PMC19 Smoothed (pmc19sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: PMC19 Smoothed (pmc19sm-il) Reynolds number: 200,000 Max Cl/Cd: 58.91 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-pmc19sm-il-200000.txt Download as CSV file: xf-pmc19sm-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6122 0.10834 0.10512 0.0141 1.0000 0.0269
-8.750 -0.6149 0.10425 0.10101 0.0109 1.0000 0.0270
-8.500 -0.6209 0.09762 0.09441 0.0088 1.0000 0.0273
-8.250 -0.6135 0.09165 0.08851 0.0105 1.0000 0.0280
-8.000 -0.6106 0.08756 0.08443 0.0098 1.0000 0.0284
-7.750 -0.6072 0.08346 0.08031 0.0084 1.0000 0.0289
-7.500 -0.6031 0.07938 0.07620 0.0066 1.0000 0.0294
-7.250 -0.5976 0.07535 0.07212 0.0049 1.0000 0.0301
-7.000 -0.5901 0.07137 0.06807 0.0033 1.0000 0.0309
-6.750 -0.5803 0.06748 0.06407 0.0019 1.0000 0.0320
-6.500 -0.5680 0.06370 0.06016 0.0007 1.0000 0.0334
-6.250 -0.5493 0.06081 0.05702 -0.0004 1.0000 0.0360
-6.000 -0.5226 0.06146 0.05715 -0.0001 1.0000 0.0377
-5.750 -0.5128 0.05427 0.04980 -0.0010 1.0000 0.0385
-5.500 -0.4983 0.04924 0.04480 -0.0016 1.0000 0.0396
-5.250 -0.4804 0.04581 0.04132 -0.0018 1.0000 0.0409
-5.000 -0.4600 0.04288 0.03828 -0.0020 1.0000 0.0427
-4.750 -0.4373 0.04024 0.03546 -0.0020 1.0000 0.0453
-4.500 -0.4041 0.04135 0.03602 -0.0006 1.0000 0.0508
-4.250 -0.3844 0.03591 0.03034 -0.0010 1.0000 0.0523
-4.000 -0.3626 0.03243 0.02691 -0.0015 1.0000 0.0545
-3.750 -0.3376 0.03027 0.02465 -0.0016 1.0000 0.0587
-3.500 -0.3093 0.02864 0.02262 -0.0012 1.0000 0.0671
-3.250 -0.2790 0.02771 0.02143 -0.0020 0.9751 0.0803
-3.000 -0.2386 0.02455 0.01821 -0.0055 0.9156 0.0905
-2.750 -0.2126 0.02314 0.01643 -0.0050 0.8722 0.1096
-2.500 -0.1793 0.02068 0.01344 -0.0020 0.8413 0.0628
-2.250 -0.1536 0.01854 0.01101 -0.0004 0.8127 0.0569
-2.000 -0.1277 0.01725 0.00945 0.0009 0.7862 0.0566
-1.750 -0.1017 0.01607 0.00804 0.0022 0.7608 0.0561
-1.500 -0.0762 0.01533 0.00716 0.0031 0.7364 0.0596
-1.250 -0.0505 0.01475 0.00640 0.0040 0.7138 0.0631
-1.000 -0.0246 0.01421 0.00572 0.0047 0.6907 0.0651
-0.750 -0.0003 0.01327 0.00474 0.0054 0.6701 0.0701
-0.500 0.0262 0.01299 0.00434 0.0058 0.6483 0.0791
-0.250 0.0521 0.01249 0.00372 0.0061 0.6287 0.0898
0.000 0.0791 0.01213 0.00329 0.0063 0.6084 0.1154
0.250 0.0875 0.00995 0.00341 0.0106 0.5931 0.8033
0.500 0.1058 0.01008 0.00355 0.0138 0.5759 0.8551
0.750 0.1239 0.01019 0.00360 0.0169 0.5596 0.8900
1.000 0.1426 0.01023 0.00357 0.0197 0.5441 0.9169
1.250 0.1638 0.01021 0.00349 0.0221 0.5291 0.9467
1.500 0.2048 0.01033 0.00349 0.0201 0.5116 0.9706
