MH 62 9.3% (mh62-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: MH 62 9.3% (mh62-il) Reynolds number: 200,000 Max Cl/Cd: 60.45 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh62-il-200000.txt Download as CSV file: xf-mh62-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 62 9.3%
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4704 0.09617 0.09327 0.0070 1.0000 0.0416
-9.000 -0.4677 0.09199 0.08911 0.0056 1.0000 0.0428
-8.750 -0.5646 0.09010 0.08704 0.0006 1.0000 0.0399
-8.500 -0.5578 0.08712 0.08408 0.0006 1.0000 0.0410
-8.250 -0.5555 0.08335 0.08035 -0.0013 1.0000 0.0418
-8.000 -0.5562 0.07916 0.07621 -0.0041 1.0000 0.0427
-7.750 -0.5613 0.07424 0.07134 -0.0087 1.0000 0.0432
-7.500 -0.5624 0.06823 0.06530 -0.0147 1.0000 0.0445
-7.250 -0.5607 0.06229 0.05927 -0.0196 1.0000 0.0458
-7.000 -0.5621 0.05701 0.05330 -0.0255 1.0000 0.0507
-6.750 -0.5582 0.04930 0.04553 -0.0274 1.0000 0.0525
-6.500 -0.5404 0.04610 0.04240 -0.0278 1.0000 0.0544
-6.250 -0.5230 0.04281 0.03896 -0.0285 1.0000 0.0573
-6.000 -0.5098 0.03003 0.02476 -0.0270 1.0000 0.0227
-5.750 -0.4896 0.02595 0.01979 -0.0252 1.0000 0.0191
-5.500 -0.4760 0.02433 0.01791 -0.0231 1.0000 0.0189
-5.250 -0.4486 0.02120 0.01443 -0.0237 0.9937 0.0197
-5.000 -0.4103 0.01977 0.01287 -0.0265 0.9851 0.0234
-4.750 -0.3719 0.01792 0.01079 -0.0283 0.9765 0.0248
-4.500 -0.3344 0.01629 0.00902 -0.0299 0.9680 0.0262
-4.250 -0.3029 0.01469 0.00734 -0.0304 0.9570 0.0294
-4.000 -0.2755 0.01355 0.00617 -0.0302 0.9446 0.0441
-3.750 -0.2561 0.01172 0.00520 -0.0288 0.9317 0.2060
-3.500 -0.2343 0.01125 0.00504 -0.0276 0.9195 0.3019
-3.250 -0.2121 0.01099 0.00489 -0.0263 0.9081 0.3583
-3.000 -0.1906 0.01073 0.00478 -0.0248 0.8973 0.4228
-2.750 -0.1699 0.01044 0.00469 -0.0229 0.8872 0.4913
-2.500 -0.1480 0.01014 0.00459 -0.0214 0.8761 0.5577
-2.250 -0.1265 0.00984 0.00450 -0.0197 0.8657 0.6288
-2.000 -0.1057 0.00953 0.00441 -0.0176 0.8561 0.7059
-1.750 -0.0841 0.00924 0.00435 -0.0153 0.8468 0.7918
-1.500 -0.0502 0.00906 0.00432 -0.0155 0.8371 0.8839
-1.250 0.0025 0.00902 0.00418 -0.0197 0.8288 0.9464
-1.000 0.0531 0.00903 0.00403 -0.0239 0.8196 0.9813
-0.750 0.0997 0.00898 0.00384 -0.0277 0.8090 1.0000
-0.500 0.1219 0.00898 0.00370 -0.0266 0.7977 1.0000
-0.250 0.1446 0.00900 0.00359 -0.0255 0.7867 1.0000
0.000 0.1675 0.00902 0.00349 -0.0243 0.7759 1.0000
0.250 0.1916 0.00904 0.00342 -0.0234 0.7640 1.0000
0.500 0.2161 0.00907 0.00336 -0.0226 0.7517 1.0000
0.750 0.2407 0.00910 0.00330 -0.0218 0.7392 1.0000
1.000 0.2656 0.00913 0.00326 -0.0210 0.7264 1.0000
1.250 0.2906 0.00917 0.00322 -0.0202 0.7132 1.0000
1.500 0.3157 0.00921 0.00320 -0.0194 0.6993 1.0000
1.750 0.3411 0.00925 0.00317 -0.0187 0.6848 1.0000
