S2050 8.93% (s2050-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S2050 8.93% (s2050-il) Reynolds number: 500,000 Max Cl/Cd: 70.6 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2050-il-500000-n5.txt Download as CSV file: xf-s2050-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2050 8.93%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.7860 0.05076 0.04810 -0.0458 1.0000 0.0048
-11.000 -0.8100 0.04374 0.04088 -0.0514 1.0000 0.0048
-10.750 -0.8297 0.04009 0.03708 -0.0516 1.0000 0.0048
-10.500 -0.8444 0.03674 0.03350 -0.0503 1.0000 0.0048
-10.250 -0.8484 0.03368 0.03017 -0.0491 1.0000 0.0048
-10.000 -0.8466 0.03087 0.02706 -0.0477 1.0000 0.0049
-9.750 -0.8391 0.02852 0.02444 -0.0464 1.0000 0.0050
-9.500 -0.8275 0.02654 0.02220 -0.0453 1.0000 0.0051
-9.250 -0.8125 0.02498 0.02041 -0.0442 1.0000 0.0052
-9.000 -0.7961 0.02347 0.01867 -0.0432 1.0000 0.0054
-8.750 -0.7776 0.02230 0.01730 -0.0422 1.0000 0.0055
-8.500 -0.7586 0.02106 0.01587 -0.0413 1.0000 0.0056
-8.250 -0.7393 0.01979 0.01442 -0.0404 1.0000 0.0057
-8.000 -0.7208 0.01810 0.01252 -0.0395 1.0000 0.0059
-7.750 -0.7002 0.01690 0.01117 -0.0387 1.0000 0.0060
-7.500 -0.6785 0.01594 0.01010 -0.0380 1.0000 0.0063
-7.250 -0.6559 0.01515 0.00922 -0.0374 1.0000 0.0065
-7.000 -0.6328 0.01448 0.00844 -0.0367 1.0000 0.0068
-6.750 -0.6093 0.01386 0.00774 -0.0362 1.0000 0.0071
-6.500 -0.5802 0.01328 0.00707 -0.0367 0.9991 0.0076
-6.250 -0.5474 0.01274 0.00644 -0.0380 0.9973 0.0080
-6.000 -0.5139 0.01227 0.00589 -0.0394 0.9955 0.0085
-5.750 -0.4807 0.01172 0.00528 -0.0408 0.9937 0.0100
-5.500 -0.4485 0.01131 0.00482 -0.0419 0.9912 0.0120
-5.250 -0.4154 0.01085 0.00437 -0.0432 0.9886 0.0169
-5.000 -0.3814 0.01043 0.00401 -0.0447 0.9861 0.0278
-4.750 -0.3463 0.01011 0.00371 -0.0464 0.9841 0.0379
-4.500 -0.3161 0.00980 0.00344 -0.0470 0.9799 0.0491
-4.250 -0.2837 0.00951 0.00320 -0.0481 0.9759 0.0641
-4.000 -0.2493 0.00920 0.00297 -0.0497 0.9726 0.0814
-3.750 -0.2185 0.00893 0.00275 -0.0504 0.9673 0.0983
-3.500 -0.1868 0.00868 0.00255 -0.0512 0.9610 0.1139
-3.250 -0.1554 0.00841 0.00235 -0.0520 0.9542 0.1349
-3.000 -0.1229 0.00815 0.00215 -0.0530 0.9463 0.1586
-2.750 -0.0894 0.00785 0.00197 -0.0543 0.9373 0.1933
-2.500 -0.0530 0.00749 0.00178 -0.0563 0.9273 0.2430
-2.250 -0.0156 0.00716 0.00158 -0.0584 0.9128 0.2956
-2.000 0.0204 0.00679 0.00140 -0.0602 0.8915 0.3654
-1.750 0.0520 0.00652 0.00125 -0.0610 0.8642 0.4324
-1.500 0.0801 0.00628 0.00115 -0.0611 0.8359 0.5092
-1.250 0.1067 0.00615 0.00115 -0.0607 0.8086 0.5804
-1.000 0.1333 0.00616 0.00116 -0.0603 0.7828 0.6253
-0.750 0.1599 0.00622 0.00118 -0.0598 0.7584 0.6544
-0.500 0.1866 0.00629 0.00120 -0.0594 0.7348 0.6734
-0.250 0.2133 0.00638 0.00121 -0.0590 0.7116 0.6884
0.000 0.2401 0.00647 0.00124 -0.0586 0.6877 0.7011
0.250 0.2668 0.00657 0.00126 -0.0583 0.6626 0.7136
0.500 0.2933 0.00668 0.00130 -0.0578 0.6362 0.7271
0.750 0.3197 0.00680 0.00135 -0.0574 0.6094 0.7394
1.000 0.3461 0.00692 0.00141 -0.0570 0.5818 0.7500
1.250 0.3726 0.00706 0.00147 -0.0566 0.5535 0.7605
