9462 0.03435 0.02380 -0.0556 0.4698 0.9993
6.250 0.9720 0.03511 0.02456 -0.0548 0.4475 0.9993
6.500 0.9979 0.03615 0.02577 -0.0545 0.4235 0.9993
6.750 1.0235 0.03715 0.02686 -0.0539 0.4007 0.9993
7.000 1.0490 0.03817 0.02798 -0.0533 0.3789 0.9993
7.250 1.0744 0.03924 0.02911 -0.0526 0.3578 0.9993
7.500 1.0996 0.04041 0.03032 -0.0520 0.3374 0.9993
7.750 1.1246 0.04169 0.03169 -0.0514 0.3179 0.9993
8.000 1.1492 0.04313 0.03320 -0.0509 0.2990 0.9993
8.250 1.1734 0.04475 0.03492 -0.0504 0.2810 0.9993
8.500 1.1968 0.04657 0.03690 -0.0499 0.2638 0.9993
8.750 1.2190 0.04864 0.03919 -0.0495 0.2475 0.9993
9.000 1.2394 0.05110 0.04193 -0.0491 0.2325 0.9993
9.250 1.2567 0.05413 0.04536 -0.0487 0.2188 0.9993
9.500 1.2696 0.05789 0.04956 -0.0482 0.2071 0.9993
9.750 1.2840 0.06119 0.05312 -0.0475 0.1964 0.9993
10.000 1.3035 0.06356 0.05554 -0.0466 0.1855 0.9993
10.250 1.2870 0.07103 0.06378 -0.0461 0.1812 0.9993
10.500 0.9446 0.13957 0.13204 -0.0892 0.3243 0.9993
|
Polar data table (+)
Polar graphs
<< Back to S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il)