2.000 0.3666 0.00929 0.00315 -0.0180 0.6696 1.0000
2.250 0.3921 0.00935 0.00314 -0.0173 0.6536 1.0000
2.500 0.4178 0.00941 0.00314 -0.0167 0.6368 1.0000
2.750 0.4439 0.00949 0.00320 -0.0162 0.6175 1.0000
3.000 0.4697 0.00959 0.00323 -0.0156 0.5982 1.0000
3.250 0.4958 0.00970 0.00330 -0.0151 0.5769 1.0000
3.500 0.5216 0.00985 0.00339 -0.0145 0.5554 1.0000
3.750 0.5477 0.01002 0.00351 -0.0141 0.5317 1.0000
4.000 0.5737 0.01022 0.00364 -0.0137 0.5078 1.0000
4.250 0.5995 0.01046 0.00380 -0.0132 0.4840 1.0000
4.500 0.6253 0.01073 0.00402 -0.0128 0.4591 1.0000
4.750 0.6511 0.01101 0.00426 -0.0125 0.4339 1.0000
5.000 0.6768 0.01132 0.00453 -0.0121 0.4087 1.0000
5.250 0.7022 0.01167 0.00482 -0.0118 0.3835 1.0000
5.500 0.7275 0.01204 0.00514 -0.0114 0.3582 1.0000
5.750 0.7526 0.01245 0.00551 -0.0111 0.3328 1.0000
6.000 0.7775 0.01288 0.00590 -0.0107 0.3068 1.0000
6.250 0.8022 0.01333 0.00632 -0.0104 0.2806 1.0000
6.500 0.8266 0.01383 0.00678 -0.0100 0.2546 1.0000
6.750 0.8507 0.01437 0.00729 -0.0096 0.2294 1.0000
7.000 0.8742 0.01497 0.00784 -0.0092 0.2057 1.0000
7.250 0.8972 0.01563 0.00848 -0.0088 0.1828 1.0000
7.500 0.9204 0.01626 0.00912 -0.0083 0.1605 1.0000
7.750 0.9425 0.01699 0.00981 -0.0078 0.1391 1.0000
8.000 0.9644 0.01773 0.01054 -0.0073 0.1181 1.0000
8.250 0.9852 0.01863 0.01142 -0.0066 0.0978 1.0000
8.500 1.0041 0.01973 0.01244 -0.0058 0.0777 1.0000
8.750 1.0220 0.02098 0.01372 -0.0048 0.0601 1.0000
9.000 1.0377 0.02243 0.01520 -0.0036 0.0474 1.0000
9.250 1.0511 0.02411 0.01694 -0.0022 0.0389 1.0000
9.500 1.0646 0.02559 0.01847 -0.0009 0.0318 1.0000
9.750 1.0767 0.02738 0.02042 0.0007 0.0269 1.0000
10.000 1.0833 0.02944 0.02250 0.0023 0.0216 1.0000
10.250 1.0933 0.03128 0.02455 0.0040 0.0189 1.0000
10.500 1.0999 0.03321 0.02665 0.0060 0.0170 1.0000
10.750 1.1029 0.03519 0.02874 0.0080 0.0157 1.0000
11.000 1.1049 0.03768 0.03136 0.0096 0.0150 1.0000
11.250 1.0993 0.04192 0.03584 0.0112 0.0141 1.0000
11.500 1.0947 0.04560 0.03978 0.0123 0.0139 1.0000
11.750 1.0860 0.04886 0.04331 0.0127 0.0135 1.0000
12.000 1.0808 0.05172 0.04640 0.0124 0.0130 1.0000
12.250 1.0723 0.05554 0.05044 0.0117 0.0128 1.0000
12.500 1.0586 0.06055 0.05569 0.0102 0.0131 1.0000
12.750 1.0501 0.06464 0.05998 0.0080 0.0123 1.0000
13.000 1.0299 0.07136 0.06692 0.0048 0.0129 1.0000
13.250 1.0149 0.07750 0.07323 0.0013 0.0131 1.0000
13.500 1.0078 0.08251 0.07840 -0.0026 0.0117 1.0000
13.750 0.9782 0.09242 0.08849 -0.0081 0.0133 1.0000
14.000 0.9558 0.10156 0.09776 -0.0137 0.0136 1.0000
14.500 0.7835 0.12225 0.11918 -0.0230 0.0179 1.0000
14.750 0.7429 0.13314 0.13013 -0.0297 0.0198 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 62 9.3% (mh62-il)