1.500 0.3991 0.00722 0.00155 -0.0563 0.5253 0.7706
1.750 0.4255 0.00737 0.00163 -0.0559 0.4967 0.7787
2.250 0.4781 0.00773 0.00183 -0.0552 0.4364 0.7942
2.500 0.5044 0.00794 0.00194 -0.0549 0.4060 0.8026
2.750 0.5306 0.00814 0.00208 -0.0545 0.3767 0.8109
3.000 0.5568 0.00835 0.00222 -0.0542 0.3479 0.8183
3.250 0.5827 0.00859 0.00237 -0.0538 0.3177 0.8262
3.500 0.6082 0.00888 0.00255 -0.0534 0.2809 0.8344
3.750 0.6337 0.00916 0.00275 -0.0530 0.2492 0.8439
4.000 0.6592 0.00939 0.00294 -0.0525 0.2256 0.8536
4.250 0.6841 0.00969 0.00316 -0.0520 0.1963 0.8641
4.500 0.7079 0.01008 0.00342 -0.0513 0.1586 0.8765
4.750 0.7313 0.01045 0.00369 -0.0504 0.1274 0.8914
5.000 0.7538 0.01078 0.00396 -0.0493 0.1024 0.9098
5.250 0.7756 0.01110 0.00423 -0.0481 0.0821 0.9346
5.500 0.8036 0.01140 0.00451 -0.0482 0.0657 0.9832
5.750 0.8298 0.01179 0.00486 -0.0481 0.0520 1.0000
6.000 0.8554 0.01222 0.00524 -0.0478 0.0399 1.0000
6.250 0.8805 0.01271 0.00566 -0.0475 0.0284 1.0000
6.500 0.9055 0.01321 0.00613 -0.0471 0.0205 1.0000
6.750 0.9308 0.01366 0.00659 -0.0467 0.0175 1.0000
7.000 0.9556 0.01414 0.00712 -0.0463 0.0157 1.0000
7.250 0.9798 0.01473 0.00775 -0.0458 0.0143 1.0000
7.500 1.0043 0.01524 0.00833 -0.0453 0.0138 1.0000
7.750 1.0284 0.01578 0.00895 -0.0448 0.0132 1.0000
8.000 1.0520 0.01637 0.00961 -0.0442 0.0127 1.0000
8.250 1.0753 0.01699 0.01032 -0.0435 0.0121 1.0000
8.500 1.0981 0.01762 0.01102 -0.0429 0.0116 1.0000
8.750 1.1202 0.01833 0.01179 -0.0421 0.0110 1.0000
9.000 1.1408 0.01921 0.01276 -0.0412 0.0106 1.0000
9.250 1.1591 0.02035 0.01400 -0.0400 0.0102 1.0000
9.500 1.1774 0.02146 0.01522 -0.0387 0.0099 1.0000
9.750 1.1970 0.02235 0.01624 -0.0377 0.0097 1.0000
10.000 1.2156 0.02333 0.01734 -0.0366 0.0096 1.0000
10.250 1.2333 0.02437 0.01850 -0.0353 0.0093 1.0000
10.500 1.2504 0.02540 0.01967 -0.0341 0.0090 1.0000
10.750 1.2665 0.02647 0.02087 -0.0327 0.0087 1.0000
11.000 1.2815 0.02757 0.02210 -0.0313 0.0084 1.0000
11.250 1.2948 0.02873 0.02338 -0.0297 0.0082 1.0000
11.500 1.3051 0.02999 0.02479 -0.0277 0.0079 1.0000
11.750 1.3116 0.03128 0.02621 -0.0253 0.0078 1.0000
12.000 1.3161 0.03266 0.02771 -0.0228 0.0076 1.0000
12.250 1.3188 0.03421 0.02939 -0.0204 0.0075 1.0000
12.500 1.3189 0.03605 0.03135 -0.0183 0.0073 1.0000
12.750 1.3163 0.03827 0.03371 -0.0165 0.0072 1.0000
13.000 1.3110 0.04096 0.03656 -0.0153 0.0071 1.0000
13.250 1.3011 0.04447 0.04024 -0.0149 0.0070 1.0000
13.500 1.2866 0.04901 0.04499 -0.0154 0.0069 1.0000
13.750 1.2769 0.05341 0.04956 -0.0169 0.0068 1.0000
14.000 1.2674 0.05822 0.05455 -0.0190 0.0068 1.0000
14.250 1.2541 0.06408 0.06060 -0.0222 0.0067 1.0000
14.500 1.2422 0.07021 0.06690 -0.0258 0.0067 1.0000
14.750 1.2278 0.07721 0.07407 -0.0302 0.0067 1.0000
15.000 1.2092 0.08537 0.08239 -0.0353 0.0067 1.0000
15.250 1.1845 0.09513 0.09233 -0.0413 0.0067 1.0000
15.500 1.1631 0.10475 0.10210 -0.0473 0.0067 1.0000
15.750 1.1396 0.11526 0.11274 -0.0537 0.0068 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S2050 8.93% (s2050-il)