CLARK Z AIRFOIL (clarkz-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK Z AIRFOIL (clarkz-il) Reynolds number: 50,000 Max Cl/Cd: 30.41 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkz-il-50000.txt Download as CSV file: xf-clarkz-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3063 0.11202 0.10479 -0.0302 1.0000 0.2150
-8.750 -0.3119 0.11053 0.10339 -0.0298 1.0000 0.2227
-8.500 -0.3498 0.11223 0.10532 -0.0296 1.0000 0.2256
-8.250 -0.3078 0.10506 0.09808 -0.0277 1.0000 0.2341
-8.000 -0.3285 0.10483 0.09802 -0.0263 1.0000 0.2414
-7.750 -0.3312 0.10207 0.09537 -0.0246 1.0000 0.2460
-7.500 -0.3253 0.09951 0.09286 -0.0224 1.0000 0.2549
-7.250 -0.3656 0.10058 0.09415 -0.0187 1.0000 0.2594
-7.000 -0.3461 0.09623 0.08982 -0.0170 1.0000 0.2673
-6.750 -0.3695 0.09584 0.08957 -0.0132 1.0000 0.2745
-6.500 -0.4220 0.09723 0.09118 -0.0120 1.0000 0.2779
-6.250 -0.3889 0.09231 0.08624 -0.0074 1.0000 0.2898
-6.000 -0.4182 0.09142 0.08551 -0.0061 1.0000 0.2970
-5.750 -0.4172 0.08934 0.08348 -0.0029 1.0000 0.3102
-5.500 -0.4157 0.08680 0.08101 0.0003 1.0000 0.3219
-5.250 -0.4253 0.08490 0.07920 0.0026 1.0000 0.3357
-5.000 -0.4317 0.08297 0.07735 0.0051 1.0000 0.3524
-4.750 -0.4338 0.08097 0.07542 0.0082 1.0000 0.3714
-4.500 -0.4363 0.07909 0.07361 0.0114 1.0000 0.3933
-4.250 -0.4437 0.07723 0.07183 0.0143 1.0000 0.4200
-4.000 -0.4406 0.07528 0.06994 0.0190 1.0000 0.4467
-3.750 -0.4405 0.07338 0.06811 0.0241 1.0000 0.4800
-3.250 -0.1659 0.06097 0.05533 0.0209 1.0000 0.8612
-3.000 -0.1570 0.05919 0.05359 0.0211 1.0000 0.8853
-2.750 -0.1932 0.05895 0.05350 0.0275 1.0000 0.8605
-2.500 -0.2531 0.04665 0.03845 -0.0384 1.0000 0.1892
-2.250 -0.2288 0.04430 0.03587 -0.0395 1.0000 0.1815
-2.000 -0.1992 0.04235 0.03325 -0.0410 1.0000 0.1711
-1.750 -0.1750 0.04083 0.03147 -0.0417 1.0000 0.1678
-1.500 -0.1272 0.03950 0.02966 -0.0462 0.9935 0.1665
-1.250 -0.0705 0.03868 0.02831 -0.0520 0.9825 0.1714
-1.000 -0.0198 0.03783 0.02713 -0.0566 0.9709 0.1761
-0.750 0.0249 0.03731 0.02649 -0.0602 0.9586 0.1860
-0.500 0.0675 0.03692 0.02601 -0.0631 0.9461 0.2027
-0.250 0.1123 0.03651 0.02560 -0.0662 0.9339 0.2309
0.000 0.1650 0.03534 0.02508 -0.0706 0.9234 0.3358
0.250 0.1976 0.03324 0.02461 -0.0696 0.9110 1.0000
0.500 0.2329 0.03404 0.02499 -0.0715 0.8961 1.0000
0.750 0.2672 0.03482 0.02548 -0.0732 0.8813 1.0000
1.000 0.3008 0.03560 0.02603 -0.0748 0.8665 1.0000
1.250 0.3344 0.03636 0.02659 -0.0763 0.8518 1.0000
