PMC19 Smoothed (pmc19sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: PMC19 Smoothed (pmc19sm-il) Reynolds number: 200,000 Max Cl/Cd: 57.91 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-pmc19sm-il-200000-n5.txt Download as CSV file: xf-pmc19sm-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6075 0.09975 0.09653 0.0143 1.0000 0.0190
-8.500 -0.6095 0.09522 0.09199 0.0108 1.0000 0.0190
-8.250 -0.6111 0.09102 0.08776 0.0084 1.0000 0.0190
-8.000 -0.6092 0.08673 0.08340 0.0063 1.0000 0.0190
-7.750 -0.6053 0.08244 0.07904 0.0047 1.0000 0.0190
-7.500 -0.6032 0.07717 0.07372 0.0032 1.0000 0.0191
-7.250 -0.5999 0.07191 0.06838 0.0021 1.0000 0.0193
-7.000 -0.5921 0.06757 0.06397 0.0013 1.0000 0.0196
-6.750 -0.5810 0.06344 0.05971 0.0005 1.0000 0.0196
-6.500 -0.5699 0.06034 0.05661 0.0002 1.0000 0.0205
-6.250 -0.5551 0.05768 0.05389 -0.0003 1.0000 0.0225
-6.000 -0.5246 0.05704 0.05279 -0.0002 1.0000 0.0268
-5.500 -0.4969 0.04494 0.04030 -0.0005 1.0000 0.0183
-5.250 -0.4778 0.04146 0.03664 -0.0005 1.0000 0.0178
-5.000 -0.4561 0.03814 0.03308 -0.0003 1.0000 0.0173
-4.750 -0.4327 0.03489 0.02957 0.0000 1.0000 0.0171
-4.500 -0.4034 0.03147 0.02581 -0.0005 0.9417 0.0170
-4.250 -0.3701 0.02806 0.02191 -0.0011 0.8829 0.0174
-4.000 -0.3433 0.02512 0.01845 0.0002 0.8449 0.0185
-3.750 -0.3193 0.02333 0.01629 0.0010 0.8132 0.0202
-3.500 -0.2945 0.02189 0.01456 0.0019 0.7852 0.0209
-3.250 -0.2686 0.02029 0.01265 0.0028 0.7597 0.0217
-3.000 -0.2423 0.01885 0.01091 0.0035 0.7360 0.0228
-2.750 -0.2160 0.01763 0.00940 0.0044 0.7135 0.0245
-2.500 -0.1892 0.01711 0.00860 0.0050 0.6912 0.0271
-2.250 -0.1642 0.01581 0.00719 0.0056 0.6706 0.0290
-2.000 -0.1383 0.01515 0.00642 0.0061 0.6500 0.0308
-1.750 -0.1121 0.01469 0.00583 0.0065 0.6303 0.0340
-1.500 -0.0858 0.01426 0.00526 0.0068 0.6111 0.0368
-1.250 -0.0600 0.01363 0.00450 0.0072 0.5928 0.0389
-1.000 -0.0338 0.01314 0.00393 0.0074 0.5750 0.0423
-0.750 -0.0069 0.01291 0.00358 0.0075 0.5578 0.0478
-0.500 0.0203 0.01264 0.00318 0.0076 0.5412 0.0533
-0.250 0.0477 0.01245 0.00286 0.0077 0.5249 0.0610
0.000 0.0752 0.01230 0.00264 0.0077 0.5092 0.0776
0.250 0.0982 0.01076 0.00229 0.0076 0.4956 0.5025
0.500 0.1185 0.01015 0.00248 0.0095 0.4824 0.7274
0.750 0.1423 0.01016 0.00258 0.0108 0.4690 0.7875
1.000 0.1667 0.01023 0.00265 0.0119 0.4563 0.8199
1.250 0.1889 0.01028 0.00275 0.0136 0.4446 0.8563
1.500 0.2134 0.01034 0.00278 0.0146 0.4331 0.8760
1.750 0.2404 0.01040 0.00277 0.0148 0.4217 0.8835
2.000 0.2678 0.01048 0.00278 0.0149 0.4110 0.8914
2.250 0.2950 0.01056 0.00280 0.0150 0.4011 0.9000
2.500 0.3225 0.01063 0.00285 0.0151 0.3914 0.9086
