CLARK V AIRFOIL (clarkv-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK V AIRFOIL (clarkv-il) Reynolds number: 500,000 Max Cl/Cd: 95.56 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkv-il-500000-n5.txt Download as CSV file: xf-clarkv-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK V 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.9077 0.04840 0.04557 -0.0832 1.0000 0.0119
-13.750 -0.9620 0.03804 0.03483 -0.0915 0.9975 0.0116
-13.500 -0.9578 0.03505 0.03165 -0.0937 0.9941 0.0119
-13.250 -0.9463 0.03284 0.02926 -0.0947 0.9905 0.0123
-13.000 -0.9307 0.03084 0.02705 -0.0958 0.9878 0.0128
-12.750 -0.9120 0.02897 0.02497 -0.0970 0.9860 0.0133
-12.500 -0.8939 0.02727 0.02303 -0.0975 0.9837 0.0138
-12.250 -0.8744 0.02629 0.02198 -0.0974 0.9806 0.0143
-12.000 -0.8494 0.02556 0.02119 -0.0980 0.9787 0.0148
-11.750 -0.8230 0.02484 0.02038 -0.0988 0.9771 0.0154
-11.500 -0.7962 0.02398 0.01938 -0.0998 0.9759 0.0162
-11.250 -0.7688 0.02301 0.01824 -0.1008 0.9749 0.0170
-11.000 -0.7467 0.02214 0.01719 -0.1006 0.9722 0.0177
-10.750 -0.7231 0.02164 0.01666 -0.1005 0.9692 0.0183
-10.500 -0.6948 0.02129 0.01627 -0.1011 0.9674 0.0190
-10.250 -0.6660 0.02083 0.01574 -0.1019 0.9659 0.0198
-10.000 -0.6375 0.02021 0.01499 -0.1027 0.9645 0.0206
-9.750 -0.6085 0.01958 0.01423 -0.1036 0.9633 0.0215
-9.500 -0.5785 0.01904 0.01354 -0.1045 0.9622 0.0222
-9.250 -0.5613 0.01835 0.01276 -0.1028 0.9570 0.0229
-9.000 -0.5352 0.01781 0.01218 -0.1030 0.9543 0.0237
-8.750 -0.5069 0.01739 0.01170 -0.1034 0.9523 0.0244
-8.500 -0.4777 0.01696 0.01121 -0.1041 0.9506 0.0253
-8.250 -0.4482 0.01647 0.01063 -0.1048 0.9491 0.0262
-8.000 -0.4266 0.01605 0.01012 -0.1037 0.9444 0.0270
-7.750 -0.4010 0.01564 0.00962 -0.1034 0.9408 0.0277
-7.500 -0.3729 0.01525 0.00913 -0.1036 0.9381 0.0282
-7.250 -0.3459 0.01442 0.00822 -0.1038 0.9357 0.0290
-7.000 -0.3198 0.01387 0.00764 -0.1037 0.9326 0.0300
-6.750 -0.2964 0.01349 0.00723 -0.1029 0.9274 0.0307
-6.500 -0.2695 0.01308 0.00675 -0.1029 0.9237 0.0314
-6.250 -0.2411 0.01267 0.00629 -0.1031 0.9207 0.0322
-6.000 -0.2144 0.01232 0.00589 -0.1030 0.9168 0.0330
-5.750 -0.1893 0.01201 0.00555 -0.1025 0.9114 0.0339
-5.500 -0.1616 0.01168 0.00515 -0.1025 0.9074 0.0345
-5.250 -0.1325 0.01135 0.00476 -0.1028 0.9041 0.0351
-5.000 -0.1078 0.01110 0.00447 -0.1022 0.8978 0.0355
-4.750 -0.0805 0.01072 0.00405 -0.1021 0.8929 0.0369
