PMC19 Smoothed (pmc19sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: PMC19 Smoothed (pmc19sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 82.21 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-pmc19sm-il-1000000-n5.txt Download as CSV file: xf-pmc19sm-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6333 0.08974 0.08831 0.0227 1.0000 0.0051
-8.250 -0.6411 0.08353 0.08211 0.0153 1.0000 0.0050
-8.000 -0.6452 0.07812 0.07665 0.0107 1.0000 0.0049
-7.750 -0.6445 0.07280 0.07126 0.0075 1.0000 0.0048
-7.500 -0.6399 0.06749 0.06584 0.0049 0.9601 0.0048
-7.250 -0.6320 0.06251 0.06046 0.0031 0.8528 0.0048
-6.250 -0.6106 0.01595 0.01089 0.0070 0.7759 0.0064
-6.000 -0.5859 0.01460 0.00924 0.0074 0.7508 0.0068
-5.750 -0.5600 0.01392 0.00839 0.0077 0.7270 0.0071
-5.500 -0.5338 0.01332 0.00763 0.0079 0.7042 0.0073
-5.250 -0.5074 0.01283 0.00699 0.0082 0.6821 0.0077
-5.000 -0.4809 0.01233 0.00635 0.0084 0.6610 0.0080
-4.750 -0.4543 0.01188 0.00576 0.0086 0.6414 0.0085
-4.500 -0.4277 0.01144 0.00519 0.0087 0.6220 0.0088
-4.250 -0.4008 0.01110 0.00472 0.0089 0.6028 0.0091
-4.000 -0.3742 0.01065 0.00414 0.0091 0.5848 0.0096
-3.750 -0.3470 0.01036 0.00378 0.0091 0.5680 0.0104
-3.500 -0.3195 0.01019 0.00354 0.0091 0.5513 0.0111
-3.250 -0.2919 0.01001 0.00328 0.0092 0.5340 0.0120
-3.000 -0.2642 0.00987 0.00307 0.0091 0.5186 0.0129
-2.750 -0.2366 0.00968 0.00279 0.0091 0.5031 0.0138
-2.500 -0.2089 0.00949 0.00254 0.0091 0.4879 0.0153
-2.250 -0.1809 0.00938 0.00237 0.0090 0.4736 0.0164
-2.000 -0.1529 0.00926 0.00220 0.0090 0.4611 0.0176
-1.750 -0.1248 0.00918 0.00205 0.0089 0.4483 0.0186
-1.500 -0.0968 0.00905 0.00185 0.0088 0.4351 0.0200
-1.250 -0.0687 0.00892 0.00167 0.0087 0.4231 0.0221
-1.000 -0.0405 0.00886 0.00157 0.0086 0.4124 0.0242
-0.750 -0.0123 0.00881 0.00148 0.0085 0.4016 0.0261
-0.500 0.0160 0.00875 0.00137 0.0084 0.3904 0.0277
-0.250 0.0443 0.00868 0.00127 0.0083 0.3803 0.0322
0.250 0.1010 0.00863 0.00115 0.0080 0.3629 0.0396
0.500 0.1293 0.00860 0.00112 0.0079 0.3543 0.0493
0.750 0.1577 0.00856 0.00110 0.0077 0.3453 0.0665
1.000 0.1858 0.00840 0.00109 0.0075 0.3377 0.1436
1.250 0.2098 0.00689 0.00092 0.0073 0.3309 0.6314
1.500 0.2375 0.00679 0.00095 0.0072 0.3246 0.6796
1.750 0.2655 0.00678 0.00100 0.0072 0.3173 0.7106
2.000 0.2930 0.00675 0.00107 0.0073 0.3105 0.7498
2.250 0.3210 0.00677 0.00113 0.0072 0.3042 0.7695
2.500 0.3491 0.00682 0.00120 0.0072 0.2987 0.7851
2.750 0.3775 0.00688 0.00125 0.0070 0.2933 0.7909
3.000 0.4058 0.00696 0.00132 0.0069 0.2868 0.7967
3.250 0.4342 0.00703 0.00140 0.0067 0.2818 0.8026
3.500 0.4624 0.00709 0.00148 0.0066 0.2766 0.8082
3.750 0.4906 0.00719 0.00157 0.0064 0.2713 0.8143
