Supermarine 371-I (root) (supermarine371i-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Supermarine 371-I (root) (supermarine371i-il) Reynolds number: 50,000 Max Cl/Cd: 27.6 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-supermarine371i-il-50000-n5.txt Download as CSV file: xf-supermarine371i-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Supermarine 371-I (root)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5961 0.09049 0.08319 -0.0496 1.0000 0.0550
-11.500 -0.6134 0.08413 0.07681 -0.0532 1.0000 0.0547
-11.250 -0.6329 0.07843 0.07107 -0.0560 1.0000 0.0544
-11.000 -0.6551 0.07334 0.06590 -0.0577 1.0000 0.0542
-10.750 -0.6772 0.06904 0.06148 -0.0580 1.0000 0.0541
-10.500 -0.6978 0.06542 0.05773 -0.0568 1.0000 0.0541
-10.250 -0.7163 0.06240 0.05456 -0.0543 1.0000 0.0540
-10.000 -0.7326 0.05933 0.05129 -0.0515 1.0000 0.0542
-9.750 -0.7460 0.05639 0.04809 -0.0482 1.0000 0.0545
-9.500 -0.7570 0.05373 0.04517 -0.0446 1.0000 0.0547
-9.250 -0.7669 0.05142 0.04260 -0.0404 1.0000 0.0549
-9.000 -0.7757 0.04934 0.04026 -0.0360 1.0000 0.0552
-8.750 -0.7787 0.04741 0.03818 -0.0322 1.0000 0.0557
-8.500 -0.7793 0.04564 0.03625 -0.0287 1.0000 0.0564
-8.250 -0.7773 0.04395 0.03439 -0.0254 1.0000 0.0573
-8.000 -0.7731 0.04244 0.03271 -0.0224 1.0000 0.0587
-7.750 -0.7670 0.04097 0.03100 -0.0196 1.0000 0.0609
-7.500 -0.7437 0.03882 0.02843 -0.0197 0.9956 0.0644
-7.250 -0.7163 0.03702 0.02646 -0.0204 0.9911 0.0674
-7.000 -0.6880 0.03558 0.02489 -0.0210 0.9868 0.0708
-6.750 -0.6586 0.03430 0.02340 -0.0217 0.9830 0.0767
-6.500 -0.6316 0.03334 0.02227 -0.0220 0.9783 0.0842
-6.250 -0.6011 0.03228 0.02109 -0.0228 0.9746 0.0932
-6.000 -0.5728 0.03125 0.01994 -0.0232 0.9708 0.1066
-5.750 -0.5484 0.03010 0.01873 -0.0230 0.9665 0.1234
-5.500 -0.5267 0.02884 0.01761 -0.0228 0.9624 0.1474
-5.250 -0.5084 0.02781 0.01674 -0.0221 0.9580 0.1784
-5.000 -0.4927 0.02686 0.01602 -0.0209 0.9530 0.2182
-4.750 -0.4760 0.02573 0.01533 -0.0202 0.9485 0.2854
-4.500 -0.4655 0.02454 0.01487 -0.0179 0.9438 0.3968
-4.250 -0.4443 0.02478 0.01630 -0.0139 0.9409 0.5830
-4.000 -0.4313 0.02513 0.01650 -0.0107 0.9361 0.6717
-3.750 -0.4084 0.02563 0.01679 -0.0090 0.9327 0.7157
-3.500 -0.3882 0.02601 0.01697 -0.0070 0.9287 0.7414
-3.250 -0.3689 0.02631 0.01705 -0.0051 0.9244 0.7631
-3.000 -0.3423 0.02685 0.01742 -0.0039 0.9213 0.7877
-2.750 -0.3094 0.02754 0.01794 -0.0035 0.9192 0.8138
-2.500 -0.2741 0.02809 0.01828 -0.0040 0.9171 0.8367
-2.250 -0.2449 0.02844 0.01848 -0.0039 0.9140 0.8546
-2.000 -0.2132 0.02875 0.01864 -0.0045 0.9109 0.8699
-1.750 -0.1752 0.02905 0.01877 -0.0064 0.9085 0.8840
-1.500 -0.1265 0.02938 0.01894 -0.0103 0.9069 0.8975
-1.250 -0.0706 0.02963 0.01904 -0.0159 0.9056 0.9094
-1.000 -0.0260 0.02974 0.01904 -0.0197 0.9035 0.9192
-0.750 0.0169 0.02982 0.01902 -0.0234 0.9014 0.9273