2.750 0.3501 0.01073 0.00290 0.0151 0.3822 0.9182
3.000 0.3784 0.01082 0.00297 0.0150 0.3730 0.9285
3.250 0.4079 0.01091 0.00306 0.0146 0.3648 0.9393
3.500 0.4391 0.01105 0.00318 0.0137 0.3569 0.9509
3.750 0.4728 0.01117 0.00333 0.0123 0.3482 0.9632
4.000 0.5079 0.01134 0.00349 0.0105 0.3405 0.9792
4.250 0.5392 0.01151 0.00371 0.0095 0.3333 1.0000
4.500 0.5668 0.01173 0.00391 0.0093 0.3270 1.0000
4.750 0.5946 0.01192 0.00415 0.0090 0.3200 1.0000
5.250 0.6501 0.01237 0.00467 0.0086 0.3070 1.0000
5.500 0.6776 0.01258 0.00492 0.0084 0.2951 1.0000
5.750 0.7051 0.01277 0.00512 0.0082 0.2793 1.0000
6.000 0.7324 0.01299 0.00537 0.0080 0.2633 1.0000
6.250 0.7596 0.01325 0.00564 0.0078 0.2458 1.0000
6.500 0.7864 0.01358 0.00597 0.0076 0.2175 1.0000
6.750 0.8104 0.01453 0.00652 0.0074 0.1329 1.0000
7.000 0.8298 0.01671 0.00813 0.0072 0.0394 1.0000
7.250 0.8548 0.01750 0.00903 0.0072 0.0317 1.0000
7.500 0.8787 0.01850 0.01017 0.0072 0.0271 1.0000
7.750 0.9029 0.01935 0.01123 0.0072 0.0248 1.0000
8.000 0.9259 0.02037 0.01241 0.0073 0.0227 1.0000
8.250 0.9473 0.02155 0.01371 0.0073 0.0209 1.0000
8.500 0.9648 0.02327 0.01552 0.0076 0.0191 1.0000
8.750 0.9858 0.02433 0.01672 0.0078 0.0179 1.0000
9.000 1.0043 0.02573 0.01827 0.0082 0.0170 1.0000
9.250 1.0217 0.02722 0.01988 0.0087 0.0162 1.0000
9.500 1.0381 0.02880 0.02157 0.0093 0.0155 1.0000
9.750 1.0537 0.03044 0.02332 0.0099 0.0149 1.0000
10.000 1.0685 0.03206 0.02502 0.0103 0.0141 1.0000
10.250 1.0800 0.03409 0.02712 0.0109 0.0133 1.0000
10.500 1.0907 0.03626 0.02946 0.0116 0.0126 1.0000
10.750 1.1013 0.03825 0.03166 0.0123 0.0122 1.0000
11.000 1.1071 0.04054 0.03420 0.0132 0.0118 1.0000
11.250 1.1103 0.04319 0.03706 0.0136 0.0115 1.0000
11.500 1.1111 0.04620 0.04030 0.0134 0.0113 1.0000
11.750 1.1096 0.04961 0.04394 0.0126 0.0111 1.0000
12.000 1.1058 0.05342 0.04798 0.0113 0.0109 1.0000
12.250 1.0997 0.05767 0.05245 0.0094 0.0108 1.0000
12.500 1.0914 0.06237 0.05737 0.0071 0.0107 1.0000
12.750 1.0811 0.06755 0.06275 0.0042 0.0106 1.0000
13.000 1.0687 0.07320 0.06861 0.0010 0.0106 1.0000
13.250 1.0547 0.07932 0.07491 -0.0027 0.0106 1.0000
13.500 1.0391 0.08593 0.08170 -0.0067 0.0106 1.0000
13.750 1.0220 0.09300 0.08894 -0.0110 0.0106 1.0000
14.000 1.0037 0.10064 0.09674 -0.0156 0.0107 1.0000
14.250 0.9847 0.10901 0.10525 -0.0207 0.0108 1.0000
14.500 0.9648 0.11816 0.11453 -0.0263 0.0109 1.0000
14.750 0.9437 0.12829 0.12478 -0.0323 0.0111 1.0000
15.000 0.9211 0.13965 0.13621 -0.0388 0.0113 1.0000
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Polar data table (+)
Polar graphs
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