S4320 (s4320-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4320 (s4320-il) Reynolds number: 500,000 Max Cl/Cd: 117.16 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4320-il-500000.txt Download as CSV file: xf-s4320-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2781 0.09182 0.08972 -0.0335 1.0000 0.0144
-8.250 -0.2733 0.08931 0.08724 -0.0340 1.0000 0.0149
-8.000 -0.2709 0.08665 0.08463 -0.0346 1.0000 0.0155
-7.750 -0.2566 0.08270 0.08070 -0.0390 0.9845 0.0158
-7.500 -0.2307 0.07720 0.07517 -0.0482 0.9645 0.0173
-7.250 -0.2066 0.07113 0.06904 -0.0599 0.9333 0.0181
-7.000 -0.1963 0.06693 0.06476 -0.0649 0.9060 0.0182
-6.750 -0.1876 0.06271 0.06043 -0.0691 0.8853 0.0183
-6.500 -0.1870 0.05780 0.05547 -0.0717 0.8694 0.0190
-6.250 -0.1738 0.05525 0.05284 -0.0735 0.8557 0.0195
-6.000 -0.1582 0.05173 0.04923 -0.0768 0.8430 0.0201
-5.750 -0.1400 0.04763 0.04500 -0.0808 0.8316 0.0208
-5.500 -0.1189 0.04261 0.03980 -0.0854 0.8214 0.0222
-5.250 -0.0908 0.03324 0.02972 -0.0919 0.8122 0.0248
-5.000 -0.0717 0.02997 0.02639 -0.0933 0.8033 0.0261
-4.750 -0.0479 0.02859 0.02487 -0.0938 0.7952 0.0277
-4.500 -0.0202 0.02429 0.01988 -0.0954 0.7869 0.0334
-4.250 0.0045 0.02304 0.01863 -0.0956 0.7794 0.0350
-4.000 0.0351 0.02470 0.02005 -0.0949 0.7707 0.0413
-3.750 0.0637 0.01555 0.00971 -0.0954 0.7652 0.0249
-3.500 0.0919 0.01439 0.00835 -0.0953 0.7572 0.0248
-3.250 0.1192 0.01272 0.00643 -0.0952 0.7507 0.0255
-3.000 0.1472 0.01178 0.00542 -0.0951 0.7429 0.0263
-2.500 0.2032 0.01061 0.00408 -0.0949 0.7286 0.0277
-2.250 0.2312 0.01023 0.00359 -0.0947 0.7220 0.0287
-2.000 0.2596 0.00990 0.00323 -0.0947 0.7145 0.0301
-1.750 0.2878 0.00967 0.00291 -0.0946 0.7077 0.0317
-1.500 0.3163 0.00935 0.00254 -0.0946 0.7003 0.0335
-1.250 0.3447 0.00915 0.00227 -0.0945 0.6934 0.0379
-1.000 0.3732 0.00889 0.00208 -0.0945 0.6859 0.0638
-0.750 0.4010 0.00837 0.00199 -0.0948 0.6788 0.2135
-0.500 0.4289 0.00797 0.00198 -0.0950 0.6710 0.3508
-0.250 0.4560 0.00752 0.00200 -0.0950 0.6638 0.5303
0.000 0.4814 0.00704 0.00207 -0.0945 0.6560 0.7178
0.250 0.5073 0.00649 0.00200 -0.0933 0.6488 1.0000
0.500 0.5357 0.00654 0.00199 -0.0934 0.6406 1.0000
0.750 0.5638 0.00663 0.00196 -0.0933 0.6332 1.0000
1.000 0.5922 0.00669 0.00197 -0.0933 0.6247 1.0000
1.250 0.6203 0.00678 0.00197 -0.0932 0.6170 1.0000
1.500 0.6484 0.00685 0.00199 -0.0932 0.6081 1.0000
1.750 0.6765 0.00694 0.00202 -0.0932 0.5994 1.0000
2.000 0.7043 0.00705 0.00204 -0.0931 0.5904 1.0000
2.250 0.7323 0.00713 0.00209 -0.0931 0.5804 1.0000
2.500 0.7601 0.00723 0.00214 -0.0930 0.5705 1.0000
2.750 0.7877 0.00735 0.00220 -0.0929 0.5605 1.0000
3.000 0.8155 0.00745 0.00227 -0.0928 0.5492 1.0000
3.250 0.8431 0.00757 0.00235 -0.0928 0.5378 1.0000
3.500 0.8705 0.00770 0.00245 -0.0927 0.5258 1.0000
