NACA M5 AIRFOIL (m5-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M5 AIRFOIL (m5-il) Reynolds number: 200,000 Max Cl/Cd: 60.61 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m5-il-200000.txt Download as CSV file: xf-m5-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M5 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6163 0.11433 0.11101 0.0213 1.0000 0.0452
-9.250 -0.6201 0.11005 0.10677 0.0150 1.0000 0.0456
-9.000 -0.6236 0.10526 0.10201 0.0088 1.0000 0.0458
-8.750 -0.6270 0.10072 0.09746 0.0045 1.0000 0.0459
-8.500 -0.6290 0.09364 0.09043 0.0058 1.0000 0.0468
-8.250 -0.6188 0.09055 0.08736 0.0084 1.0000 0.0479
-8.000 -0.6139 0.08706 0.08387 0.0079 1.0000 0.0490
-7.750 -0.6088 0.08312 0.07991 0.0058 1.0000 0.0503
-7.500 -0.6032 0.07884 0.07558 0.0031 1.0000 0.0521
-7.250 -0.5959 0.07411 0.07078 -0.0005 1.0000 0.0547
-6.500 -0.5660 0.05917 0.05543 -0.0072 1.0000 0.0613
-6.250 -0.5505 0.05621 0.05241 -0.0073 1.0000 0.0639
-6.000 -0.5273 0.05416 0.04956 -0.0086 1.0000 0.0716
-5.750 -0.5169 0.04701 0.04253 -0.0092 1.0000 0.0736
-5.500 -0.4977 0.04475 0.04035 -0.0090 1.0000 0.0764
-5.250 -0.4767 0.04168 0.03668 -0.0090 1.0000 0.0870
-5.000 -0.4562 0.03864 0.03374 -0.0092 1.0000 0.0894
-4.750 -0.4321 0.03724 0.03177 -0.0088 1.0000 0.1010
-4.500 -0.4106 0.03386 0.02861 -0.0092 1.0000 0.1042
-4.250 -0.3865 0.03206 0.02653 -0.0093 1.0000 0.1170
-4.000 -0.3551 0.02409 0.01736 -0.0072 1.0000 0.0694
-3.750 -0.3306 0.02233 0.01530 -0.0068 1.0000 0.0699
-3.500 -0.2957 0.02022 0.01289 -0.0084 0.9876 0.0695
-3.250 -0.2551 0.01851 0.01088 -0.0109 0.9717 0.0696
-3.000 -0.2192 0.01739 0.00954 -0.0122 0.9524 0.0705
-2.750 -0.1910 0.01642 0.00838 -0.0119 0.9310 0.0728
-2.500 -0.1677 0.01550 0.00742 -0.0105 0.9104 0.0750
-2.250 -0.1449 0.01490 0.00677 -0.0090 0.8908 0.0771
-2.000 -0.1220 0.01440 0.00621 -0.0075 0.8733 0.0798
-1.750 -0.0984 0.01397 0.00568 -0.0062 0.8572 0.0833
-1.500 -0.0746 0.01344 0.00511 -0.0050 0.8420 0.0879
-1.250 -0.0501 0.01308 0.00477 -0.0041 0.8274 0.0966
-1.000 -0.0253 0.01266 0.00437 -0.0032 0.8134 0.1079
-0.750 -0.0002 0.01224 0.00400 -0.0025 0.7999 0.1335
-0.500 0.0925 0.01001 0.00453 -0.0146 0.7892 1.0000
-0.250 0.1182 0.01002 0.00436 -0.0141 0.7756 1.0000
0.000 0.1440 0.01004 0.00422 -0.0136 0.7628 1.0000
0.250 0.1698 0.01007 0.00411 -0.0131 0.7506 1.0000
0.500 0.1958 0.01009 0.00403 -0.0127 0.7379 1.0000
0.750 0.2219 0.01013 0.00397 -0.0123 0.7255 1.0000
1.000 0.2479 0.01018 0.00393 -0.0119 0.7138 1.0000
1.250 0.2738 0.01024 0.00391 -0.0115 0.7025 1.0000
1.500 0.2994 0.01031 0.00389 -0.0110 0.6918 1.0000
1.750 0.3256 0.01036 0.00391 -0.0106 0.6797 1.0000
2.000 0.3516 0.01044 0.00394 -0.0103 0.6681 1.0000
2.250 0.3775 0.01052 0.00399 -0.0098 0.6570 1.0000
2.500 0.4032 0.01062 0.00403 -0.0093 0.6463 1.0000
2.750 0.4291 0.01070 0.00410 -0.0089 0.6345 1.0000
3.000 0.4550 0.01080 0.00420 -0.0085 0.6224 1.0000
3.250 0.4808 0.01091 0.00431 -0.0081 0.6105 1.0000
3.500 0.5065 0.01102 0.00441 -0.0076 0.5982 1.0000
3.750 0.5321 0.01111 0.00450 -0.0070 0.5843 1.0000
4.000 0.5576 0.01119 0.00458 -0.0065 0.5688 1.0000
4.250 0.5829 0.01125 0.00466 -0.0059 0.5507 1.0000
4.500 0.6079 0.01131 0.00466 -0.0052 0.5300 1.0000
4.750 0.6335 0.01138 0.00478 -0.0047 0.5083 1.0000
5.000 0.6586 0.01149 0.00487 -0.0041 0.4853 1.0000
5.250 0.6838 0.01162 0.00499 -0.0035 0.4572 1.0000
5.500 0.7089 0.01180 0.00515 -0.0030 0.4221 1.0000
5.750 0.7334 0.01210 0.00535 -0.0025 0.3753 1.0000
6.000 0.7564 0.01279 0.00572 -0.0020 0.2890 1.0000
6.250 0.7719 0.01548 0.00712 -0.0017 0.0844 1.0000
6.500 0.7927 0.01688 0.00841 -0.0010 0.0616 1.0000
6.750 0.8122 0.01831 0.00982 -0.0001 0.0517 1.0000
7.000 0.8337 0.01934 0.01096 0.0008 0.0473 1.0000
7.250 0.8540 0.02051 0.01215 0.0018 0.0430 1.0000
7.500 0.8721 0.02237 0.01399 0.0030 0.0395 1.0000
7.750 0.8941 0.02356 0.01529 0.0040 0.0375 1.0000
8.000 0.9160 0.02503 0.01686 0.0050 0.0359 1.0000
8.250 0.9379 0.02661 0.01855 0.0059 0.0343 1.0000
8.500 0.9588 0.02821 0.02020 0.0066 0.0323 1.0000
9.000 0.9970 0.03439 0.02684 0.0084 0.0303 1.0000
9.250 1.0139 0.03717 0.02996 0.0096 0.0302 1.0000
9.500 1.0274 0.04131 0.03444 0.0107 0.0304 1.0000
9.750 1.0435 0.04403 0.03743 0.0119 0.0310 1.0000
10.000 1.0375 0.04926 0.04375 0.0156 0.0361 1.0000
10.250 1.0340 0.05462 0.04944 0.0170 0.0382 1.0000
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Polar data table (+)
Polar graphs
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