PMC19 Smoothed (pmc19sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: PMC19 Smoothed (pmc19sm-il) Reynolds number: 100,000 Max Cl/Cd: 44.55 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-pmc19sm-il-100000.txt Download as CSV file: xf-pmc19sm-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5974 0.09284 0.08852 0.0136 1.0000 0.0616
-7.750 -0.6010 0.08865 0.08429 0.0087 1.0000 0.0628
-7.500 -0.6034 0.08578 0.08122 0.0037 1.0000 0.0642
-7.250 -0.6030 0.08459 0.07966 0.0008 1.0000 0.0650
-7.000 -0.5937 0.07709 0.07226 0.0000 1.0000 0.0660
-6.750 -0.5812 0.07134 0.06668 0.0004 1.0000 0.0681
-6.500 -0.5697 0.06737 0.06264 -0.0001 1.0000 0.0708
-6.250 -0.5565 0.06386 0.05897 -0.0011 1.0000 0.0747
-6.000 -0.5400 0.06379 0.05816 -0.0025 1.0000 0.0797
-5.750 -0.5261 0.05663 0.05130 -0.0030 1.0000 0.0821
-5.500 -0.5090 0.05304 0.04766 -0.0032 1.0000 0.0870
-5.250 -0.4885 0.05073 0.04489 -0.0037 1.0000 0.0951
-5.000 -0.4703 0.04663 0.04086 -0.0039 1.0000 0.1009
-4.750 -0.4219 0.02792 0.02254 -0.0065 1.0000 0.1147
-4.500 -0.4042 0.02485 0.01928 -0.0065 1.0000 0.1304
-4.250 -0.4089 0.03811 0.03168 -0.0046 1.0000 0.1518
-4.000 -0.3906 0.03453 0.02814 -0.0048 1.0000 0.1825
-3.750 -0.3710 0.03172 0.02518 -0.0048 1.0000 0.2221
-3.500 -0.3481 0.02878 0.02215 -0.0048 1.0000 0.2504
-3.250 -0.3228 0.02574 0.01912 -0.0049 1.0000 0.2693
-3.000 -0.2918 0.02388 0.01699 -0.0050 1.0000 0.2693
-2.750 -0.2413 0.02563 0.01770 -0.0039 1.0000 0.1640
-2.500 -0.2102 0.02453 0.01619 -0.0020 1.0000 0.1066
-2.250 -0.1558 0.02182 0.01320 -0.0060 0.9684 0.0908
-2.000 -0.1041 0.02041 0.01147 -0.0096 0.9329 0.0931
-1.750 -0.0682 0.01909 0.01000 -0.0100 0.8954 0.0938
-1.500 -0.0443 0.01793 0.00885 -0.0083 0.8608 0.0963
-1.250 -0.0231 0.01730 0.00821 -0.0061 0.8300 0.1035
-1.000 -0.0025 0.01669 0.00756 -0.0039 0.8018 0.1117
-0.750 0.0197 0.01626 0.00695 -0.0022 0.7752 0.1206
-0.500 0.0427 0.01573 0.00627 -0.0009 0.7502 0.1397
-0.250 0.0585 0.01349 0.00569 0.0011 0.7297 0.6171
0.000 0.0560 0.01354 0.00648 0.0118 0.7115 0.8716
0.250 0.0975 0.01386 0.00659 0.0140 0.6877 0.9631
0.500 0.1962 0.01416 0.00641 0.0010 0.6544 1.0000
0.750 0.2193 0.01418 0.00625 0.0013 0.6340 1.0000
1.000 0.2419 0.01423 0.00611 0.0018 0.6160 1.0000
1.250 0.2644 0.01431 0.00602 0.0023 0.5992 1.0000
1.500 0.2870 0.01441 0.00601 0.0028 0.5821 1.0000
1.750 0.3091 0.01455 0.00603 0.0033 0.5666 1.0000