-4.500 -0.0522 0.01043 0.00373 -0.1022 0.8886 0.0383
-4.250 -0.0260 0.01021 0.00350 -0.1019 0.8822 0.0399
-4.000 0.0024 0.00999 0.00325 -0.1020 0.8771 0.0420
-3.750 0.0298 0.00982 0.00304 -0.1019 0.8712 0.0443
-3.500 0.0572 0.00960 0.00284 -0.1018 0.8649 0.0496
-3.250 0.0854 0.00941 0.00265 -0.1019 0.8592 0.0574
-3.000 0.1124 0.00925 0.00251 -0.1017 0.8521 0.0682
-2.750 0.1408 0.00910 0.00235 -0.1018 0.8461 0.0795
-2.500 0.1675 0.00894 0.00223 -0.1016 0.8386 0.0929
-2.250 0.1952 0.00875 0.00210 -0.1016 0.8320 0.1182
-2.000 0.2218 0.00858 0.00201 -0.1014 0.8242 0.1480
-1.750 0.2491 0.00839 0.00191 -0.1014 0.8170 0.1845
-1.500 0.2748 0.00811 0.00185 -0.1011 0.8088 0.2521
-1.250 0.3013 0.00788 0.00180 -0.1009 0.8011 0.3227
-1.000 0.3272 0.00770 0.00177 -0.1006 0.7914 0.3774
-0.750 0.3529 0.00754 0.00174 -0.1002 0.7792 0.4338
-0.500 0.3778 0.00737 0.00172 -0.0996 0.7644 0.4992
-0.250 0.4029 0.00726 0.00170 -0.0990 0.7501 0.5513
0.000 0.4277 0.00712 0.00171 -0.0984 0.7385 0.6150
0.250 0.4511 0.00691 0.00175 -0.0974 0.7268 0.7040
0.500 0.4726 0.00667 0.00184 -0.0958 0.7150 0.8119
0.750 0.4962 0.00660 0.00195 -0.0944 0.7029 0.8952
1.000 0.5283 0.00668 0.00202 -0.0951 0.6899 0.9391
1.250 0.5627 0.00681 0.00208 -0.0964 0.6739 0.9624
1.500 0.5960 0.00698 0.00213 -0.0976 0.6520 0.9763
1.750 0.6279 0.00716 0.00219 -0.0986 0.6285 0.9858
2.000 0.6613 0.00734 0.00227 -0.0999 0.6077 0.9930
2.250 0.6957 0.00752 0.00235 -0.1015 0.5887 0.9985
2.500 0.7206 0.00768 0.00244 -0.1010 0.5713 1.0000
2.750 0.7419 0.00784 0.00253 -0.0996 0.5551 1.0000
3.000 0.7630 0.00801 0.00262 -0.0983 0.5381 1.0000
3.250 0.7836 0.00820 0.00274 -0.0968 0.5186 1.0000
3.500 0.8038 0.00843 0.00287 -0.0952 0.4968 1.0000
3.750 0.8243 0.00866 0.00302 -0.0938 0.4742 1.0000
4.000 0.8450 0.00892 0.00317 -0.0924 0.4515 1.0000
4.250 0.8644 0.00925 0.00337 -0.0908 0.4210 1.0000
4.500 0.8829 0.00966 0.00360 -0.0890 0.3851 1.0000
4.750 0.9022 0.01005 0.00384 -0.0875 0.3540 1.0000
5.000 0.9231 0.01039 0.00408 -0.0862 0.3314 1.0000
5.500 0.9657 0.01104 0.00458 -0.0839 0.2940 1.0000
5.750 0.9871 0.01137 0.00484 -0.0828 0.2753 1.0000
6.000 1.0086 0.01169 0.00512 -0.0818 0.2587 1.0000
6.250 1.0299 0.01202 0.00540 -0.0807 0.2428 1.0000
6.500 1.0499 0.01243 0.00571 -0.0793 0.2227 1.0000
6.750 1.0687 0.01286 0.00604 -0.0778 0.2015 1.0000
