PMC19 Smoothed (pmc19sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: PMC19 Smoothed (pmc19sm-il) Reynolds number: 500,000 Max Cl/Cd: 73.98 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-pmc19sm-il-500000-n5.txt Download as CSV file: xf-pmc19sm-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: PMC19 Smoothed
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6197 0.09178 0.08976 0.0218 1.0000 0.0089
-8.250 -0.6217 0.08705 0.08505 0.0178 1.0000 0.0087
-8.000 -0.6273 0.08199 0.07997 0.0125 1.0000 0.0085
-7.750 -0.6270 0.07719 0.07512 0.0091 1.0000 0.0083
-7.500 -0.6240 0.07242 0.07028 0.0064 1.0000 0.0081
-7.250 -0.6183 0.06767 0.06543 0.0044 1.0000 0.0079
-7.000 -0.6097 0.06296 0.06060 0.0028 1.0000 0.0077
-6.750 -0.5985 0.05835 0.05584 0.0017 1.0000 0.0077
-6.500 -0.5847 0.05388 0.05121 0.0010 1.0000 0.0077
-6.250 -0.5686 0.04952 0.04667 0.0007 1.0000 0.0079
-6.000 -0.5428 0.04467 0.04145 -0.0011 0.8924 0.0082
-5.750 -0.5255 0.04075 0.03713 0.0000 0.8447 0.0084
-5.500 -0.5055 0.03641 0.03238 0.0011 0.8135 0.0089
-5.250 -0.4837 0.03206 0.02759 0.0022 0.7878 0.0092
-5.000 -0.4620 0.02723 0.02228 0.0034 0.7656 0.0092
-4.750 -0.4401 0.02005 0.01435 0.0052 0.7473 0.0097
-4.500 -0.4146 0.01847 0.01248 0.0057 0.7241 0.0102
-4.250 -0.3887 0.01681 0.01051 0.0063 0.7024 0.0109
-4.000 -0.3628 0.01520 0.00858 0.0068 0.6816 0.0117
-3.750 -0.3368 0.01407 0.00720 0.0073 0.6614 0.0126
-3.500 -0.3102 0.01356 0.00649 0.0076 0.6413 0.0134
-3.250 -0.2839 0.01297 0.00581 0.0078 0.6220 0.0147
-3.000 -0.2570 0.01264 0.00537 0.0080 0.6029 0.0157
-2.750 -0.2303 0.01222 0.00482 0.0082 0.5852 0.0169
-2.500 -0.2034 0.01182 0.00429 0.0084 0.5676 0.0182
-2.250 -0.1763 0.01150 0.00385 0.0085 0.5505 0.0192
-2.000 -0.1493 0.01117 0.00347 0.0085 0.5344 0.0215
-1.750 -0.1218 0.01098 0.00320 0.0085 0.5180 0.0232
-1.500 -0.0943 0.01076 0.00287 0.0085 0.5022 0.0249
-1.250 -0.0665 0.01063 0.00265 0.0085 0.4878 0.0266
-1.000 -0.0389 0.01034 0.00228 0.0085 0.4741 0.0294
-0.750 -0.0110 0.01020 0.00208 0.0084 0.4602 0.0322
-0.500 0.0170 0.01011 0.00191 0.0083 0.4468 0.0355
-0.250 0.0451 0.01004 0.00177 0.0083 0.4348 0.0384
0.000 0.0732 0.00994 0.00164 0.0082 0.4235 0.0465
0.250 0.1014 0.00989 0.00155 0.0080 0.4120 0.0553
0.500 0.1294 0.00981 0.00149 0.0079 0.4005 0.0806
0.750 0.1526 0.00810 0.00125 0.0077 0.3910 0.6078
1.000 0.1791 0.00791 0.00130 0.0079 0.3821 0.6914
1.250 0.2062 0.00788 0.00136 0.0081 0.3727 0.7328
1.500 0.2332 0.00787 0.00143 0.0084 0.3637 0.7683
1.750 0.2602 0.00791 0.00151 0.0086 0.3551 0.7951
2.000 0.2875 0.00796 0.00158 0.0088 0.3471 0.8141
2.250 0.3153 0.00803 0.00164 0.0088 0.3401 0.8226
2.500 0.3435 0.00811 0.00170 0.0087 0.3324 0.8291
2.750 0.3714 0.00819 0.00176 0.0087 0.3252 0.8350
3.000 0.3994 0.00827 0.00184 0.0086 0.3181 0.8416
