S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Reynolds number: 200,000 Max Cl/Cd: 53.38 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4095-il-200000.txt Download as CSV file: xf-s4095-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6112 0.11907 0.11569 0.0269 1.0007 0.0432
-8.750 -0.6174 0.11366 0.11032 0.0222 1.0007 0.0446
-8.500 -0.6276 0.10795 0.10467 0.0177 1.0007 0.0450
-8.250 -0.6152 0.10531 0.10203 0.0199 1.0007 0.0458
-8.000 -0.6151 0.10148 0.09822 0.0185 1.0007 0.0468
-7.750 -0.6141 0.09591 0.09267 0.0126 1.0007 0.0485
-7.500 -0.6092 0.08817 0.08490 0.0029 1.0007 0.0497
-7.250 -0.5213 0.07931 0.07625 -0.0018 1.0007 0.0557
-7.000 -0.5819 0.07679 0.07339 -0.0078 1.0007 0.0546
-6.750 -0.5597 0.06976 0.06612 -0.0160 1.0007 0.0590
-6.500 -0.5431 0.06607 0.06243 -0.0166 1.0007 0.0601
-6.250 -0.5153 0.05900 0.05499 -0.0237 1.0007 0.0651
-6.000 -0.4875 0.05469 0.05038 -0.0273 1.0007 0.0704
-5.750 -0.4647 0.05108 0.04681 -0.0283 1.0007 0.0718
-5.500 -0.4342 0.04674 0.04214 -0.0316 1.0007 0.0780
-5.250 -0.3878 0.03421 0.02834 -0.0368 1.0007 0.0506
-5.000 -0.3469 0.02642 0.01928 -0.0386 1.0007 0.0383
-4.750 -0.3148 0.02437 0.01681 -0.0394 1.0007 0.0396
-4.500 -0.2832 0.02242 0.01454 -0.0399 1.0007 0.0397
-4.250 -0.2520 0.02082 0.01270 -0.0403 1.0007 0.0401
-4.000 -0.2216 0.01947 0.01128 -0.0407 1.0007 0.0412
-3.750 -0.1914 0.01845 0.01029 -0.0412 1.0007 0.0431
-3.500 -0.1611 0.01752 0.00937 -0.0416 1.0007 0.0459
-3.250 -0.1309 0.01682 0.00873 -0.0422 1.0007 0.0516
-3.000 -0.1002 0.01607 0.00806 -0.0429 1.0007 0.0603
-2.750 -0.0689 0.01507 0.00736 -0.0437 1.0007 0.1027
-2.500 -0.0384 0.01440 0.00707 -0.0447 1.0007 0.1758
-2.250 -0.0081 0.01378 0.00691 -0.0457 1.0007 0.2791
-2.000 0.0212 0.01284 0.00690 -0.0468 1.0007 0.4946
-1.750 0.0390 0.01171 0.00705 -0.0439 1.0007 0.8266
-1.500 0.0672 0.01087 0.00633 -0.0438 1.0007 0.9993
-1.250 0.1067 0.01130 0.00657 -0.0465 0.9749 0.9993
-1.000 0.1435 0.01153 0.00660 -0.0482 0.9305 0.9993
-0.750 0.1691 0.01175 0.00662 -0.0471 0.8881 0.9993
-0.500 0.1937 0.01195 0.00660 -0.0458 0.8534 0.9993
-0.250 0.2195 0.01214 0.00658 -0.0449 0.8242 0.9993
0.000 0.2467 0.01231 0.00654 -0.0445 0.7974 0.9993
0.250 0.2744 0.01248 0.00653 -0.0442 0.7732 0.9993
0.500 0.3026 0.01265 0.00653 -0.0441 0.7508 0.9993
0.750 0.3311 0.01282 0.00654 -0.0441 0.7295 0.9993
1.000 0.3597 0.01299 0.00656 -0.0441 0.7091 0.9993
1.250 0.3885 0.01316 0.00660 -0.0442 0.6895 0.9993
1.500 0.4174 0.01334 0.00664 -0.0444 0.6703 0.9993
1.750 0.4462 0.01352 0.00670 -0.0445 0.6516 0.9993
2.000 0.4751 0.01371 0.00677 -0.0447 0.6332 0.9993
2.250 0.5041 0.01390 0.00685 -0.0448 0.6145 0.9993
2.500 0.5332 0.01407 0.00694 -0.0451 0.5953 0.9993
2.750 0.5623 0.01425 0.00704 -0.0454 0.5761 0.9993
3.000 0.5914 0.01444 0.00716 -0.0456 0.5569 0.9993
3.250 0.6204 0.01463 0.00730 -0.0459 0.5376 0.9993
3.500 0.6494 0.01483 0.00743 -0.0462 0.5178 0.9993
3.750 0.6784 0.01505 0.00757 -0.0464 0.4978 0.9993