7.000 1.0872 0.01329 0.00640 -0.0763 0.1830 1.0000
7.250 1.1053 0.01375 0.00678 -0.0747 0.1656 1.0000
7.500 1.1237 0.01421 0.00718 -0.0731 0.1500 1.0000
7.750 1.1421 0.01468 0.00758 -0.0716 0.1349 1.0000
8.000 1.1600 0.01518 0.00801 -0.0701 0.1177 1.0000
8.250 1.1763 0.01579 0.00852 -0.0683 0.0978 1.0000
8.500 1.1928 0.01639 0.00905 -0.0666 0.0842 1.0000
8.750 1.2100 0.01694 0.00958 -0.0650 0.0738 1.0000
9.000 1.2264 0.01755 0.01015 -0.0634 0.0628 1.0000
9.250 1.2406 0.01830 0.01082 -0.0614 0.0485 1.0000
9.500 1.2533 0.01916 0.01160 -0.0593 0.0339 1.0000
9.750 1.2658 0.02003 0.01243 -0.0572 0.0242 1.0000
10.000 1.2794 0.02084 0.01323 -0.0554 0.0195 1.0000
10.250 1.2939 0.02159 0.01402 -0.0536 0.0173 1.0000
10.500 1.3070 0.02245 0.01491 -0.0518 0.0154 1.0000
10.750 1.3215 0.02321 0.01574 -0.0502 0.0144 1.0000
11.000 1.3349 0.02405 0.01665 -0.0485 0.0134 1.0000
11.250 1.3470 0.02499 0.01765 -0.0467 0.0126 1.0000
11.500 1.3575 0.02608 0.01879 -0.0448 0.0118 1.0000
11.750 1.3682 0.02715 0.01995 -0.0430 0.0113 1.0000
12.000 1.3793 0.02822 0.02110 -0.0413 0.0109 1.0000
12.250 1.3894 0.02937 0.02234 -0.0397 0.0105 1.0000
12.500 1.3986 0.03062 0.02368 -0.0380 0.0101 1.0000
12.750 1.4070 0.03197 0.02511 -0.0364 0.0097 1.0000
13.000 1.4142 0.03344 0.02666 -0.0348 0.0094 1.0000
13.250 1.4193 0.03513 0.02843 -0.0332 0.0090 1.0000
13.500 1.4205 0.03722 0.03061 -0.0315 0.0087 1.0000
13.750 1.4260 0.03899 0.03247 -0.0302 0.0085 1.0000
14.000 1.4304 0.04090 0.03450 -0.0290 0.0083 1.0000
14.250 1.4334 0.04302 0.03672 -0.0279 0.0081 1.0000
14.500 1.4354 0.04533 0.03915 -0.0270 0.0079 1.0000
14.750 1.4365 0.04784 0.04177 -0.0262 0.0077 1.0000
15.000 1.4364 0.05056 0.04460 -0.0256 0.0075 1.0000
15.250 1.4354 0.05347 0.04763 -0.0252 0.0074 1.0000
15.500 1.4335 0.05663 0.05090 -0.0250 0.0072 1.0000
15.750 1.4304 0.06004 0.05443 -0.0251 0.0071 1.0000
16.000 1.4265 0.06367 0.05817 -0.0253 0.0070 1.0000
16.250 1.4211 0.06762 0.06223 -0.0258 0.0069 1.0000
16.500 1.4143 0.07188 0.06661 -0.0266 0.0068 1.0000
16.750 1.4063 0.07647 0.07133 -0.0276 0.0067 1.0000
17.000 1.3965 0.08144 0.07642 -0.0289 0.0067 1.0000
17.250 1.3853 0.08673 0.08183 -0.0305 0.0066 1.0000
17.500 1.3732 0.09232 0.08755 -0.0323 0.0065 1.0000
17.750 1.3599 0.09824 0.09359 -0.0344 0.0065 1.0000
18.000 1.3459 0.10436 0.09983 -0.0368 0.0064 1.0000
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