1.750 0.2444 0.01045 0.00348 0.0174 0.4947 0.9762
2.000 0.2829 0.01059 0.00350 0.0149 0.4795 0.9829
2.250 0.3230 0.01075 0.00356 0.0120 0.4650 0.9885
2.500 0.3620 0.01091 0.00362 0.0093 0.4514 0.9955
2.750 0.3948 0.01106 0.00368 0.0078 0.4397 1.0000
3.000 0.4161 0.01116 0.00374 0.0085 0.4300 1.0000
3.250 0.4376 0.01130 0.00387 0.0092 0.4204 1.0000
3.500 0.4610 0.01151 0.00399 0.0096 0.4118 1.0000
3.750 0.4869 0.01170 0.00416 0.0096 0.4024 1.0000
4.000 0.5139 0.01195 0.00440 0.0095 0.3942 1.0000
4.250 0.5412 0.01221 0.00463 0.0093 0.3863 1.0000
4.500 0.5690 0.01246 0.00492 0.0090 0.3778 1.0000
4.750 0.5966 0.01279 0.00519 0.0088 0.3711 1.0000
5.000 0.6246 0.01305 0.00555 0.0085 0.3632 1.0000
5.250 0.6521 0.01338 0.00583 0.0084 0.3561 1.0000
5.500 0.6796 0.01351 0.00606 0.0082 0.3449 1.0000
5.750 0.7068 0.01360 0.00620 0.0081 0.3316 1.0000
6.000 0.7340 0.01370 0.00636 0.0080 0.3184 1.0000
6.250 0.7612 0.01381 0.00654 0.0079 0.3050 1.0000
6.500 0.7882 0.01386 0.00668 0.0078 0.2881 1.0000
6.750 0.8153 0.01384 0.00676 0.0077 0.2605 1.0000
7.000 0.8343 0.01583 0.00771 0.0075 0.0707 1.0000
7.250 0.8563 0.01752 0.00938 0.0077 0.0488 1.0000
7.500 0.8797 0.01870 0.01076 0.0078 0.0430 1.0000
7.750 0.8985 0.02057 0.01276 0.0082 0.0391 1.0000
8.000 0.9188 0.02206 0.01435 0.0087 0.0370 1.0000
8.250 0.9401 0.02330 0.01567 0.0091 0.0342 1.0000
8.500 0.9600 0.02484 0.01728 0.0097 0.0325 1.0000
8.750 0.9797 0.02655 0.01903 0.0105 0.0312 1.0000
9.000 0.9996 0.02851 0.02104 0.0112 0.0302 1.0000
9.250 1.0198 0.03087 0.02351 0.0120 0.0295 1.0000
9.500 1.0378 0.03529 0.02806 0.0126 0.0281 1.0000
9.750 1.0546 0.03721 0.03030 0.0132 0.0272 1.0000
10.000 1.0703 0.04030 0.03369 0.0139 0.0271 1.0000
10.250 1.0821 0.04487 0.03856 0.0145 0.0275 1.0000
10.500 1.1006 0.04738 0.04127 0.0152 0.0285 1.0000
10.750 1.0969 0.05105 0.04588 0.0173 0.0342 1.0000
11.000 1.0169 0.04325 0.03850 0.0238 0.0331 1.0000
11.250 0.9967 0.04778 0.04328 0.0244 0.0347 1.0000
11.500 0.9758 0.05256 0.04826 0.0239 0.0356 1.0000
11.750 0.9537 0.05790 0.05376 0.0226 0.0362 1.0000
12.000 0.9303 0.06372 0.05973 0.0207 0.0366 1.0000
12.250 0.9062 0.06976 0.06591 0.0181 0.0367 1.0000
12.500 0.8808 0.07610 0.07240 0.0148 0.0365 1.0000
12.750 0.8544 0.08295 0.07937 0.0110 0.0362 1.0000
13.000 0.8274 0.09023 0.08677 0.0068 0.0360 1.0000
13.250 0.7989 0.09806 0.09470 0.0023 0.0358 1.0000
13.500 0.7691 0.10651 0.10325 -0.0026 0.0358 1.0000
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Polar data table (+)
Polar graphs
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