MH 108 11.98% (mh108-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 108 11.98% (mh108-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.75 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh108-il-1000000-n5.txt Download as CSV file: xf-mh108-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 108 11.98%
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
------ -------- --------- --------- -------- -------- --------
-16.500 -1.0306 0.10163 0.09895 0.0089 1.0000 0.0020
-16.250 -1.0691 0.09020 0.08737 0.0024 1.0000 0.0019
-16.000 -1.1170 0.07729 0.07428 -0.0051 1.0000 0.0019
-15.750 -1.1459 0.06795 0.06479 -0.0106 1.0000 0.0018
-15.500 -1.1610 0.06112 0.05784 -0.0147 1.0000 0.0018
-15.250 -1.1913 0.05177 0.04828 -0.0210 1.0000 0.0018
-15.000 -1.2111 0.04500 0.04134 -0.0254 1.0000 0.0018
-14.750 -1.2200 0.04070 0.03691 -0.0275 1.0000 0.0018
-14.500 -1.2341 0.03657 0.03262 -0.0286 1.0000 0.0018
-14.250 -1.2472 0.03329 0.02918 -0.0280 1.0000 0.0018
-14.000 -1.2534 0.03103 0.02680 -0.0264 1.0000 0.0018
-13.750 -1.2549 0.02935 0.02501 -0.0243 1.0000 0.0018
-13.500 -1.2590 0.02765 0.02318 -0.0214 1.0000 0.0019
-13.250 -1.2584 0.02634 0.02177 -0.0183 1.0000 0.0020
-13.000 -1.2534 0.02534 0.02068 -0.0153 1.0000 0.0020
-12.750 -1.2448 0.02437 0.01962 -0.0129 1.0000 0.0020
-12.500 -1.2325 0.02340 0.01857 -0.0110 1.0000 0.0021
-12.250 -1.2183 0.02250 0.01757 -0.0092 1.0000 0.0021
-12.000 -1.2022 0.02167 0.01667 -0.0077 1.0000 0.0022
-11.750 -1.1850 0.02090 0.01583 -0.0063 1.0000 0.0023
-11.500 -1.1670 0.02014 0.01498 -0.0050 1.0000 0.0023
-11.250 -1.1479 0.01944 0.01422 -0.0038 1.0000 0.0024
-11.000 -1.1280 0.01878 0.01350 -0.0027 1.0000 0.0025
-10.750 -1.1078 0.01811 0.01275 -0.0015 1.0000 0.0025
-10.500 -1.0868 0.01750 0.01209 -0.0005 1.0000 0.0027
-10.250 -1.0652 0.01693 0.01145 0.0005 1.0000 0.0027
-10.000 -1.0431 0.01639 0.01086 0.0014 1.0000 0.0028
-9.750 -1.0207 0.01587 0.01028 0.0023 1.0000 0.0029
-9.500 -0.9977 0.01539 0.00975 0.0031 1.0000 0.0030
-9.250 -0.9754 0.01482 0.00913 0.0040 1.0000 0.0032
-9.000 -0.9524 0.01432 0.00859 0.0049 1.0000 0.0034
-8.750 -0.9289 0.01387 0.00811 0.0057 1.0000 0.0036
-8.500 -0.9051 0.01346 0.00766 0.0064 1.0000 0.0039
-8.250 -0.8811 0.01307 0.00724 0.0072 1.0000 0.0042
-8.000 -0.8568 0.01271 0.00685 0.0079 1.0000 0.0046
-7.750 -0.8240 0.01228 0.00640 0.0067 0.9718 0.0052
-7.500 -0.7900 0.01204 0.00595 0.0056 0.8729 0.0062
-7.250 -0.7675 0.01191 0.00561 0.0068 0.8194 0.0069
-7.000 -0.7438 0.01168 0.00525 0.0077 0.7787 0.0087
