CLARK V AIRFOIL (clarkv-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: CLARK V AIRFOIL (clarkv-il) Reynolds number: 50,000 Max Cl/Cd: 35.49 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkv-il-50000.txt Download as CSV file: xf-clarkv-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3884 0.10313 0.09630 -0.0199 1.0000 0.3075
-7.750 -0.3981 0.10103 0.09429 -0.0178 1.0000 0.3165
-7.500 -0.4211 0.10054 0.09395 -0.0147 1.0000 0.3277
-7.250 -0.4050 0.09661 0.09002 -0.0129 1.0000 0.3400
-7.000 -0.4093 0.09421 0.08768 -0.0103 1.0000 0.3510
-6.750 -0.4586 0.09524 0.08896 -0.0049 1.0000 0.3602
-6.500 -0.4535 0.09228 0.08603 -0.0022 1.0000 0.3755
-6.250 -0.4596 0.09010 0.08392 0.0010 1.0000 0.3915
-6.000 -0.4732 0.08838 0.08230 0.0043 1.0000 0.4083
-5.750 -0.4453 0.08427 0.07815 0.0072 1.0000 0.4305
-5.500 -0.4483 0.08208 0.07603 0.0107 1.0000 0.4500
-5.000 -0.4817 0.05571 0.04851 -0.0336 1.0000 0.1907
-4.750 -0.4577 0.04914 0.04105 -0.0377 1.0000 0.1701
-4.500 -0.4361 0.04548 0.03708 -0.0384 1.0000 0.1652
-4.250 -0.4108 0.04174 0.03268 -0.0397 1.0000 0.1608
-4.000 -0.3870 0.03944 0.02997 -0.0400 1.0000 0.1633
-3.750 -0.3620 0.03733 0.02741 -0.0402 1.0000 0.1662
-3.500 -0.3359 0.03540 0.02500 -0.0404 1.0000 0.1683
-3.250 -0.3094 0.03384 0.02291 -0.0404 1.0000 0.1719
-3.000 -0.2862 0.03257 0.02167 -0.0401 1.0000 0.1808
-2.750 -0.2611 0.03146 0.02034 -0.0399 1.0000 0.1911
-2.500 -0.2356 0.03049 0.01921 -0.0395 1.0000 0.2038
-2.250 -0.2117 0.02966 0.01851 -0.0391 1.0000 0.2255
-2.000 -0.1858 0.02890 0.01783 -0.0389 1.0000 0.2619
-1.750 -0.1577 0.02787 0.01738 -0.0391 1.0000 0.3503
-1.500 -0.1415 0.02475 0.01719 -0.0331 1.0000 0.9552
-1.250 -0.1202 0.02499 0.01673 -0.0332 1.0000 1.0000
-1.000 -0.0986 0.02545 0.01674 -0.0332 1.0000 1.0000
-0.750 -0.0776 0.02595 0.01690 -0.0331 1.0000 1.0000
-0.500 -0.0570 0.02650 0.01715 -0.0330 1.0000 1.0000
-0.250 -0.0367 0.02709 0.01748 -0.0329 1.0000 1.0000
0.000 -0.0167 0.02772 0.01789 -0.0328 1.0000 1.0000
0.250 0.0030 0.02840 0.01837 -0.0327 1.0000 1.0000
0.500 0.0225 0.02913 0.01892 -0.0326 1.0000 1.0000
0.750 0.0418 0.02989 0.01953 -0.0325 1.0000 1.0000
1.000 0.0607 0.03071 0.02022 -0.0325 1.0000 1.0000
1.250 0.0794 0.03157 0.02096 -0.0325 1.0000 1.0000
1.500 0.0977 0.03249 0.02177 -0.0325 1.0000 1.0000
1.750 0.1474 0.03423 0.02339 -0.0384 0.9864 1.0000
2.000 0.1995 0.03595 0.02500 -0.0445 0.9694 1.0000
2.250 0.2398 0.03720 0.02618 -0.0483 0.9520 1.0000
2.500 0.2802 0.03840 0.02734 -0.0519 0.9349 1.0000
2.750 0.3205 0.03952 0.02844 -0.0553 0.9181 1.0000
3.000 0.3610 0.04057 0.02948 -0.0585 0.9014 1.0000
