CLARK Z AIRFOIL (clarkz-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK Z AIRFOIL (clarkz-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.52 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkz-il-1000000-n5.txt Download as CSV file: xf-clarkz-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK Z AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.8488 0.03496 0.03230 -0.0927 0.9944 0.0202
-12.500 -0.8374 0.03161 0.02872 -0.0952 0.9888 0.0203
-12.250 -0.8182 0.02944 0.02639 -0.0969 0.9845 0.0204
-12.000 -0.7982 0.02782 0.02464 -0.0977 0.9792 0.0205
-11.750 -0.7760 0.02643 0.02313 -0.0984 0.9739 0.0207
-11.500 -0.7542 0.02520 0.02177 -0.0987 0.9683 0.0208
-11.250 -0.7326 0.02407 0.02052 -0.0987 0.9616 0.0209
-11.000 -0.7108 0.02303 0.01936 -0.0986 0.9551 0.0210
-10.750 -0.6893 0.02206 0.01827 -0.0982 0.9475 0.0211
-10.500 -0.6668 0.02120 0.01729 -0.0979 0.9408 0.0213
-10.250 -0.6441 0.02044 0.01642 -0.0974 0.9329 0.0215
-10.000 -0.6210 0.01968 0.01553 -0.0970 0.9258 0.0217
-9.750 -0.5981 0.01882 0.01453 -0.0966 0.9175 0.0219
-9.500 -0.5749 0.01800 0.01357 -0.0961 0.9100 0.0220
-9.250 -0.5510 0.01724 0.01267 -0.0957 0.9018 0.0222
-9.000 -0.5268 0.01654 0.01184 -0.0953 0.8939 0.0223
-8.750 -0.5021 0.01588 0.01106 -0.0949 0.8856 0.0225
-8.500 -0.4771 0.01528 0.01033 -0.0946 0.8777 0.0227
-8.250 -0.4517 0.01472 0.00966 -0.0942 0.8691 0.0228
-8.000 -0.4261 0.01421 0.00904 -0.0939 0.8610 0.0230
-7.750 -0.4001 0.01374 0.00847 -0.0936 0.8522 0.0231
-7.500 -0.3741 0.01331 0.00794 -0.0933 0.8441 0.0232
-7.250 -0.3477 0.01291 0.00745 -0.0930 0.8349 0.0234
-7.000 -0.3212 0.01255 0.00700 -0.0927 0.8264 0.0235
-6.750 -0.2945 0.01222 0.00659 -0.0925 0.8169 0.0236
-6.500 -0.2683 0.01177 0.00605 -0.0922 0.8081 0.0238
-6.250 -0.2423 0.01131 0.00550 -0.0918 0.7983 0.0241
-6.000 -0.2155 0.01099 0.00514 -0.0916 0.7886 0.0244
-5.750 -0.1886 0.01075 0.00484 -0.0913 0.7784 0.0247
-5.500 -0.1615 0.01052 0.00456 -0.0911 0.7677 0.0250
-5.250 -0.1344 0.01030 0.00428 -0.0909 0.7577 0.0252
-4.750 -0.0799 0.00990 0.00377 -0.0905 0.7376 0.0257
-4.500 -0.0527 0.00972 0.00353 -0.0902 0.7278 0.0260
-4.250 -0.0254 0.00955 0.00330 -0.0900 0.7173 0.0263
-4.000 0.0020 0.00939 0.00310 -0.0899 0.7071 0.0266
-3.750 0.0293 0.00926 0.00290 -0.0896 0.6964 0.0269
-3.500 0.0569 0.00912 0.00272 -0.0895 0.6857 0.0272
-3.250 0.0844 0.00901 0.00256 -0.0893 0.6759 0.0275
-3.000 0.1119 0.00891 0.00241 -0.0891 0.6657 0.0278
-2.750 0.1395 0.00877 0.00223 -0.0889 0.6560 0.0282
-2.500 0.1669 0.00865 0.00207 -0.0887 0.6461 0.0289
-2.250 0.1946 0.00856 0.00196 -0.0886 0.6358 0.0295
-2.000 0.2222 0.00850 0.00187 -0.0885 0.6262 0.0303
-1.750 0.2498 0.00845 0.00178 -0.0883 0.6157 0.0311
-1.500 0.2776 0.00840 0.00171 -0.0882 0.6050 0.0320
-1.250 0.3052 0.00838 0.00164 -0.0880 0.5947 0.0326
-1.000 0.3327 0.00834 0.00157 -0.0878 0.5835 0.0342
-0.750 0.3603 0.00831 0.00152 -0.0877 0.5720 0.0362
-0.500 0.3878 0.00830 0.00149 -0.0875 0.5605 0.0390
-0.250 0.4152 0.00829 0.00146 -0.0874 0.5488 0.0457
0.000 0.4425 0.00824 0.00145 -0.0872 0.5361 0.0631
0.250 0.4696 0.00820 0.00145 -0.0870 0.5231 0.0904
0.500 0.4968 0.00818 0.00147 -0.0869 0.5109 0.1151
0.750 0.5238 0.00820 0.00150 -0.0867 0.4980 0.1394
1.000 0.5508 0.00820 0.00153 -0.0865 0.4841 0.1692
1.250 0.5774 0.00809 0.00158 -0.0863 0.4710 0.2450
1.500 0.6029 0.00779 0.00165 -0.0861 0.4592 0.4029
1.750 0.6275 0.00743 0.00174 -0.0856 0.4467 0.5919
2.000 0.6501 0.00707 0.00186 -0.0846 0.4345 0.7731
2.250 0.6714 0.00681 0.00202 -0.0827 0.4219 0.9479