-6.750 -0.7192 0.01146 0.00492 0.0084 0.7450 0.0110
-6.500 -0.6944 0.01120 0.00458 0.0091 0.7152 0.0151
-6.000 -0.6441 0.01065 0.00396 0.0102 0.6640 0.0294
-5.750 -0.6186 0.01041 0.00367 0.0107 0.6422 0.0383
-5.500 -0.5928 0.01016 0.00343 0.0112 0.6228 0.0487
-5.250 -0.5668 0.00994 0.00320 0.0116 0.6040 0.0599
-5.000 -0.5407 0.00973 0.00298 0.0120 0.5855 0.0723
-4.750 -0.5145 0.00952 0.00277 0.0124 0.5686 0.0871
-4.250 -0.4614 0.00918 0.00243 0.0131 0.5385 0.1134
-4.000 -0.4346 0.00904 0.00227 0.0134 0.5225 0.1255
-3.750 -0.4077 0.00890 0.00213 0.0137 0.5079 0.1405
-3.500 -0.3809 0.00876 0.00200 0.0140 0.4945 0.1568
-3.250 -0.3537 0.00864 0.00188 0.0142 0.4819 0.1704
-3.000 -0.3267 0.00852 0.00177 0.0145 0.4690 0.1871
-2.750 -0.2997 0.00840 0.00166 0.0148 0.4562 0.2043
-2.500 -0.2726 0.00829 0.00157 0.0150 0.4439 0.2233
-2.250 -0.2454 0.00820 0.00149 0.0153 0.4331 0.2420
-2.000 -0.2181 0.00811 0.00141 0.0155 0.4224 0.2592
-1.750 -0.1910 0.00799 0.00134 0.0157 0.4122 0.2835
-1.500 -0.1639 0.00789 0.00128 0.0160 0.4019 0.3082
-1.000 -0.1095 0.00772 0.00119 0.0164 0.3822 0.3561
-0.750 -0.0823 0.00763 0.00115 0.0167 0.3741 0.3830
-0.500 -0.0551 0.00755 0.00112 0.0169 0.3658 0.4103
-0.250 -0.0279 0.00747 0.00110 0.0171 0.3579 0.4374
0.000 -0.0007 0.00741 0.00109 0.0174 0.3493 0.4654
0.250 0.0264 0.00733 0.00108 0.0176 0.3423 0.4957
0.500 0.0533 0.00725 0.00108 0.0179 0.3355 0.5284
0.750 0.0801 0.00716 0.00109 0.0182 0.3297 0.5629
1.000 0.1068 0.00708 0.00110 0.0186 0.3230 0.6003
1.250 0.1332 0.00700 0.00112 0.0190 0.3167 0.6395
1.500 0.1596 0.00691 0.00115 0.0194 0.3115 0.6784
1.750 0.1856 0.00684 0.00119 0.0199 0.3054 0.7180
2.000 0.2115 0.00676 0.00123 0.0205 0.3002 0.7579
2.250 0.2373 0.00670 0.00128 0.0211 0.2946 0.7962
2.500 0.2630 0.00666 0.00134 0.0217 0.2890 0.8337
2.750 0.2895 0.00662 0.00142 0.0223 0.2845 0.8680
3.000 0.3173 0.00663 0.00150 0.0225 0.2790 0.8988
3.250 0.3481 0.00670 0.00161 0.0221 0.2736 0.9236
3.500 0.3821 0.00678 0.00172 0.0209 0.2686 0.9404
3.750 0.4172 0.00691 0.00183 0.0195 0.2628 0.9514
4.000 0.4517 0.00703 0.00194 0.0181 0.2579 0.9587
4.250 0.4835 0.00714 0.00205 0.0174 0.2525 0.9656
4.500 0.5154 0.00728 0.00216 0.0166 0.2463 0.9705
4.750 0.5491 0.00739 0.00228 0.0154 0.2412 0.9740
5.000 0.5801 0.00753 0.00240 0.0148 0.2345 0.9782
5.250 0.6096 0.00767 0.00253 0.0145 0.2284 0.9823
5.500 0.6460 0.00782 0.00266 0.0127 0.2208 0.9845
5.750 0.6815 0.00798 0.00280 0.0110 0.2125 0.9872
6.000 0.7147 0.00817 0.00296 0.0098 0.2036 0.9899