3.250 0.4025 0.04155 0.03047 -0.0617 0.8851 1.0000
3.500 0.4343 0.04236 0.03130 -0.0632 0.8676 1.0000
3.750 0.4648 0.04312 0.03211 -0.0644 0.8494 1.0000
4.000 0.4992 0.04382 0.03288 -0.0660 0.8314 1.0000
4.250 0.5373 0.04438 0.03351 -0.0679 0.8135 1.0000
4.500 0.5794 0.04471 0.03393 -0.0700 0.7959 1.0000
4.750 0.6098 0.04512 0.03445 -0.0704 0.7762 1.0000
5.000 0.6409 0.04539 0.03483 -0.0706 0.7557 1.0000
5.250 0.6843 0.04501 0.03461 -0.0718 0.7367 1.0000
5.500 0.7349 0.04396 0.03373 -0.0732 0.7189 1.0000
5.750 0.7563 0.04419 0.03409 -0.0716 0.6960 1.0000
6.000 0.8021 0.04284 0.03295 -0.0718 0.6774 1.0000
6.250 0.8555 0.04064 0.03098 -0.0722 0.6603 1.0000
6.500 0.9265 0.03739 0.02803 -0.0743 0.6427 1.0000
6.750 0.9605 0.03650 0.02731 -0.0731 0.6178 1.0000
7.000 1.0203 0.03411 0.02512 -0.0744 0.5915 1.0000
7.250 1.0645 0.03286 0.02393 -0.0742 0.5600 1.0000
7.500 1.0986 0.03232 0.02339 -0.0732 0.5263 1.0000
7.750 1.1287 0.03221 0.02323 -0.0718 0.4925 1.0000
8.000 1.1547 0.03254 0.02346 -0.0703 0.4601 1.0000
8.250 1.1763 0.03327 0.02413 -0.0685 0.4299 1.0000
8.500 1.1955 0.03423 0.02507 -0.0664 0.4011 1.0000
8.750 1.2143 0.03536 0.02616 -0.0645 0.3733 1.0000
9.000 1.2330 0.03658 0.02729 -0.0625 0.3456 1.0000
9.250 1.2506 0.03784 0.02841 -0.0605 0.3173 1.0000
9.500 1.2656 0.03908 0.02948 -0.0581 0.2887 1.0000
9.750 1.2674 0.04047 0.03102 -0.0540 0.2638 1.0000
10.000 1.2719 0.04174 0.03221 -0.0504 0.2380 1.0000
10.250 1.2773 0.04305 0.03331 -0.0470 0.2120 1.0000
10.500 1.2766 0.04482 0.03511 -0.0429 0.1894 1.0000
10.750 1.2815 0.04695 0.03711 -0.0398 0.1672 1.0000
11.000 1.2834 0.04941 0.03967 -0.0364 0.1504 1.0000
11.250 1.2888 0.05206 0.04238 -0.0336 0.1372 1.0000
11.500 1.3002 0.05492 0.04528 -0.0318 0.1263 1.0000
11.750 1.2929 0.05781 0.04856 -0.0279 0.1206 1.0000
12.000 1.3049 0.06089 0.05163 -0.0265 0.1135 1.0000
12.250 1.2887 0.06444 0.05562 -0.0224 0.1117 1.0000
12.500 1.2710 0.06827 0.05983 -0.0188 0.1103 1.0000
12.750 1.2499 0.07242 0.06430 -0.0159 0.1095 1.0000
13.000 1.2245 0.07707 0.06926 -0.0136 0.1094 1.0000
13.250 1.1945 0.08246 0.07493 -0.0124 0.1099 1.0000
13.500 1.1614 0.08876 0.08146 -0.0126 0.1110 1.0000
13.750 1.1276 0.09598 0.08886 -0.0142 0.1123 1.0000
14.000 1.0955 0.10407 0.09704 -0.0170 0.1135 1.0000
14.250 1.0673 0.11278 0.10582 -0.0207 0.1145 1.0000
14.500 0.8971 0.16139 0.15405 -0.0560 0.1631 1.0000
14.750 0.8944 0.16826 0.16091 -0.0589 0.1668 1.0000
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Polar data table (+)
Polar graphs
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