PMC19 Smoothed (pmc19sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: PMC19 Smoothed (pmc19sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.75 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-pmc19sm-il-1000000.txt Download as CSV file: xf-pmc19sm-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6172 0.09154 0.09011 0.0191 1.0000 0.0092
-8.250 -0.6224 0.08614 0.08471 0.0131 1.0000 0.0092
-8.000 -0.6237 0.08153 0.08005 0.0098 1.0000 0.0092
-7.750 -0.6208 0.07694 0.07539 0.0073 1.0000 0.0092
-7.500 -0.6155 0.07244 0.07082 0.0055 1.0000 0.0093
-7.250 -0.6201 0.06492 0.06318 0.0032 1.0000 0.0095
-7.000 -0.6114 0.06089 0.05906 0.0023 1.0000 0.0096
-6.750 -0.5984 0.05764 0.05574 0.0017 1.0000 0.0098
-6.500 -0.5835 0.05449 0.05251 0.0011 1.0000 0.0100
-6.250 -0.5669 0.05139 0.04931 0.0007 1.0000 0.0103
-6.000 -0.5487 0.04829 0.04610 0.0004 1.0000 0.0106
-5.750 -0.5289 0.04513 0.04280 0.0002 1.0000 0.0113
-5.500 -0.4917 0.04228 0.03960 -0.0004 0.9025 0.0132
-5.250 -0.4725 0.03916 0.03612 0.0008 0.8506 0.0133
-5.000 -0.4516 0.03592 0.03257 0.0017 0.8174 0.0133
-4.750 -0.4295 0.03272 0.02907 0.0024 0.7901 0.0133
-4.000 -0.3641 0.01556 0.01032 0.0063 0.7305 0.0119
-3.750 -0.3377 0.01372 0.00817 0.0069 0.7095 0.0129
-3.500 -0.3102 0.01345 0.00774 0.0071 0.6872 0.0133
-3.250 -0.2862 0.01118 0.00519 0.0079 0.6680 0.0146
-3.000 -0.2589 0.01091 0.00485 0.0080 0.6480 0.0155
-2.750 -0.2315 0.01070 0.00454 0.0081 0.6281 0.0167
-2.500 -0.2036 0.01061 0.00438 0.0081 0.6083 0.0182
-2.250 -0.1754 0.01064 0.00431 0.0081 0.5893 0.0190
-2.000 -0.1502 0.00955 0.00310 0.0085 0.5729 0.0216
-1.750 -0.1224 0.00942 0.00291 0.0085 0.5554 0.0234
-1.500 -0.0944 0.00931 0.00273 0.0084 0.5377 0.0253
-1.250 -0.0663 0.00925 0.00260 0.0084 0.5208 0.0266
-1.000 -0.0390 0.00883 0.00205 0.0084 0.5056 0.0285
-0.750 -0.0110 0.00863 0.00179 0.0084 0.4903 0.0321
-0.500 0.0172 0.00856 0.00165 0.0083 0.4748 0.0354
-0.250 0.0455 0.00852 0.00154 0.0082 0.4603 0.0376
0.000 0.0736 0.00836 0.00132 0.0081 0.4472 0.0450
0.250 0.1020 0.00832 0.00124 0.0080 0.4346 0.0509
0.500 0.1302 0.00820 0.00118 0.0078 0.4221 0.0874
0.750 0.1530 0.00639 0.00096 0.0077 0.4109 0.6601
1.000 0.1800 0.00627 0.00101 0.0079 0.3992 0.7268
1.250 0.2077 0.00626 0.00105 0.0079 0.3888 0.7601
1.500 0.2356 0.00629 0.00110 0.0080 0.3791 0.7792
1.750 0.2635 0.00635 0.00114 0.0080 0.3692 0.7945
2.000 0.2911 0.00640 0.00121 0.0081 0.3593 0.8153
2.250 0.3189 0.00645 0.00128 0.0081 0.3510 0.8286
2.750 0.3750 0.00659 0.00140 0.0080 0.3351 0.8469
3.000 0.4029 0.00667 0.00147 0.0080 0.3272 0.8532
3.250 0.4312 0.00674 0.00154 0.0078 0.3200 0.8601
3.500 0.4590 0.00682 0.00163 0.0078 0.3133 0.8667
3.750 0.4872 0.00689 0.00171 0.0077 0.3069 0.8740