4.000 0.7074 0.01527 0.00773 -0.0467 0.4774 0.9993
4.250 0.7363 0.01551 0.00792 -0.0470 0.4568 0.9993
4.500 0.7651 0.01577 0.00812 -0.0474 0.4360 0.9993
4.750 0.7939 0.01606 0.00834 -0.0477 0.4152 0.9993
5.000 0.8226 0.01637 0.00859 -0.0480 0.3945 0.9993
5.250 0.8512 0.01671 0.00888 -0.0483 0.3740 0.9993
5.500 0.8797 0.01707 0.00918 -0.0487 0.3538 0.9993
5.750 0.9081 0.01746 0.00951 -0.0490 0.3338 0.9993
6.000 0.9365 0.01785 0.00988 -0.0494 0.3140 0.9993
6.250 0.9648 0.01826 0.01028 -0.0498 0.2946 0.9993
6.500 0.9930 0.01870 0.01070 -0.0501 0.2756 0.9993
6.750 1.0211 0.01916 0.01116 -0.0504 0.2571 0.9993
7.000 1.0489 0.01965 0.01164 -0.0508 0.2391 0.9993
7.250 1.0766 0.02018 0.01216 -0.0511 0.2217 0.9993
7.500 1.1040 0.02075 0.01272 -0.0514 0.2050 0.9993
7.750 1.1312 0.02136 0.01331 -0.0517 0.1890 0.9993
8.000 1.1580 0.02205 0.01396 -0.0520 0.1740 0.9993
8.250 1.1846 0.02274 0.01467 -0.0522 0.1598 0.9993
8.500 1.2111 0.02345 0.01542 -0.0524 0.1463 0.9993
8.750 1.2372 0.02423 0.01624 -0.0526 0.1338 0.9993
9.000 1.2628 0.02505 0.01709 -0.0527 0.1222 0.9993
9.250 1.2878 0.02590 0.01795 -0.0528 0.1111 0.9993
9.500 1.3124 0.02674 0.01882 -0.0529 0.1000 0.9993
9.750 1.3373 0.02743 0.01959 -0.0531 0.0886 0.9993
10.000 1.3611 0.02828 0.02048 -0.0532 0.0789 0.9993
10.250 1.3845 0.02919 0.02150 -0.0531 0.0703 0.9993
10.500 1.4065 0.03025 0.02261 -0.0529 0.0626 0.9993
10.750 1.4279 0.03135 0.02383 -0.0527 0.0532 0.9993
11.000 1.4467 0.03283 0.02538 -0.0522 0.0410 0.9993
11.250 1.4606 0.03488 0.02746 -0.0512 0.0312 0.9993
11.500 1.4717 0.03700 0.02965 -0.0499 0.0267 0.9993
11.750 1.4797 0.03924 0.03202 -0.0482 0.0241 0.9993
12.000 1.4833 0.04164 0.03453 -0.0461 0.0226 0.9993
12.250 1.4841 0.04411 0.03716 -0.0437 0.0214 0.9993
12.500 1.4754 0.04691 0.04006 -0.0405 0.0208 0.9993
12.750 1.4660 0.05037 0.04360 -0.0385 0.0203 0.9993
13.000 1.4600 0.05412 0.04759 -0.0377 0.0197 0.9993
13.250 1.4543 0.05813 0.05179 -0.0376 0.0192 0.9993
13.500 1.4488 0.06230 0.05611 -0.0379 0.0188 0.9993
13.750 1.4436 0.06655 0.06048 -0.0384 0.0184 0.9993
14.000 1.4388 0.07071 0.06473 -0.0389 0.0181 0.9993
14.250 1.4352 0.07464 0.06869 -0.0390 0.0177 0.9993
14.500 1.4262 0.07981 0.07410 -0.0403 0.0176 0.9993
14.750 1.4163 0.08516 0.07968 -0.0418 0.0174 0.9993
15.000 1.4052 0.09082 0.08555 -0.0437 0.0173 0.9993
15.250 1.3932 0.09677 0.09172 -0.0459 0.0172 0.9993
15.500 1.3798 0.10310 0.09826 -0.0486 0.0171 0.9993
15.750 1.3658 0.10976 0.10513 -0.0518 0.0171 0.9993
16.000 1.3515 0.11691 0.11248 -0.0556 0.0171 0.9993
16.250 1.3365 0.12458 0.12035 -0.0600 0.0171 0.9993
16.500 1.3211 0.13267 0.12864 -0.0649 0.0172 0.9993
16.750 1.3053 0.14124 0.13740 -0.0704 0.0173 0.9993
17.000 1.2892 0.15035 0.14669 -0.0765 0.0174 0.9993
17.250 1.2731 0.15991 0.15641 -0.0830 0.0175 0.9993
17.500 1.2574 0.16977 0.16641 -0.0898 0.0177 0.9993
|
Polar data table (+)
Polar graphs
<< Back to S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il)