-0.500 0.0398 0.02988 0.01903 -0.0235 0.8967 0.9344
-0.250 0.0701 0.02993 0.01904 -0.0250 0.8924 0.9401
0.000 0.1000 0.03002 0.01909 -0.0264 0.8885 0.9461
0.250 0.1401 0.03007 0.01912 -0.0297 0.8852 0.9499
0.500 0.1608 0.03021 0.01926 -0.0295 0.8789 0.9565
0.750 0.1952 0.03032 0.01939 -0.0318 0.8744 0.9617
1.000 0.2401 0.03040 0.01950 -0.0358 0.8712 0.9660
1.250 0.2600 0.03062 0.01977 -0.0356 0.8638 0.9737
1.500 0.2990 0.03073 0.01995 -0.0386 0.8590 0.9780
1.750 0.3319 0.03090 0.02018 -0.0405 0.8536 0.9826
2.000 0.3583 0.03109 0.02048 -0.0413 0.8461 0.9876
2.250 0.3995 0.03115 0.02064 -0.0444 0.8410 0.9904
2.500 0.4223 0.03138 0.02098 -0.0446 0.8311 0.9963
2.750 0.4669 0.03129 0.02105 -0.0478 0.8246 0.9990
3.000 0.4782 0.03149 0.02135 -0.0455 0.8127 1.0000
3.250 0.4886 0.03165 0.02161 -0.0428 0.8011 1.0000
3.500 0.5126 0.03160 0.02170 -0.0422 0.7912 1.0000
3.750 0.5362 0.03145 0.02172 -0.0412 0.7800 1.0000
4.000 0.5479 0.03139 0.02178 -0.0383 0.7660 1.0000
4.250 0.5626 0.03118 0.02170 -0.0356 0.7514 1.0000
4.500 0.5789 0.03084 0.02150 -0.0330 0.7362 1.0000
4.750 0.5991 0.03024 0.02108 -0.0306 0.7197 1.0000
5.000 0.6185 0.02945 0.02044 -0.0278 0.7010 1.0000
5.250 0.6169 0.02922 0.02030 -0.0223 0.6796 1.0000
5.500 0.6353 0.02828 0.01952 -0.0191 0.6575 1.0000
5.750 0.6288 0.02828 0.01957 -0.0133 0.6320 1.0000
6.000 0.6276 0.02816 0.01952 -0.0081 0.6036 1.0000
6.250 0.6358 0.02773 0.01921 -0.0040 0.5678 1.0000
6.500 0.6666 0.02633 0.01780 -0.0017 0.5065 1.0000
6.750 0.7042 0.02551 0.01629 -0.0002 0.3931 1.0000
7.000 0.7054 0.02647 0.01672 0.0041 0.3258 1.0000
7.250 0.7044 0.02770 0.01758 0.0080 0.2719 1.0000
7.500 0.7058 0.02906 0.01858 0.0112 0.2281 1.0000
7.750 0.7109 0.03047 0.01971 0.0137 0.1939 1.0000
8.000 0.7192 0.03185 0.02088 0.0157 0.1660 1.0000
8.250 0.7295 0.03326 0.02207 0.0175 0.1451 1.0000
8.500 0.7443 0.03457 0.02335 0.0188 0.1271 1.0000
8.750 0.7620 0.03589 0.02466 0.0199 0.1125 1.0000
9.000 0.7837 0.03723 0.02597 0.0207 0.1004 1.0000
9.250 0.8082 0.03857 0.02736 0.0211 0.0898 1.0000
9.500 0.8393 0.04015 0.02917 0.0210 0.0811 1.0000
9.750 0.8656 0.04189 0.03088 0.0209 0.0747 1.0000
10.000 0.8881 0.04386 0.03323 0.0214 0.0688 1.0000
10.250 0.9116 0.04601 0.03554 0.0215 0.0654 1.0000
10.500 0.9313 0.04850 0.03815 0.0218 0.0623 1.0000
10.750 0.9369 0.05106 0.04116 0.0238 0.0597 1.0000
11.000 0.9401 0.05361 0.04402 0.0256 0.0573 1.0000
11.250 0.9419 0.05624 0.04690 0.0273 0.0556 1.0000
11.500 0.9412 0.05915 0.05004 0.0289 0.0545 1.0000
11.750 0.9376 0.06222 0.05337 0.0304 0.0537 1.0000
12.000 0.9310 0.06550 0.05686 0.0316 0.0531 1.0000
12.250 0.9230 0.06899 0.06052 0.0325 0.0525 1.0000
12.500 0.9139 0.07279 0.06447 0.0330 0.0519 1.0000
12.750 0.8955 0.07719 0.06906 0.0330 0.0518 1.0000
13.000 0.8724 0.08232 0.07440 0.0321 0.0518 1.0000
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