4.000 0.5147 0.00699 0.00181 0.0077 0.3000 0.8811
4.500 0.5700 0.00714 0.00200 0.0077 0.2820 0.8972
5.000 0.6246 0.00732 0.00220 0.0077 0.2644 0.9163
5.250 0.6514 0.00741 0.00233 0.0079 0.2542 0.9277
5.500 0.6781 0.00751 0.00244 0.0080 0.2405 0.9420
5.750 0.7074 0.00763 0.00257 0.0076 0.2251 0.9615
6.000 0.7425 0.00792 0.00277 0.0056 0.1981 1.0000
6.250 0.7651 0.00956 0.00368 0.0054 0.0616 1.0000
6.500 0.7911 0.01034 0.00433 0.0052 0.0282 1.0000
6.750 0.8184 0.01068 0.00469 0.0050 0.0238 1.0000
7.000 0.8451 0.01122 0.00526 0.0050 0.0189 1.0000
7.250 0.8722 0.01157 0.00565 0.0048 0.0172 1.0000
7.500 0.8988 0.01201 0.00613 0.0047 0.0155 1.0000
7.750 0.9244 0.01272 0.00692 0.0047 0.0138 1.0000
8.000 0.9488 0.01366 0.00800 0.0048 0.0128 1.0000
8.250 0.9751 0.01402 0.00840 0.0047 0.0123 1.0000
8.500 1.0007 0.01455 0.00898 0.0047 0.0115 1.0000
8.750 1.0257 0.01517 0.00968 0.0047 0.0108 1.0000
9.000 1.0502 0.01582 0.01038 0.0047 0.0102 1.0000
9.250 1.0739 0.01659 0.01120 0.0048 0.0096 1.0000
9.500 1.0890 0.01877 0.01357 0.0055 0.0087 1.0000
9.750 1.1126 0.01939 0.01426 0.0056 0.0085 1.0000
10.000 1.1355 0.02009 0.01503 0.0057 0.0081 1.0000
10.250 1.1567 0.02099 0.01603 0.0059 0.0077 1.0000
10.500 1.1769 0.02198 0.01710 0.0062 0.0073 1.0000
10.750 1.1965 0.02298 0.01818 0.0065 0.0070 1.0000
11.000 1.2153 0.02400 0.01927 0.0068 0.0067 1.0000
11.250 1.2327 0.02510 0.02044 0.0071 0.0064 1.0000
11.500 1.2459 0.02661 0.02204 0.0076 0.0061 1.0000
11.750 1.2485 0.02920 0.02478 0.0086 0.0059 1.0000
12.000 1.2316 0.03350 0.02933 0.0099 0.0057 1.0000
12.250 1.2295 0.03677 0.03277 0.0091 0.0056 1.0000
12.500 1.2344 0.03940 0.03553 0.0076 0.0055 1.0000
12.750 1.2366 0.04252 0.03880 0.0059 0.0054 1.0000
13.000 1.2364 0.04603 0.04244 0.0040 0.0053 1.0000
13.250 1.2323 0.05014 0.04670 0.0020 0.0053 1.0000
13.500 1.2258 0.05464 0.05134 -0.0002 0.0052 1.0000
13.750 1.2179 0.05939 0.05623 -0.0026 0.0051 1.0000
14.000 1.2071 0.06464 0.06162 -0.0051 0.0051 1.0000
14.250 1.1948 0.07017 0.06729 -0.0078 0.0050 1.0000
14.500 1.1807 0.07609 0.07334 -0.0108 0.0050 1.0000
14.750 1.1647 0.08248 0.07987 -0.0140 0.0050 1.0000
15.000 1.1487 0.08926 0.08679 -0.0175 0.0050 1.0000
15.250 1.1312 0.09659 0.09425 -0.0213 0.0050 1.0000
15.500 1.1125 0.10447 0.10227 -0.0255 0.0050 1.0000
15.750 1.0922 0.11291 0.11083 -0.0299 0.0050 1.0000
16.000 1.0695 0.12230 0.12035 -0.0349 0.0050 1.0000
16.250 1.0449 0.13252 0.13070 -0.0403 0.0051 1.0000
16.500 1.0172 0.14419 0.14248 -0.0466 0.0052 1.0000
16.750 0.9562 0.16695 0.16542 -0.0582 0.0055 1.0000
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Polar data table (+)
Polar graphs
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