4.000 0.5189 0.00726 0.00166 0.0063 0.2665 0.8199
4.250 0.5469 0.00738 0.00177 0.0062 0.2560 0.8262
4.500 0.5748 0.00752 0.00189 0.0060 0.2437 0.8324
4.750 0.6026 0.00764 0.00201 0.0059 0.2326 0.8390
5.000 0.6305 0.00779 0.00214 0.0058 0.2208 0.8457
5.250 0.6577 0.00800 0.00232 0.0057 0.2025 0.8525
5.500 0.6847 0.00835 0.00255 0.0056 0.1701 0.8598
5.750 0.7081 0.00952 0.00325 0.0056 0.0690 0.8674
6.000 0.7340 0.01012 0.00373 0.0056 0.0331 0.8756
6.250 0.7606 0.01038 0.00402 0.0057 0.0258 0.8843
6.500 0.7872 0.01067 0.00433 0.0057 0.0206 0.8933
6.750 0.8137 0.01091 0.00463 0.0058 0.0178 0.9038
7.000 0.8397 0.01119 0.00494 0.0059 0.0150 0.9159
7.250 0.8656 0.01149 0.00530 0.0061 0.0128 0.9308
7.500 0.8928 0.01174 0.00565 0.0059 0.0119 0.9516
7.750 0.9260 0.01209 0.00607 0.0043 0.0108 1.0000
8.000 0.9525 0.01250 0.00650 0.0042 0.0098 1.0000
8.250 0.9784 0.01304 0.00709 0.0042 0.0089 1.0000
8.500 1.0044 0.01348 0.00758 0.0041 0.0084 1.0000
8.750 1.0304 0.01390 0.00806 0.0040 0.0080 1.0000
9.000 1.0560 0.01437 0.00859 0.0040 0.0076 1.0000
9.250 1.0813 0.01488 0.00916 0.0039 0.0072 1.0000
9.500 1.1063 0.01541 0.00973 0.0039 0.0068 1.0000
9.750 1.1308 0.01598 0.01034 0.0039 0.0063 1.0000
10.000 1.1534 0.01689 0.01135 0.0040 0.0057 1.0000
10.250 1.1770 0.01754 0.01207 0.0041 0.0055 1.0000
10.500 1.2004 0.01818 0.01278 0.0041 0.0053 1.0000
10.750 1.2231 0.01889 0.01357 0.0043 0.0051 1.0000
11.000 1.2451 0.01966 0.01443 0.0044 0.0049 1.0000
11.250 1.2664 0.02047 0.01532 0.0046 0.0046 1.0000
11.500 1.2870 0.02132 0.01625 0.0048 0.0044 1.0000
11.750 1.3070 0.02219 0.01721 0.0050 0.0042 1.0000
12.000 1.3260 0.02312 0.01821 0.0052 0.0040 1.0000
12.250 1.3435 0.02415 0.01932 0.0055 0.0038 1.0000
12.500 1.3581 0.02543 0.02070 0.0059 0.0037 1.0000
12.750 1.3668 0.02723 0.02262 0.0064 0.0035 1.0000
13.000 1.3632 0.02992 0.02547 0.0067 0.0034 1.0000
13.250 1.3644 0.03297 0.02866 0.0049 0.0033 1.0000
13.500 1.3658 0.03641 0.03224 0.0026 0.0033 1.0000
13.750 1.3656 0.04021 0.03616 0.0002 0.0033 1.0000
14.000 1.3620 0.04447 0.04055 -0.0023 0.0032 1.0000
14.250 1.3549 0.04917 0.04537 -0.0047 0.0032 1.0000
14.500 1.3461 0.05403 0.05035 -0.0071 0.0032 1.0000
14.750 1.3359 0.05905 0.05549 -0.0093 0.0032 1.0000
15.000 1.3237 0.06431 0.06086 -0.0116 0.0031 1.0000
15.250 1.3113 0.06962 0.06628 -0.0139 0.0031 1.0000
15.500 1.2977 0.07511 0.07187 -0.0162 0.0031 1.0000
15.750 1.2848 0.08065 0.07751 -0.0185 0.0031 1.0000
16.000 1.2722 0.08634 0.08330 -0.0210 0.0031 1.0000
16.250 1.2601 0.09211 0.08918 -0.0236 0.0030 1.0000
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Polar data table (+)
Polar graphs
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