CLARK W AIRFOIL (clarkw-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK W AIRFOIL (clarkw-il) Reynolds number: 500,000 Max Cl/Cd: 91.15 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkw-il-500000-n5.txt Download as CSV file: xf-clarkw-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK W AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.8045 0.04341 0.04038 -0.0784 1.0000 0.0219
-11.750 -0.8066 0.03720 0.03374 -0.0840 0.9948 0.0221
-11.500 -0.7949 0.03368 0.02986 -0.0865 0.9902 0.0224
-11.250 -0.7762 0.03121 0.02709 -0.0882 0.9865 0.0228
-11.000 -0.7521 0.02947 0.02507 -0.0898 0.9843 0.0230
-10.750 -0.7342 0.02726 0.02266 -0.0903 0.9800 0.0234
-10.500 -0.7104 0.02579 0.02106 -0.0911 0.9767 0.0237
-10.250 -0.6842 0.02457 0.01972 -0.0920 0.9741 0.0240
-10.000 -0.6571 0.02346 0.01850 -0.0929 0.9717 0.0243
-9.750 -0.6349 0.02252 0.01744 -0.0925 0.9663 0.0245
-9.500 -0.6086 0.02161 0.01642 -0.0929 0.9627 0.0249
-9.250 -0.5808 0.02075 0.01543 -0.0936 0.9598 0.0253
-9.000 -0.5575 0.01996 0.01452 -0.0931 0.9542 0.0257
-8.750 -0.5323 0.01913 0.01356 -0.0930 0.9493 0.0260
-8.500 -0.5051 0.01832 0.01262 -0.0933 0.9457 0.0263
-8.250 -0.4812 0.01761 0.01180 -0.0928 0.9397 0.0266
-8.000 -0.4557 0.01695 0.01102 -0.0925 0.9342 0.0269
-7.750 -0.4285 0.01632 0.01029 -0.0925 0.9299 0.0272
-7.500 -0.4039 0.01579 0.00967 -0.0920 0.9234 0.0274
-7.250 -0.3775 0.01534 0.00911 -0.0917 0.9176 0.0277
-7.000 -0.3517 0.01466 0.00835 -0.0915 0.9124 0.0281
-6.750 -0.3273 0.01402 0.00766 -0.0909 0.9055 0.0286
-6.500 -0.3011 0.01351 0.00708 -0.0906 0.8996 0.0289
-6.250 -0.2752 0.01307 0.00660 -0.0903 0.8933 0.0293
-6.000 -0.2490 0.01268 0.00616 -0.0899 0.8866 0.0297
-5.750 -0.2222 0.01231 0.00574 -0.0897 0.8808 0.0301
-5.500 -0.1960 0.01198 0.00536 -0.0893 0.8736 0.0305
-5.250 -0.1691 0.01167 0.00499 -0.0891 0.8673 0.0309
-5.000 -0.1424 0.01138 0.00466 -0.0887 0.8604 0.0314
-4.750 -0.1155 0.01112 0.00434 -0.0885 0.8535 0.0319
-4.500 -0.0885 0.01088 0.00405 -0.0882 0.8461 0.0324
-4.250 -0.0617 0.01068 0.00377 -0.0878 0.8361 0.0330
-4.000 -0.0351 0.01046 0.00350 -0.0874 0.8248 0.0338
-3.750 -0.0085 0.01024 0.00321 -0.0871 0.8146 0.0349
-3.500 0.0185 0.01005 0.00298 -0.0868 0.8055 0.0359
-3.250 0.0456 0.00989 0.00279 -0.0865 0.7971 0.0372
-3.000 0.0727 0.00976 0.00260 -0.0862 0.7879 0.0386
-2.750 0.0998 0.00963 0.00244 -0.0859 0.7788 0.0410
-2.500 0.1266 0.00946 0.00228 -0.0856 0.7697 0.0478
-2.250 0.1531 0.00923 0.00216 -0.0852 0.7602 0.0767
-2.000 0.1798 0.00909 0.00206 -0.0849 0.7509 0.0972
-1.750 0.2066 0.00897 0.00198 -0.0846 0.7406 0.1127
-1.500 0.2334 0.00887 0.00190 -0.0843 0.7305 0.1302
-1.250 0.2599 0.00877 0.00184 -0.0840 0.7198 0.1522
-1.000 0.2865 0.00868 0.00179 -0.0836 0.7081 0.1767
-0.750 0.3129 0.00858 0.00177 -0.0833 0.6964 0.2074
-0.500 0.3391 0.00852 0.00176 -0.0829 0.6837 0.2393
-0.250 0.3654 0.00851 0.00176 -0.0825 0.6704 0.2626
0.000 0.3915 0.00850 0.00177 -0.0821 0.6561 0.2868
0.500 0.4438 0.00854 0.00182 -0.0812 0.6250 0.3312
0.750 0.4696 0.00859 0.00184 -0.0807 0.6080 0.3482
1.000 0.4954 0.00866 0.00188 -0.0802 0.5903 0.3641
1.250 0.5209 0.00871 0.00193 -0.0797 0.5717 0.3836
1.500 0.5460 0.00875 0.00198 -0.0791 0.5516 0.4132
1.750 0.5706 0.00875 0.00204 -0.0785 0.5324 0.4551
2.000 0.5832 0.00781 0.00218 -0.0753 0.5151 0.8331
2.250 0.6138 0.00790 0.00239 -0.0754 0.4943 0.9412
2.500 0.6495 0.00812 0.00252 -0.0771 0.4740 0.9657
2.750 0.6841 0.00834 0.00265 -0.0786 0.4568 0.9795
