MH 78 14.47% (mh78-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 78 14.47% (mh78-il) Reynolds number: 100,000 Max Cl/Cd: 22.45 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh78-il-100000.txt Download as CSV file: xf-mh78-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 78 14.47%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4984 0.09402 0.09035 0.0192 1.0000 0.1444
-8.250 -0.4809 0.09121 0.08762 0.0199 1.0000 0.1493
-8.000 -0.5452 0.08490 0.08138 0.0084 1.0000 0.1563
-7.750 -0.5106 0.08066 0.07731 0.0099 1.0000 0.1606
-7.500 -0.4942 0.07746 0.07423 0.0090 1.0000 0.1656
-7.000 -0.5986 0.04555 0.03993 -0.0028 0.9198 0.0722
-6.750 -0.5858 0.04291 0.03695 -0.0001 0.8620 0.0693
-6.500 -0.5856 0.03882 0.03162 0.0047 0.8301 0.0632
-6.250 -0.5700 0.03652 0.02907 0.0072 0.7997 0.0626
-6.000 -0.5519 0.03435 0.02654 0.0094 0.7720 0.0620
-5.750 -0.5325 0.03242 0.02421 0.0115 0.7479 0.0618
-5.500 -0.5112 0.03068 0.02205 0.0135 0.7261 0.0620
-5.250 -0.4874 0.02912 0.02009 0.0151 0.7046 0.0627
-5.000 -0.4622 0.02758 0.01835 0.0163 0.6838 0.0645
-4.750 -0.4369 0.02654 0.01725 0.0172 0.6643 0.0681
-4.500 -0.4109 0.02545 0.01590 0.0185 0.6462 0.0719
-4.250 -0.3846 0.02429 0.01478 0.0193 0.6281 0.0765
-4.000 -0.3585 0.02320 0.01368 0.0202 0.6108 0.0828
-3.750 -0.3342 0.02228 0.01282 0.0213 0.5946 0.0938
-3.500 -0.3111 0.02137 0.01196 0.0227 0.5801 0.1115
-3.250 -0.2914 0.02011 0.01103 0.0246 0.5675 0.1600
-3.000 -0.2772 0.01822 0.01037 0.0269 0.5542 0.3449
-2.750 -0.2618 0.01714 0.01013 0.0297 0.5429 0.5190
-2.500 -0.2235 0.01681 0.01077 0.0309 0.5278 0.7500
-2.250 -0.1820 0.01789 0.01179 0.0318 0.5123 0.8497
-2.000 -0.1192 0.01935 0.01291 0.0290 0.4953 0.8970
-1.750 -0.0565 0.02022 0.01337 0.0248 0.4802 0.9272
-1.500 0.0081 0.02061 0.01337 0.0192 0.4659 0.9484
-1.250 0.0676 0.02074 0.01328 0.0137 0.4512 0.9690
-1.000 0.1310 0.02057 0.01284 0.0071 0.4383 0.9864
-0.750 0.1867 0.02022 0.01219 0.0017 0.4276 1.0000
-0.500 0.2087 0.02031 0.01221 0.0020 0.4197 1.0000
-0.250 0.2305 0.02035 0.01213 0.0026 0.4120 1.0000
0.000 0.2520 0.02047 0.01201 0.0034 0.4064 1.0000
0.250 0.2758 0.02070 0.01229 0.0036 0.3987 1.0000
0.500 0.2986 0.02085 0.01234 0.0042 0.3922 1.0000
0.750 0.3209 0.02106 0.01232 0.0050 0.3872 1.0000
1.000 0.3454 0.02143 0.01278 0.0051 0.3801 1.0000
1.250 0.3688 0.02168 0.01296 0.0056 0.3740 1.0000
1.500 0.3918 0.02193 0.01305 0.0064 0.3696 1.0000
1.750 0.4159 0.02248 0.01364 0.0066 0.3641 1.0000
2.000 0.4396 0.02294 0.01413 0.0069 0.3581 1.0000
2.250 0.4626 0.02324 0.01433 0.0076 0.3533 1.0000
2.500 0.4851 0.02365 0.01456 0.0085 0.3495 1.0000
2.750 0.5086 0.02454 0.01567 0.0084 0.3440 1.0000
3.000 0.5313 0.02518 0.01635 0.0089 0.3390 1.0000
3.250 0.5537 0.02557 0.01667 0.0097 0.3349 1.0000
3.500 0.5759 0.02601 0.01694 0.0107 0.3314 1.0000
3.750 0.5969 0.02732 0.01851 0.0107 0.3262 1.0000
4.000 0.6175 0.02840 0.01971 0.0110 0.3217 1.0000
4.250 0.6387 0.02902 0.02030 0.0119 0.3180 1.0000
4.500 0.6604 0.02942 0.02059 0.0130 0.3149 1.0000
4.750 0.6794 0.03066 0.02188 0.0136 0.3113 1.0000
5.000 0.6926 0.03297 0.02455 0.0136 0.3060 1.0000
5.250 0.7083 0.03445 0.02614 0.0142 0.3022 1.0000
5.500 0.7277 0.03511 0.02675 0.0154 0.2993 1.0000
5.750 0.7496 0.03538 0.02690 0.0168 0.2969 1.0000
6.000 0.7570 0.03803 0.02975 0.0174 0.2933 1.0000
6.250 0.5214 0.06854 0.06121 0.0080 0.2915 1.0000
6.500 0.5072 0.07306 0.06570 0.0079 0.2928 1.0000
6.750 0.5089 0.07677 0.06940 0.0077 0.2967 1.0000
7.000 0.5272 0.07878 0.07139 0.0088 0.2958 1.0000
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Polar data table (+)
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