S4320 (s4320-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S4320 (s4320-il) Reynolds number: 200,000 Max Cl/Cd: 82.01 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4320-il-200000-n5.txt Download as CSV file: xf-s4320-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4320
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2886 0.10435 0.10088 -0.0297 1.0000 0.0226
-9.000 -0.2875 0.10129 0.09788 -0.0324 1.0000 0.0239
-8.750 -0.2853 0.09830 0.09494 -0.0346 1.0000 0.0242
-8.500 -0.1984 0.08082 0.07775 -0.0460 0.9567 0.0247
-8.250 -0.1848 0.07634 0.07325 -0.0470 0.9429 0.0253
-7.750 -0.1657 0.06887 0.06573 -0.0502 0.9112 0.0262
-7.500 -0.1615 0.06526 0.06209 -0.0515 0.8951 0.0264
-7.250 -0.1604 0.06150 0.05832 -0.0530 0.8798 0.0263
-7.000 -0.2119 0.06826 0.06497 -0.0614 0.9102 0.0179
-6.750 -0.1996 0.06466 0.06132 -0.0649 0.8931 0.0175
-6.500 -0.1881 0.06018 0.05677 -0.0697 0.8765 0.0172
-6.250 -0.1748 0.05529 0.05179 -0.0749 0.8621 0.0169
-6.000 -0.1586 0.04973 0.04608 -0.0805 0.8494 0.0167
-5.750 -0.1387 0.04225 0.03830 -0.0870 0.8384 0.0173
-5.500 -0.1159 0.03317 0.02851 -0.0926 0.8282 0.0182
-5.250 -0.0931 0.02863 0.02339 -0.0945 0.8193 0.0182
-5.000 -0.0692 0.02480 0.01897 -0.0956 0.8110 0.0185
-4.750 -0.0438 0.02228 0.01603 -0.0961 0.8024 0.0190
-4.500 -0.0177 0.02071 0.01413 -0.0962 0.7948 0.0198
-4.250 0.0091 0.01975 0.01297 -0.0963 0.7862 0.0214
-4.000 0.0364 0.01843 0.01127 -0.0962 0.7790 0.0226
-3.750 0.0641 0.01716 0.00968 -0.0960 0.7708 0.0232
-3.500 0.0916 0.01617 0.00844 -0.0958 0.7639 0.0238
-3.250 0.1192 0.01539 0.00746 -0.0955 0.7559 0.0244
-3.000 0.1463 0.01452 0.00651 -0.0954 0.7491 0.0260
-2.750 0.1738 0.01403 0.00598 -0.0953 0.7412 0.0280
-2.500 0.2014 0.01354 0.00538 -0.0951 0.7345 0.0292
-2.250 0.2292 0.01312 0.00487 -0.0950 0.7268 0.0305
-2.000 0.2571 0.01281 0.00442 -0.0948 0.7202 0.0321
-1.750 0.2851 0.01247 0.00404 -0.0948 0.7124 0.0353
-1.500 0.3131 0.01224 0.00375 -0.0946 0.7058 0.0434
-1.250 0.3411 0.01189 0.00350 -0.0946 0.6979 0.0749
-1.000 0.3687 0.01154 0.00335 -0.0947 0.6913 0.1516
-0.750 0.3962 0.01117 0.00330 -0.0948 0.6833 0.2562
-0.500 0.4228 0.01071 0.00328 -0.0948 0.6764 0.4096
-0.250 0.4450 0.00994 0.00339 -0.0935 0.6684 0.6780
0.000 0.4727 0.00932 0.00324 -0.0925 0.6612 1.0000
0.250 0.5007 0.00941 0.00318 -0.0924 0.6526 1.0000
0.500 0.5286 0.00950 0.00313 -0.0923 0.6445 1.0000
0.750 0.5565 0.00960 0.00310 -0.0921 0.6360 1.0000
1.000 0.5843 0.00969 0.00310 -0.0921 0.6271 1.0000
1.250 0.6119 0.00981 0.00308 -0.0919 0.6187 1.0000
1.500 0.6396 0.00991 0.00312 -0.0918 0.6091 1.0000
1.750 0.6672 0.01002 0.00315 -0.0917 0.6000 1.0000
2.000 0.6946 0.01015 0.00318 -0.0915 0.5908 1.0000
2.250 0.7221 0.01027 0.00326 -0.0914 0.5805 1.0000
2.500 0.7494 0.01040 0.00333 -0.0912 0.5705 1.0000