3.000 0.7192 0.00855 0.00278 -0.0802 0.4410 0.9884
3.250 0.7540 0.00876 0.00292 -0.0818 0.4258 0.9947
3.500 0.7900 0.00899 0.00306 -0.0838 0.4102 0.9994
3.750 0.8135 0.00920 0.00320 -0.0829 0.3959 1.0000
4.000 0.8355 0.00939 0.00334 -0.0817 0.3824 1.0000
4.250 0.8579 0.00956 0.00347 -0.0806 0.3717 1.0000
4.500 0.8799 0.00976 0.00362 -0.0794 0.3615 1.0000
4.750 0.9017 0.00997 0.00379 -0.0782 0.3494 1.0000
5.000 0.9240 0.01016 0.00395 -0.0771 0.3383 1.0000
5.250 0.9461 0.01038 0.00413 -0.0760 0.3277 1.0000
5.500 0.9678 0.01063 0.00432 -0.0748 0.3146 1.0000
5.750 0.9895 0.01090 0.00453 -0.0736 0.2986 1.0000
6.000 1.0109 0.01120 0.00475 -0.0725 0.2800 1.0000
6.250 1.0327 0.01150 0.00498 -0.0714 0.2647 1.0000
6.500 1.0548 0.01178 0.00523 -0.0704 0.2523 1.0000
6.750 1.0769 0.01208 0.00548 -0.0693 0.2386 1.0000
7.000 1.0981 0.01244 0.00577 -0.0682 0.2224 1.0000
7.250 1.1190 0.01282 0.00609 -0.0671 0.2039 1.0000
7.500 1.1390 0.01327 0.00645 -0.0658 0.1822 1.0000
7.750 1.1572 0.01384 0.00688 -0.0643 0.1558 1.0000
8.000 1.1742 0.01449 0.00738 -0.0626 0.1308 1.0000
8.250 1.1919 0.01507 0.00788 -0.0610 0.1135 1.0000
8.500 1.2097 0.01561 0.00837 -0.0595 0.1002 1.0000
8.750 1.2263 0.01616 0.00886 -0.0577 0.0875 1.0000
9.000 1.2419 0.01677 0.00940 -0.0558 0.0742 1.0000
9.250 1.2572 0.01740 0.00998 -0.0539 0.0629 1.0000
9.500 1.2729 0.01801 0.01056 -0.0522 0.0551 1.0000
9.750 1.2885 0.01863 0.01117 -0.0504 0.0496 1.0000
10.000 1.3040 0.01926 0.01181 -0.0487 0.0453 1.0000
10.250 1.3193 0.01991 0.01248 -0.0471 0.0421 1.0000
10.500 1.3347 0.02055 0.01316 -0.0455 0.0394 1.0000
10.750 1.3485 0.02131 0.01393 -0.0437 0.0370 1.0000
11.000 1.3630 0.02204 0.01471 -0.0421 0.0352 1.0000
11.250 1.3772 0.02279 0.01551 -0.0406 0.0334 1.0000
11.500 1.3898 0.02366 0.01642 -0.0389 0.0316 1.0000
11.750 1.4010 0.02465 0.01744 -0.0372 0.0300 1.0000
12.000 1.4141 0.02552 0.01839 -0.0358 0.0288 1.0000
12.250 1.4259 0.02651 0.01944 -0.0343 0.0275 1.0000
12.500 1.4361 0.02765 0.02063 -0.0328 0.0261 1.0000
12.750 1.4447 0.02895 0.02197 -0.0313 0.0249 1.0000
13.000 1.4553 0.03011 0.02322 -0.0300 0.0238 1.0000
13.250 1.4646 0.03142 0.02460 -0.0288 0.0226 1.0000
13.500 1.4722 0.03291 0.02614 -0.0275 0.0216 1.0000
13.750 1.4777 0.03462 0.02791 -0.0263 0.0207 1.0000
14.000 1.4845 0.03628 0.02967 -0.0252 0.0200 1.0000
14.250 1.4904 0.03806 0.03154 -0.0242 0.0191 1.0000
14.500 1.4951 0.04001 0.03357 -0.0234 0.0183 1.0000
14.750 1.4983 0.04217 0.03579 -0.0226 0.0176 1.0000
15.000 1.4993 0.04465 0.03834 -0.0220 0.0170 1.0000
15.250 1.5009 0.04715 0.04094 -0.0215 0.0164 1.0000
15.500 1.5019 0.04980 0.04370 -0.0212 0.0159 1.0000
15.750 1.5017 0.05269 0.04669 -0.0211 0.0154 1.0000
16.000 1.5004 0.05583 0.04993 -0.0211 0.0150 1.0000
16.250 1.4976 0.05921 0.05341 -0.0214 0.0146 1.0000
16.500 1.4935 0.06288 0.05718 -0.0218 0.0143 1.0000
16.750 1.4875 0.06692 0.06132 -0.0225 0.0140 1.0000
17.000 1.4795 0.07136 0.06586 -0.0235 0.0137 1.0000
17.250 1.4717 0.07582 0.07044 -0.0245 0.0135 1.0000
17.500 1.4644 0.08031 0.07506 -0.0257 0.0133 1.0000
17.750 1.4561 0.08504 0.07991 -0.0270 0.0130 1.0000
18.000 1.4472 0.08991 0.08489 -0.0285 0.0128 1.0000
18.250 1.4377 0.09489 0.09000 -0.0301 0.0126 1.0000
18.500 1.4279 0.10002 0.09523 -0.0318 0.0124 1.0000
18.750 1.4177 0.10526 0.10059 -0.0337 0.0122 1.0000
19.000 1.4078 0.11051 0.10594 -0.0357 0.0120 1.0000
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Polar data table (+)
Polar graphs
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