1.500 0.3682 0.03711 0.02718 -0.0778 0.8375 1.0000
1.750 0.4043 0.03778 0.02770 -0.0794 0.8235 1.0000
2.000 0.4461 0.03830 0.02810 -0.0816 0.8106 1.0000
2.250 0.4714 0.03905 0.02877 -0.0816 0.7954 1.0000
2.500 0.4960 0.03986 0.02952 -0.0815 0.7806 1.0000
2.750 0.5203 0.04071 0.03031 -0.0814 0.7660 1.0000
3.000 0.5459 0.04153 0.03108 -0.0813 0.7518 1.0000
3.250 0.5740 0.04228 0.03180 -0.0815 0.7386 1.0000
3.750 0.6371 0.04336 0.03284 -0.0823 0.7134 1.0000
4.000 0.6532 0.04461 0.03409 -0.0812 0.6992 1.0000
4.250 0.6710 0.04581 0.03529 -0.0803 0.6856 1.0000
4.500 0.6972 0.04662 0.03612 -0.0801 0.6737 1.0000
4.750 0.7374 0.04648 0.03601 -0.0806 0.6633 1.0000
5.000 0.7439 0.04845 0.03800 -0.0790 0.6491 1.0000
5.250 0.7542 0.05026 0.03983 -0.0777 0.6357 1.0000
5.500 0.7759 0.05133 0.04093 -0.0770 0.6241 1.0000
5.750 0.8175 0.05081 0.04050 -0.0771 0.6142 1.0000
6.000 0.8170 0.05353 0.04325 -0.0754 0.6000 1.0000
6.250 0.8209 0.05600 0.04575 -0.0740 0.5868 1.0000
6.500 0.9000 0.05192 0.04183 -0.0745 0.5800 1.0000
6.750 0.8911 0.05544 0.04539 -0.0726 0.5650 1.0000
7.000 0.8854 0.05882 0.04881 -0.0710 0.5504 1.0000
7.250 0.8855 0.06171 0.05175 -0.0697 0.5365 1.0000
7.500 0.8966 0.06349 0.05360 -0.0683 0.5227 1.0000
7.750 0.9235 0.06346 0.05368 -0.0667 0.5085 1.0000
8.000 1.0490 0.05180 0.04226 -0.0646 0.4932 1.0000
8.250 1.1180 0.04712 0.03767 -0.0640 0.4742 1.0000
8.500 1.1745 0.04413 0.03472 -0.0638 0.4546 1.0000
8.750 1.2293 0.04167 0.03215 -0.0640 0.4327 1.0000
9.000 1.2390 0.04265 0.03326 -0.0611 0.4119 1.0000
9.250 1.2726 0.04193 0.03243 -0.0600 0.3874 1.0000
9.500 1.2885 0.04263 0.03312 -0.0576 0.3642 1.0000
9.750 1.3054 0.04343 0.03390 -0.0554 0.3417 1.0000
10.000 1.3337 0.04386 0.03411 -0.0545 0.3199 1.0000
10.250 1.3438 0.04545 0.03575 -0.0521 0.3031 1.0000
10.500 1.3604 0.04694 0.03722 -0.0505 0.2882 1.0000
10.750 1.3589 0.04945 0.03997 -0.0474 0.2776 1.0000
11.000 1.3615 0.05197 0.04267 -0.0449 0.2684 1.0000
11.250 1.3894 0.05318 0.04379 -0.0446 0.2575 1.0000
11.500 1.3602 0.05725 0.04827 -0.0398 0.2534 1.0000
11.750 1.3425 0.06081 0.05205 -0.0363 0.2488 1.0000
12.000 1.3662 0.06270 0.05394 -0.0359 0.2418 1.0000
12.250 1.3156 0.06877 0.06029 -0.0318 0.2414 1.0000
12.500 1.2443 0.07846 0.07018 -0.0306 0.2422 1.0000
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Polar data table (+)
Polar graphs
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