3.750 0.8978 0.00785 0.00255 -0.0925 0.5131 1.0000
4.000 0.9249 0.00801 0.00266 -0.0924 0.4995 1.0000
4.250 0.9518 0.00818 0.00279 -0.0923 0.4849 1.0000
4.500 0.9786 0.00837 0.00295 -0.0921 0.4693 1.0000
4.750 1.0052 0.00858 0.00310 -0.0919 0.4528 1.0000
5.000 1.0315 0.00882 0.00328 -0.0917 0.4354 1.0000
5.250 1.0574 0.00909 0.00348 -0.0914 0.4170 1.0000
5.500 1.0833 0.00937 0.00372 -0.0912 0.3977 1.0000
5.750 1.1088 0.00967 0.00396 -0.0909 0.3777 1.0000
6.000 1.1338 0.01003 0.00423 -0.0905 0.3580 1.0000
6.250 1.1589 0.01037 0.00451 -0.0902 0.3378 1.0000
6.500 1.1835 0.01075 0.00483 -0.0898 0.3180 1.0000
6.750 1.2078 0.01115 0.00517 -0.0894 0.2994 1.0000
7.000 1.2322 0.01154 0.00551 -0.0890 0.2824 1.0000
7.250 1.2562 0.01195 0.00588 -0.0885 0.2652 1.0000
7.500 1.2798 0.01239 0.00628 -0.0880 0.2483 1.0000
7.750 1.3031 0.01283 0.00668 -0.0875 0.2332 1.0000
8.000 1.3256 0.01334 0.00713 -0.0869 0.2164 1.0000
8.250 1.3481 0.01383 0.00757 -0.0863 0.1994 1.0000
8.500 1.3701 0.01434 0.00806 -0.0856 0.1839 1.0000
8.750 1.3914 0.01489 0.00856 -0.0848 0.1682 1.0000
9.000 1.4118 0.01548 0.00909 -0.0839 0.1521 1.0000
9.250 1.4318 0.01609 0.00965 -0.0830 0.1378 1.0000
9.500 1.4513 0.01669 0.01024 -0.0820 0.1255 1.0000
9.750 1.4699 0.01734 0.01087 -0.0809 0.1133 1.0000
10.000 1.4873 0.01803 0.01153 -0.0796 0.1010 1.0000
10.250 1.5038 0.01873 0.01222 -0.0783 0.0909 1.0000
10.500 1.5182 0.01951 0.01297 -0.0766 0.0799 1.0000
10.750 1.5288 0.02034 0.01376 -0.0743 0.0701 1.0000
11.000 1.5367 0.02128 0.01467 -0.0718 0.0596 1.0000
11.250 1.5422 0.02242 0.01577 -0.0692 0.0466 1.0000
11.500 1.5402 0.02416 0.01738 -0.0661 0.0290 1.0000
11.750 1.5343 0.02636 0.01948 -0.0631 0.0152 1.0000
12.000 1.5332 0.02840 0.02155 -0.0608 0.0109 1.0000
12.250 1.5358 0.03027 0.02351 -0.0592 0.0095 1.0000
12.500 1.5392 0.03217 0.02552 -0.0578 0.0086 1.0000
12.750 1.5404 0.03437 0.02782 -0.0565 0.0080 1.0000
13.000 1.5397 0.03687 0.03044 -0.0554 0.0075 1.0000
13.250 1.5371 0.03967 0.03337 -0.0545 0.0071 1.0000
13.500 1.5373 0.04232 0.03615 -0.0539 0.0069 1.0000
13.750 1.5365 0.04516 0.03911 -0.0536 0.0066 1.0000
14.000 1.5331 0.04842 0.04251 -0.0534 0.0064 1.0000
14.250 1.5300 0.05177 0.04598 -0.0535 0.0060 1.0000
14.500 1.5245 0.05555 0.04990 -0.0538 0.0058 1.0000
14.750 1.5175 0.05974 0.05421 -0.0545 0.0057 1.0000
15.000 1.5081 0.06447 0.05908 -0.0555 0.0056 1.0000
15.250 1.4985 0.06945 0.06420 -0.0568 0.0055 1.0000
15.500 1.4863 0.07506 0.06994 -0.0586 0.0054 1.0000
15.750 1.4745 0.08084 0.07586 -0.0606 0.0053 1.0000
16.000 1.4588 0.08749 0.08266 -0.0631 0.0052 1.0000
16.250 1.4451 0.09401 0.08932 -0.0658 0.0052 1.0000
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Polar data table (+)
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