2.000 0.3309 0.01471 0.00609 0.0040 0.5523 1.0000
2.250 0.3524 0.01490 0.00619 0.0047 0.5389 1.0000
2.500 0.3739 0.01511 0.00630 0.0055 0.5266 1.0000
2.750 0.3957 0.01536 0.00647 0.0062 0.5145 1.0000
3.000 0.4188 0.01566 0.00674 0.0067 0.5024 1.0000
3.250 0.4433 0.01599 0.00706 0.0070 0.4909 1.0000
3.500 0.4687 0.01636 0.00738 0.0071 0.4806 1.0000
3.750 0.4947 0.01673 0.00768 0.0073 0.4713 1.0000
4.000 0.5213 0.01716 0.00816 0.0071 0.4605 1.0000
4.250 0.5481 0.01762 0.00868 0.0070 0.4511 1.0000
4.500 0.5749 0.01806 0.00909 0.0070 0.4430 1.0000
4.750 0.6020 0.01860 0.00977 0.0067 0.4335 1.0000
5.000 0.6289 0.01912 0.01030 0.0067 0.4258 1.0000
5.250 0.6559 0.01969 0.01102 0.0064 0.4173 1.0000
5.500 0.6828 0.02033 0.01181 0.0063 0.4098 1.0000
5.750 0.7097 0.02092 0.01252 0.0062 0.4021 1.0000
6.000 0.7361 0.02156 0.01334 0.0060 0.3931 1.0000
6.250 0.7619 0.02149 0.01329 0.0065 0.3777 1.0000
6.500 0.7877 0.02108 0.01286 0.0072 0.3595 1.0000
6.750 0.8134 0.02079 0.01253 0.0078 0.3424 1.0000
7.000 0.8385 0.02038 0.01236 0.0083 0.3199 1.0000
7.250 0.8630 0.01937 0.01152 0.0091 0.2805 1.0000
7.500 0.8811 0.02061 0.01187 0.0093 0.1036 1.0000
7.750 0.8978 0.02320 0.01427 0.0095 0.0756 1.0000
8.000 0.9161 0.02510 0.01628 0.0099 0.0656 1.0000
8.250 0.9311 0.02721 0.01843 0.0106 0.0613 1.0000
8.500 0.9498 0.02882 0.02015 0.0117 0.0585 1.0000
8.750 0.9694 0.03059 0.02195 0.0128 0.0561 1.0000
9.000 0.9894 0.03267 0.02397 0.0137 0.0527 1.0000
9.250 1.0114 0.03613 0.02734 0.0145 0.0498 1.0000
9.500 1.0336 0.03868 0.03015 0.0152 0.0492 1.0000
9.750 1.0539 0.04177 0.03355 0.0159 0.0491 1.0000
10.000 1.0708 0.04549 0.03762 0.0165 0.0494 1.0000
10.250 1.0848 0.05027 0.04271 0.0169 0.0499 1.0000
10.500 1.0939 0.05455 0.04740 0.0174 0.0501 1.0000
10.750 1.0967 0.05875 0.05198 0.0179 0.0500 1.0000
11.000 1.0967 0.06289 0.05651 0.0182 0.0501 1.0000
11.250 1.0951 0.06541 0.05938 0.0188 0.0506 1.0000
11.500 1.0797 0.06760 0.06199 0.0192 0.0518 1.0000
11.750 1.0491 0.07200 0.06670 0.0166 0.0525 1.0000
12.000 1.0036 0.08018 0.07525 0.0086 0.0547 1.0000
12.250 0.9675 0.09001 0.08528 0.0004 0.0573 1.0000
12.500 0.9397 0.09958 0.09493 -0.0064 0.0591 1.0000
12.750 0.9210 0.10809 0.10346 -0.0110 0.0606 1.0000
13.000 0.7535 0.10603 0.10155 -0.0011 0.0583 1.0000
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Polar data table (+)
Polar graphs
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