6.250 0.7458 0.00835 0.00312 0.0091 0.1932 0.9921
6.500 0.7766 0.00856 0.00330 0.0084 0.1826 0.9938
6.750 0.8093 0.00879 0.00349 0.0072 0.1702 0.9951
7.000 0.8414 0.00906 0.00371 0.0061 0.1572 0.9965
7.250 0.8732 0.00934 0.00396 0.0051 0.1451 0.9980
7.500 0.9047 0.00965 0.00422 0.0041 0.1333 0.9992
7.750 0.9335 0.01000 0.00452 0.0036 0.1197 1.0000
8.000 0.9559 0.01036 0.00482 0.0045 0.1080 1.0000
8.250 0.9789 0.01065 0.00510 0.0053 0.1005 1.0000
8.500 1.0014 0.01099 0.00543 0.0062 0.0920 1.0000
8.750 1.0231 0.01141 0.00580 0.0072 0.0809 1.0000
9.000 1.0442 0.01187 0.00620 0.0082 0.0693 1.0000
9.250 1.0650 0.01236 0.00664 0.0093 0.0587 1.0000
9.500 1.0849 0.01292 0.00714 0.0104 0.0468 1.0000
9.750 1.1045 0.01350 0.00766 0.0116 0.0371 1.0000
10.000 1.1235 0.01411 0.00823 0.0128 0.0285 1.0000
10.250 1.1429 0.01466 0.00877 0.0140 0.0233 1.0000
10.500 1.1623 0.01518 0.00930 0.0152 0.0194 1.0000
10.750 1.1811 0.01574 0.00987 0.0164 0.0162 1.0000
11.000 1.2000 0.01628 0.01042 0.0176 0.0139 1.0000
11.250 1.2174 0.01691 0.01107 0.0190 0.0112 1.0000
11.500 1.2345 0.01753 0.01172 0.0204 0.0094 1.0000
11.750 1.2513 0.01815 0.01238 0.0217 0.0080 1.0000
12.000 1.2662 0.01887 0.01312 0.0233 0.0066 1.0000
12.250 1.2807 0.01957 0.01387 0.0249 0.0056 1.0000
12.500 1.2937 0.02031 0.01466 0.0266 0.0049 1.0000
12.750 1.3039 0.02117 0.01556 0.0286 0.0042 1.0000
13.000 1.3106 0.02194 0.01640 0.0312 0.0041 1.0000
13.250 1.3137 0.02288 0.01741 0.0339 0.0038 1.0000
13.500 1.3160 0.02416 0.01876 0.0357 0.0034 1.0000
13.750 1.3184 0.02582 0.02050 0.0366 0.0033 1.0000
14.000 1.3189 0.02807 0.02285 0.0365 0.0029 1.0000
14.250 1.3197 0.03069 0.02557 0.0357 0.0027 1.0000
14.500 1.3200 0.03362 0.02860 0.0345 0.0026 1.0000
14.750 1.3184 0.03694 0.03203 0.0330 0.0025 1.0000
15.000 1.3142 0.04065 0.03584 0.0314 0.0026 1.0000
15.250 1.3071 0.04475 0.04005 0.0295 0.0024 1.0000
15.500 1.2971 0.04925 0.04466 0.0276 0.0024 1.0000
15.750 1.2846 0.05408 0.04959 0.0255 0.0022 1.0000
16.000 1.2691 0.05933 0.05495 0.0233 0.0021 1.0000
16.250 1.2548 0.06446 0.06018 0.0212 0.0021 1.0000
16.500 1.2406 0.06962 0.06545 0.0190 0.0022 1.0000
16.750 1.2239 0.07539 0.07132 0.0165 0.0021 1.0000
17.000 1.2122 0.08051 0.07653 0.0143 0.0022 1.0000
17.250 1.1962 0.08640 0.08252 0.0117 0.0021 1.0000
17.500 1.1795 0.09247 0.08867 0.0090 0.0019 1.0000
17.750 1.1671 0.09799 0.09429 0.0066 0.0020 1.0000
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Polar data table (+)
Polar graphs
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