2.750 0.7766 0.01054 0.00341 -0.0910 0.5600 1.0000
3.000 0.8037 0.01069 0.00350 -0.0908 0.5483 1.0000
3.250 0.8306 0.01084 0.00361 -0.0906 0.5361 1.0000
3.500 0.8574 0.01100 0.00373 -0.0904 0.5234 1.0000
3.750 0.8841 0.01118 0.00389 -0.0902 0.5101 1.0000
4.000 0.9105 0.01138 0.00404 -0.0899 0.4960 1.0000
4.250 0.9367 0.01159 0.00420 -0.0896 0.4813 1.0000
4.500 0.9627 0.01182 0.00441 -0.0893 0.4655 1.0000
4.750 0.9884 0.01208 0.00461 -0.0889 0.4494 1.0000
5.000 1.0137 0.01236 0.00484 -0.0885 0.4323 1.0000
5.250 1.0388 0.01267 0.00510 -0.0881 0.4149 1.0000
5.500 1.0637 0.01299 0.00540 -0.0877 0.3962 1.0000
5.750 1.0881 0.01335 0.00571 -0.0873 0.3777 1.0000
6.250 1.1359 0.01416 0.00643 -0.0862 0.3405 1.0000
6.500 1.1592 0.01460 0.00685 -0.0856 0.3217 1.0000
6.750 1.1821 0.01508 0.00728 -0.0850 0.3041 1.0000
7.250 1.2268 0.01609 0.00823 -0.0837 0.2707 1.0000
7.500 1.2487 0.01662 0.00877 -0.0829 0.2546 1.0000
7.750 1.2701 0.01717 0.00931 -0.0822 0.2394 1.0000
8.000 1.2910 0.01774 0.00989 -0.0813 0.2251 1.0000
8.250 1.3114 0.01833 0.01049 -0.0805 0.2117 1.0000
8.500 1.3311 0.01896 0.01113 -0.0795 0.1984 1.0000
8.750 1.3500 0.01962 0.01182 -0.0784 0.1858 1.0000
9.000 1.3678 0.02033 0.01254 -0.0772 0.1742 1.0000
9.250 1.3854 0.02102 0.01327 -0.0760 0.1626 1.0000
9.500 1.4019 0.02176 0.01405 -0.0747 0.1518 1.0000
9.750 1.4168 0.02255 0.01489 -0.0732 0.1416 1.0000
10.000 1.4285 0.02341 0.01578 -0.0712 0.1310 1.0000
10.250 1.4378 0.02437 0.01674 -0.0690 0.1194 1.0000
10.500 1.4463 0.02543 0.01779 -0.0669 0.1080 1.0000
10.750 1.4555 0.02651 0.01890 -0.0651 0.0976 1.0000
11.000 1.4638 0.02770 0.02014 -0.0633 0.0888 1.0000
11.250 1.4706 0.02906 0.02153 -0.0616 0.0802 1.0000
11.500 1.4757 0.03063 0.02310 -0.0600 0.0709 1.0000
11.750 1.4814 0.03224 0.02474 -0.0586 0.0614 1.0000
12.000 1.4855 0.03407 0.02661 -0.0573 0.0520 1.0000
12.250 1.4891 0.03602 0.02860 -0.0562 0.0446 1.0000
12.500 1.4910 0.03822 0.03085 -0.0552 0.0371 1.0000
12.750 1.4907 0.04075 0.03340 -0.0542 0.0292 1.0000
13.000 1.4883 0.04361 0.03629 -0.0535 0.0223 1.0000
13.250 1.4839 0.04680 0.03954 -0.0530 0.0172 1.0000
13.500 1.4787 0.05023 0.04305 -0.0527 0.0139 1.0000
13.750 1.4742 0.05371 0.04666 -0.0527 0.0122 1.0000
14.000 1.4692 0.05739 0.05048 -0.0529 0.0111 1.0000
14.250 1.4617 0.06155 0.05477 -0.0534 0.0102 1.0000
14.500 1.4549 0.06581 0.05918 -0.0542 0.0096 1.0000
14.750 1.4485 0.07020 0.06374 -0.0553 0.0091 1.0000
15.000 1.4407 0.07499 0.06870 -0.0566 0.0086 1.0000
15.250 1.4321 0.08008 0.07395 -0.0583 0.0082 1.0000
15.500 1.4222 0.08560 0.07965 -0.0603 0.0079 1.0000
15.750 1.4112 0.09151 0.08574 -0.0627 0.0077 1.0000
16.000 1.3976 0.09809 0.09248 -0.0655 0.0074 1.0000
16.250 1.3848 0.10478 0.09934 -0.0686 0.0073 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S4320 (s4320-il)