2.500 0.7174 0.00703 0.00214 -0.0867 0.4018 0.9931
2.750 0.7549 0.00723 0.00223 -0.0889 0.3844 1.0000
3.250 0.8036 0.00755 0.00241 -0.0875 0.3587 1.0000
3.500 0.8282 0.00772 0.00252 -0.0868 0.3465 1.0000
3.750 0.8527 0.00792 0.00264 -0.0861 0.3328 1.0000
4.000 0.8774 0.00812 0.00276 -0.0855 0.3199 1.0000
4.250 0.9023 0.00832 0.00289 -0.0849 0.3070 1.0000
4.500 0.9274 0.00851 0.00303 -0.0844 0.2948 1.0000
4.750 0.9525 0.00871 0.00317 -0.0839 0.2842 1.0000
5.000 0.9773 0.00893 0.00333 -0.0834 0.2720 1.0000
5.250 1.0022 0.00916 0.00350 -0.0828 0.2593 1.0000
5.500 1.0273 0.00938 0.00367 -0.0824 0.2479 1.0000
5.750 1.0519 0.00963 0.00386 -0.0818 0.2353 1.0000
6.000 1.0760 0.00992 0.00407 -0.0812 0.2204 1.0000
6.250 1.0991 0.01028 0.00433 -0.0805 0.2015 1.0000
6.500 1.1216 0.01069 0.00462 -0.0796 0.1817 1.0000
6.750 1.1442 0.01108 0.00492 -0.0788 0.1638 1.0000
7.000 1.1664 0.01150 0.00524 -0.0780 0.1463 1.0000
7.250 1.1881 0.01194 0.00559 -0.0770 0.1296 1.0000
7.500 1.2098 0.01238 0.00594 -0.0761 0.1151 1.0000
7.750 1.2317 0.01278 0.00628 -0.0752 0.1043 1.0000
8.000 1.2534 0.01318 0.00664 -0.0743 0.0953 1.0000
8.250 1.2747 0.01360 0.00700 -0.0733 0.0876 1.0000
8.500 1.2969 0.01394 0.00733 -0.0725 0.0833 1.0000
8.750 1.3181 0.01432 0.00769 -0.0716 0.0793 1.0000
9.000 1.3396 0.01467 0.00805 -0.0706 0.0762 1.0000
9.250 1.3607 0.01497 0.00837 -0.0696 0.0743 1.0000
9.500 1.3805 0.01532 0.00873 -0.0684 0.0721 1.0000
9.750 1.3991 0.01573 0.00914 -0.0670 0.0693 1.0000
10.000 1.4172 0.01617 0.00958 -0.0656 0.0664 1.0000
10.250 1.4364 0.01654 0.00998 -0.0644 0.0650 1.0000
10.500 1.4549 0.01696 0.01042 -0.0631 0.0628 1.0000
10.750 1.4722 0.01744 0.01092 -0.0617 0.0603 1.0000
11.000 1.4884 0.01801 0.01147 -0.0602 0.0574 1.0000
11.250 1.5057 0.01851 0.01200 -0.0589 0.0554 1.0000
11.500 1.5217 0.01909 0.01259 -0.0575 0.0526 1.0000
11.750 1.5360 0.01979 0.01329 -0.0559 0.0493 1.0000
12.000 1.5513 0.02044 0.01397 -0.0545 0.0468 1.0000
12.250 1.5633 0.02133 0.01484 -0.0528 0.0421 1.0000
12.500 1.5731 0.02237 0.01586 -0.0510 0.0352 1.0000
12.750 1.5713 0.02428 0.01768 -0.0482 0.0207 1.0000
13.000 1.5763 0.02579 0.01920 -0.0462 0.0167 1.0000
13.250 1.5843 0.02714 0.02059 -0.0447 0.0150 1.0000
13.500 1.5926 0.02850 0.02200 -0.0433 0.0140 1.0000
13.750 1.5999 0.02999 0.02354 -0.0419 0.0132 1.0000
14.000 1.6075 0.03150 0.02511 -0.0408 0.0126 1.0000
14.250 1.6152 0.03304 0.02672 -0.0397 0.0122 1.0000
14.500 1.6218 0.03472 0.02847 -0.0387 0.0118 1.0000
14.750 1.6271 0.03657 0.03038 -0.0377 0.0114 1.0000
15.000 1.6310 0.03861 0.03248 -0.0368 0.0110 1.0000
15.250 1.6334 0.04083 0.03477 -0.0360 0.0106 1.0000
15.500 1.6348 0.04327 0.03729 -0.0354 0.0102 1.0000
15.750 1.6383 0.04555 0.03965 -0.0349 0.0100 1.0000
16.000 1.6406 0.04801 0.04219 -0.0345 0.0098 1.0000
16.250 1.6418 0.05065 0.04491 -0.0343 0.0096 1.0000
16.500 1.6418 0.05351 0.04785 -0.0341 0.0093 1.0000
16.750 1.6407 0.05658 0.05100 -0.0341 0.0091 1.0000
17.000 1.6384 0.05984 0.05435 -0.0343 0.0089 1.0000
17.250 1.6347 0.06334 0.05794 -0.0345 0.0088 1.0000
17.500 1.6298 0.06709 0.06178 -0.0349 0.0086 1.0000
17.750 1.6236 0.07110 0.06589 -0.0356 0.0085 1.0000
18.000 1.6158 0.07539 0.07027 -0.0363 0.0083 1.0000
18.250 1.6069 0.07989 0.07487 -0.0372 0.0082 1.0000
18.500 1.5966 0.08471 0.07979 -0.0384 0.0080 1.0000
18.750 1.5882 0.08930 0.08449 -0.0395 0.0080 1.0000
19.000 1.5786 0.09409 0.08939 -0.0408 0.0079 1.0000
19.250 1.5683 0.09907 0.09446 -0.0423 0.0078 1.0000
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