3.250 0.4273 0.00836 0.00194 0.0085 0.3123 0.8481
3.500 0.4551 0.00844 0.00204 0.0085 0.3060 0.8550
3.750 0.4828 0.00856 0.00215 0.0085 0.2998 0.8620
4.000 0.5105 0.00863 0.00226 0.0085 0.2940 0.8694
4.250 0.5380 0.00874 0.00241 0.0085 0.2885 0.8769
4.500 0.5654 0.00884 0.00255 0.0085 0.2830 0.8851
4.750 0.5925 0.00897 0.00267 0.0086 0.2715 0.8935
5.250 0.6464 0.00923 0.00296 0.0087 0.2466 0.9134
5.500 0.6734 0.00937 0.00314 0.0088 0.2338 0.9253
5.750 0.7008 0.00956 0.00332 0.0087 0.2173 0.9398
6.000 0.7309 0.00988 0.00356 0.0079 0.1864 0.9573
6.250 0.7592 0.01169 0.00464 0.0061 0.0453 1.0000
6.500 0.7857 0.01222 0.00516 0.0059 0.0305 1.0000
6.750 0.8127 0.01262 0.00560 0.0057 0.0249 1.0000
7.000 0.8392 0.01311 0.00610 0.0056 0.0206 1.0000
7.250 0.8657 0.01359 0.00665 0.0055 0.0183 1.0000
7.500 0.8920 0.01404 0.00718 0.0054 0.0163 1.0000
7.750 0.9178 0.01460 0.00777 0.0053 0.0143 1.0000
8.000 0.9424 0.01542 0.00869 0.0053 0.0129 1.0000
8.250 0.9677 0.01602 0.00938 0.0053 0.0123 1.0000
8.500 0.9923 0.01670 0.01016 0.0053 0.0116 1.0000
8.750 1.0164 0.01744 0.01101 0.0053 0.0109 1.0000
9.000 1.0404 0.01813 0.01177 0.0053 0.0102 1.0000
9.250 1.0638 0.01887 0.01256 0.0053 0.0094 1.0000
9.500 1.0831 0.02027 0.01408 0.0055 0.0087 1.0000
9.750 1.1042 0.02127 0.01518 0.0057 0.0084 1.0000
10.000 1.1244 0.02233 0.01637 0.0060 0.0081 1.0000
10.250 1.1432 0.02351 0.01770 0.0063 0.0078 1.0000
10.500 1.1609 0.02475 0.01906 0.0066 0.0074 1.0000
10.750 1.1781 0.02595 0.02037 0.0069 0.0070 1.0000
11.000 1.1949 0.02710 0.02161 0.0072 0.0067 1.0000
11.250 1.2108 0.02825 0.02285 0.0073 0.0063 1.0000
11.500 1.2232 0.02971 0.02440 0.0075 0.0060 1.0000
11.750 1.2255 0.03193 0.02674 0.0078 0.0058 1.0000
12.000 1.2206 0.03553 0.03050 0.0065 0.0056 1.0000
12.250 1.2222 0.03871 0.03383 0.0049 0.0056 1.0000
12.500 1.2236 0.04202 0.03729 0.0032 0.0055 1.0000
12.750 1.2232 0.04562 0.04104 0.0014 0.0054 1.0000
13.000 1.2209 0.04947 0.04506 -0.0004 0.0053 1.0000
13.250 1.2165 0.05362 0.04935 -0.0022 0.0052 1.0000
13.500 1.2106 0.05799 0.05388 -0.0041 0.0051 1.0000
13.750 1.2033 0.06259 0.05861 -0.0061 0.0050 1.0000
14.000 1.1944 0.06746 0.06363 -0.0082 0.0050 1.0000
14.250 1.1842 0.07259 0.06890 -0.0105 0.0049 1.0000
14.500 1.1728 0.07797 0.07442 -0.0129 0.0049 1.0000
14.750 1.1606 0.08366 0.08026 -0.0155 0.0048 1.0000
15.000 1.1479 0.08975 0.08648 -0.0184 0.0048 1.0000
15.250 1.1344 0.09618 0.09305 -0.0216 0.0048 1.0000
15.500 1.1201 0.10301 0.10003 -0.0250 0.0047 1.0000
15.750 1.1047 0.11024 0.10739 -0.0286 0.0047 1.0000
16.000 1.0881 0.11797 0.11526 -0.0326 0.0047 1.0000
16.250 1.0703 0.12629 0.12371 -0.0369 0.0047 1.0000
16.500 1.0506 0.13535 0.13291 -0.0416 0.0047 1.0000
16.750 1.0282 0.14569 0.14338 -0.0471 0.0048 1.0000
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